MSC Patran-Nastran Preference Guide Volume 2: thermal analsis

Table of contents :
Overview......Page 9
Using this Guide......Page 10
Thermal Material Properties......Page 11
Thermal Loads and Boundary Conditions......Page 13
Steady-State Analysis......Page 17
Transient Analysis......Page 19
References......Page 20
Getting Started - A Guided Exercise......Page 23
Objectives......Page 24
Start Patran......Page 25
Create a Database......Page 26
Create a Rectangular Geometric Surface......Page 29
Mesh the Surface with Elements......Page 30
Modify the Mesh (Reduce the Number of Elements)......Page 31
Assign Element Properties......Page 32
Define the Temperature at the Plate’s Bottom Edge......Page 35
Apply Heat Flux to the Plate’s Right Edge......Page 37
Apply Convection to the Plate’s Left Edge......Page 40
Perform a Steady-State Thermal Analysis......Page 43
Visualize the Thermal Results (Contour Plot)......Page 44
Building A Model......Page 47
Introduction......Page 48
Nodes......Page 49
Finite Elements......Page 51
Multi-Point Constraints......Page 52
Material Library......Page 53
Materials Form......Page 54
Constitutive Models......Page 57
Finite Element Properties......Page 58
Element Properties Form......Page 59
Loads and Boundary Conditions Form......Page 69
Load Cases......Page 106
Running a Thermal Analysis......Page 107
Review of the Analysis Form......Page 108
Analysis Form......Page 109
Translation Parameters......Page 113
Numbering Options......Page 114
Solution Types......Page 116
Solution Parameters......Page 118
Direct Text Input......Page 122
Subcases......Page 123
Subcase Parameters......Page 125
Output Requests......Page 132
Direct Text Input......Page 136
Subcase Select......Page 137
Results Processing and Visualization......Page 139
Reading Thermal Analysis Results......Page 140
Attach HDF5......Page 141
Read Output2 Form......Page 144
Attach XDB Form......Page 147
Results Visualization Options......Page 151
Contour Plots......Page 152
XY Plots......Page 154
Read Input File......Page 161
Review of Read Input File Form......Page 162
Read Input File Form......Page 163
Entity Selection Form......Page 165
Define Offsets Form......Page 167
Selection of Input File......Page 168
Reject Card Form......Page 169
Conflict Resolution......Page 170
Overview......Page 171
Example 1 - Transient Thermal Analysis......Page 172
Example 2 - Free Convection on Printed Circuit Board......Page 198
Example 3 - Forced Air Convection on Printed Circuit Board......Page 211
Example 4 - Thermal Contact Resistance......Page 230
Example 5 - Typical Avionics Flow......Page 240
Example 6 - Radiation Enclosures......Page 261
Example 7 - Axisymmetric Flow in a Pipe......Page 271
Example 8 - Directional Heat Loads......Page 287
Example 9 - Thermal Stress Analysis from Directional Heat Loads......Page 299
Example 10 - Thermal Stress Analysis of a Bi-Metallic Plate......Page 307
Files......Page 331
Files......Page 332
Error Messages......Page 333
Error Messages......Page 334
Supported Commands......Page 335
Case Control Commands......Page 336
Bulk Data Entries......Page 337

Citation preview



Patran 2018

Interface To MSC Nastran Preference Guide Volume 2: Thermal Analysis

Corporate

Europe, Middle East, Africa

MSC Software Corporation 4675 MacArthur Court, Suite 900 Newport Beach, CA 92660 Telephone: (714) 540-8900 Toll Free Number: 1 855 672 7638 Email: [email protected]

MSC Software GmbH Am Moosfeld 13 81829 Munich, Germany Telephone: (49) 89 431 98 70 Email: [email protected]

Japan

Asia-Pacific

MSC Software Japan Ltd. Shinjuku First West 8F 23-7 Nishi Shinjuku 1-Chome, Shinjuku-Ku Tokyo 160-0023, JAPAN Telephone: (81) (3)-6911-1200 Email: [email protected]

MSC Software (S) Pte. Ltd. 100 Beach Road #16-05 Shaw Tower Singapore 189702 Telephone: 65-6272-0082 Email: [email protected]

Worldwide Web www.mscsoftware.com

Support http://www.mscsoftware.com/Contents/Services/Technical-Support/Contact-Technical-Support.aspx

Disclaimer This documentation, as well as the software described in it, is furnished under license and may be used only in accordance with the terms of such license. MSC Software Corporation reserves the right to make changes in specifications and other information contained in this document without prior notice. The concepts, methods, and examples presented in this text are for illustrative and educational purposes only, and are not intended to be exhaustive or to apply to any particular engineering problem or design. MSC Software Corporation assumes no liability or responsibility to any person or company for direct or indirect damages resulting from the use of any information contained herein. User Documentation: Copyright 2018 MSC Software Corporation. All Rights Reserved. This notice shall be marked on any reproduction of this documentation, in whole or in part. Any reproduction or distribution of this document, in whole or in part, without the prior written consent of MSC Software Corporation is prohibited. This software may contain certain third-party software that is protected by copyright and licensed from MSC Software suppliers. Additional terms and conditions and/or notices may apply for certain third party software. Such additional third party software terms and conditions and/or notices may be set forth in documentation and/or at http://www.mscsoftware.com/thirdpartysoftware (or successor website designated by MSC from time to time). The MSC Software Logo, MSC, MSC Nastran, Marc, Patran, Dytran, and Laminate Modeler are trademarks or registered trademarks of MSC Software Corporation in the United States and/or other countries. NASTRAN is a registered trademark of NASA. PAM-CRASH is a trademark or registered trademark of ESI Group. SAMCEF is a trademark or registered trademark of Samtech SA. LS-DYNA is a trademark or registered trademark of Livermore Software Technology Corporation. ANSYS is a registered trademark of SAS IP, Inc., a wholly owned subsidiary of ANSYS Inc. ACIS is a registered trademark of Spatial Technology, Inc. ABAQUS, and CATIA are registered trademark of Dassault Systemes, SA. FLEXlm and FlexNet Publisher are trademarks or registered trademarks of Flexera Software. PostScript is a registered trademark of Adobe Systems, Inc. PTC and Pro/ENGINEER are trademarks or registered trademarks of Parametric Technology Corporation or its subsidiaries in the United States and/or other countries. Unigraphics, Parasolid and I-DEAS are registered trademarks of Siemens Product Lifecycle Management, Inc. All other brand names, product names or trademarks belong to their respective owners.

P3:V2018:Z:INT-NATHM:Z:DC-USR-PDF

Main Index

Documentation Feedback At MSC Software, we strive to produce the highest quality documentation and welcome your feedback. If you have comments or suggestions about our documentation, please write to us at [email protected]. Please include the following information with your feedback: 

Document name



Release/Version number



Chapter/Section name



Topic title (for Online Help)



Brief description of the content (for example, incomplete/incorrect information, grammatical errors, information that requires clarification or more details and so on.)



Your suggestions for correcting/improving documentation

You may also provide your feedback about MSC Software documentation by taking a short 5-minute survey at: http://mscdocumentation.questionpro.com.

Note:

Main Index

The above mentioned e-mail address is only for providing documentation specific feedback. If you have any technical problems, issues, or queries, please contact the Technical Support team at: http://www.mscsoftware.com/support/technical-support-programs-and-offerings.

Main Index

Contents Patran Interface to MSC Nastran Thermal

Contents

1

2

Main Index

Overview Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

2

Using this Guide . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

2

Thermal Material Properties . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

3

Thermal Loads and Boundary Conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

5

Thermal Analysis . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Steady-State Analysis. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Transient Analysis . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Steady-State and Transient Convergence Criteria . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

9 9 11 12 12

Getting Started - A Guided Exercise Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

16

Objectives . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

16

Start Patran . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

17

Create a Database . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

18

Create a Rectangular Geometric Surface . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

21

Mesh the Surface with Elements. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

22

Modify the Mesh (Reduce the Number of Elements) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

23

Specify Material Properties . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

24

Assign Element Properties. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

24

Define the Temperature at the Plate’s Bottom Edge . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

27

Apply Heat Flux to the Plate’s Right Edge . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

29

Apply Convection to the Plate’s Left Edge . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

32

Perform a Steady-State Thermal Analysis . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

35

Visualize the Thermal Results (Contour Plot) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

36

vi Patran Interface to MSC Nastran Thermal

3

4

5

Main Index

Building A Model Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

40

Finite Elements. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Nodes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Finite Elements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Multi-Point Constraints. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Coordinate Frames. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

41 41 43 44 45

Material Library . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Materials Form. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Constitutive Models . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Finite Element Properties . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Element Properties Form . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Loads and Boundary Conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Loads and Boundary Conditions Form . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Load Cases . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

45 46 49 50 51 61 61 98

Running a Thermal Analysis Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

100

Review of the Analysis Form . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Analysis Form . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Translation Parameters . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Numbering Options . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Solution Types . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Solution Parameters. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Direct Text Input . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

100 101 105 106 108 110 114

Subcases . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Subcase Parameters . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Output Requests . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Direct Text Input. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Subcase Select. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

115 117 124 128 129

Results Processing and Visualization Overview. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

132

Reading Thermal Analysis Results . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Attach HDF5. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Read Output2 Form . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Attach XDB Form . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

132 133 136 139

Contents vii

Results Visualization Options . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Contour Plots . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . XY Plots . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

6

7

A

Read Input File Review of Read Input File Form . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Read Input File Form. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Entity Selection Form . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Define Offsets Form . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Selection of Input File . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Summary Data Form. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Reject Card Form . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Data Translated from the NASTRAN Input File . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

154 155 157 159 160 161 161 162

Conflict Resolution . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

162

Example Problems Overview . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

163

Example 1 - Transient Thermal Analysis. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

164

Example 2 - Free Convection on Printed Circuit Board. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

190

Example 3 - Forced Air Convection on Printed Circuit Board. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

203

Example 4 - Thermal Contact Resistance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

222

Example 5 - Typical Avionics Flow . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

232

Example 6 - Radiation Enclosures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

253

Example 7 - Axisymmetric Flow in a Pipe . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

263

Example 8 - Directional Heat Loads . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

279

Example 9 - Thermal Stress Analysis from Directional Heat Loads. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

291

Example 10 - Thermal Stress Analysis of a Bi-Metallic Plate . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

299

Files Files. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

B

324

Error Messages Error Messages. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Main Index

143 144 146

326

viii Patran Interface to MSC Nastran Thermal

C

Supported Commands File Management Statements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

328

Executive Control Statements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

328

Case Control Commands . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

328

Bulk Data Entries . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

329

Index 333

Main Index

Chapter 1: Overview MSC Nastran Implicit Nonlinear (SOL 600) User’s GuidePatran Interface to MSC Nastran Thermal

1

Main Index

Overview



Introduction



Using this Guide



Thermal Material Properties



Thermal Loads and Boundary Conditions



Thermal Analysis



References

2

12

2

9

3 5

2

Patran Interface to MSC Nastran Thermal Introduction

Introduction The Patran MSC Nastran Heat Transfer Preference supports the full range of thermal analysis capabilities available within MSC Nastran. These capabilities include: 

conduction in one, two, and three dimensions



fundamental convection



one dimensional advection



radiant exchange with space



radiant exchange in enclosures



specified temperatures



surface and volumetric heat loads



elements of thermal control systems



contact conduction

MSC Nastran can span the full range of thermal analysis from system-level analysis of global energy balances to the detailed analysis associated with temperature and thermal stress limit levels. Within the integrated Patran-MSC Nastran environment, you can simulate linear, nonlinear, steady-state, and transient thermal behavior. You can apply loads and boundary conditions either on the model’s geometry or on its finite element entities.MSC Nastran’s sophisticated solution strategy automatically addresses the existence and extent of nonlinear behavior and adjusts the solution process accordingly.

Using this Guide This guide is written for both new and experienced users of Patran and MSC Nastran. It provides: 

practical, “how to” descriptions of thermal modeling, analysis, and results processing and visualization techniques



descriptions of the relevant Patran menu forms



basic engineering concepts and theory associated with MSC Nastran's thermal solution capabilities

The Patran on-line help system provides logical and efficient access to all of this material. The remainder of Overview (Ch. 1), describes heat transfer basics. It discusses the concepts of thermal material properties, loads and boundary conditions, steady-state and transient analysis, and convergence criteria. Getting Started - A Guided Exercise (Ch. 2), is designed to familiarize users quickly with the basic Patran menu interfaces to thermal modeling, steady-state analysis, and results processing. Before beginning, please review the Guided Tour at the top of the Patran on-line help system. Building A Model (Ch. 3), describes Patran's menu forms for each phase of thermal modeling:

Main Index



Meshing the geometric model with finite elements



Defining material properties



Specifying element properties



Applying loads and boundary conditions

Chapter 1: Overview Thermal Material Properties

Running a Thermal Analysis (Ch. 4), describes how to select steady-state or transient analysis solution types, define solution and subcase input data, select load cases, and submit the MSC Nastran analysis job. Results Processing and Visualization (Ch. 5), describes how to retrieve MSC Nastran thermal analysis results into the Patran database. This chapter also summarizes the options for sorting and graphically rendering analysis results as contour or XY plots. Example Problems (Ch. 7), presents more advanced engineering problems covering the following applications: 

Transient thermal analysis (using the same flat plate model, plate.db, created in Getting Started - A Guided Exercise (Ch. 2))



Free convection on a printed circuit board



Forced air convection on a printed circuit board



Thermal contact resistance



Typical avionics flow



Radiation enclosures



Axisymmetric flow in a pipe



Directional heat loads



Thermal stress analysis from directional heat loads



Thermal stress analysis of bi-metallic plate

Files (App. A), describes the files created when using the Patran MSC Nastran thermal preference product. Error Messages (App. B) describes general error and diagnostic messages. Supported Commands (App. C) describes the MSC Nastran input data used “behind the scenes,” including File

Management Statements, Executive Control Statements, Case Control Commands, and Bulk Data Entries.

Thermal Material Properties MSC Nastran thermal material properties include thermal conductivity, constant pressure specific heat, density, dynamic viscosity, internal heat generation, and temperature range and latent heat quantities associated with phase change phenomena.

Conductivity Thermal conductivity is an intrinsic property of all materials and in the absence of any other mode of heat transfer, provides the proportionality constant between the flow of heat through a region and the temperature gradient maintained across the region (Fourier’s Law). Thermal conductivity is generally a mild function of temperature, decreasing with increasing temperature for solids and generally increasing with increasing temperature for liquids and gases. Additionally, within a solid, thermal conductivity can vary due to material orientation (anisotropy). Preferential paths for heat flow can result. MSC Nastran allows for temperaturedependent and directionally dependent thermal conductivity.

Main Index

3

4

Patran Interface to MSC Nastran Thermal Thermal Material Properties

Specific Heat and Heat Capacitance Specific heat is another intrinsic material property. When multiplied by the volume and density of material, the quantity of interest is referred to as heat capacitance. Given a closed thermodynamic system, heat capacitance provides the proportionality constant between heat added or subtracted from the system and the resultant temperature rise or fall of the system (dq = C * dT). Since heat capacitance only multiplies the time derivative of temperature in the heat conduction equation, specific heat is usually only relevant in the solution of transient thermal phenomenon. We will note later that advection introduces a pseudo-transient flavor even in steady-state analysis and therefore the specific heat and density of the advecting fluid are needed in these calculations. Specific heat is also slightly temperature dependent. However, in typical heat transfer problems, the largest variations in specific heat are generally attributed to materials changing phase.

Density For the purpose of conserving mass, the density cannot be allowed to vary with temperature. Since grid points are fixed in space in MSC Nastran thermal analysis, if the density were to change with temperature, Density*Volume would also be changing, thus altering the system mass. Table 1-1 provides several sets of consistent units which may be used by MSC Nastran for the various material properties.

Table 1-1 Typical Units for Thermal Material Properties Table 1-2

Thermal Conductivity

Table 1-3

W Table 1-4 / m -

Btu/h r-fto F

o

C Table 1-5

Specific Heat

Table 1-6

J/ Table 1-7 k go

C

Main Index

Btu/l b moF

Chapter 1: Overview Thermal Loads and Boundary Conditions

Table 1-1 Typical Units for Thermal Material Properties Table 1-8

Density

Table 1-9

k Table 1-10 g/ m

lbm/ft 3

3

Table 1-11

Dynamic Viscosity

Table 1-12

k Table 1-13 g/ m s e c

lbm/ft -hr

Table 1-14

Enthalpy

Table 1-15

J/ k g

Table 1-16

Btu/l bm

Table 1-17

Latent Heat

Table 1-18

J/ k g

Table 1-19

Btu/l bm

Thermal Loads and Boundary Conditions MSC Nastran supports a full range of thermal boundary conditions and heat loads, starting with simple temperature constraints and heat flux boundary conditions, and moving on to more complicated heat transfer mechanisms associated with contact, convection and radiation. All of the thermal boundary conditions can be modeled as functions of time. Thermal boundary conditions can be applied to finite element entities as well as geometric entities and include the following: Table 1-20 Table 1-21

Typical Units for Thermal Loads and Boundary Conditions

Temperature

Table 1-22

oC

o

Table 1-23

oF

oR

K Table 1-24

Normal Heat Flux

Table 1-25

W/m Table 1-26

Btu/hr-ft2

Table 1-27

Directional Heat Flux

Table 1-28

W/m Table 1-29

Btu/hr-ft2

Table 1-30

Nodal Source

Table 1-31

W

Btu/hr

Table 1-33

Volumetric Generation

Table 1-34

W/m Table 1-35

Btu/hr-ft3

Table 1-36

Convection Heat Flow

Table 1-37

W/m Table 1-38

Btu/hr-ft2

Main Index

2 2

Table 1-32

3 2

5

6

Patran Interface to MSC Nastran Thermal Thermal Loads and Boundary Conditions

Table 1-20

Typical Units for Thermal Loads and Boundary Conditions

Table 1-39

Advection Heat Flow

Table 1-40

W

Table 1-42

Convection Heat Transfer Coefficient

Table 1-43

W/m Table 1-44 2-oC

Btu/hr-ft2oF

Table 1-45

Radiation to Space

Table 1-46

W/m Table 1-47

Btu/hr-ft2

Table 1-48

Radiation Enclosure

Table 1-49

W/m Table 1-50

Btu/hr-ft2

Note:

Table 1-41

2 2

Btu/hr

When applying flux type loads or boundary conditions to nodal points, the units will still be those of a flu per unit area. Patran’s input data forms for thermal loads and boundary conditions require you to specify a nodal area.

Temperature Boundary Conditions Temperature constraints can only be applied to nodal points. Temperature constraints can be defined as constant, spatially varying, or time varying.

Normal Heat Flux Normal heat flux is defined using the nodal, element uniform, or element variable loading operations. As with temperature boundary conditions, heat flux loads can be made to vary with space or time.

Directional Heat Flux MSC Nastran supports vector heat flux from a distant radiant heat source. This capability allows you to model phenomena such as diurnal or orbital heating. The required input for this capability includes: 

the magnitude of the flux vector



the absorptivity of the surface on which the flux is being applied



the vector components of the flux vector

The absorptivity can be dependent on temperature. The magnitude and components of the heat flux can be defined as constant, spatial varying, or time varying.

Nodal Source Heat can be applied directly on nodal points (or “grid points” in MSC Nastran terminology). Nodal source heat can be defined as constant, spatially varying in a global sense, or time varying.

Volumetric Heat Generation Volumetric heat can be applied to one or more conduction elements and can be defined as constant, spatially varying, or time varying. The Patran MSC Nastran interface also includes a heat generation multiplier for specifying temperature dependence. The multiplier feature is available in the input form used to specify the material property data.

Main Index

Chapter 1: Overview Thermal Loads and Boundary Conditions

Basic Convection Basic convection boundaries can be defined. The approach to basic convection heat transfer in MSC Nastran is to define the basic convection via a heat transfer coefficient and associated ambient temperature. The film coefficient is user specified and is available from a number of sources, including Reference 1. (p. 14). The film coefficient can be defined as a function of temperature; the ambient temperature can be defined as a function of time.

Advection, Forced Convection Advection, forced convection, is a complicated heat transfer phenomenon that includes aspects of heat transfer as well as fluid flow. MSC Nastran supports 1D fluid flow, which allows for energy transport due to streamwise advection and diffusion. Heat transfer between the fluid stream and the surroundings may be accounted for through a forced convection heat transfer coefficient based on locally computed Reynolds and Prandtl numbers; see Reference 1. (p. 14) and Reference 2. (p. 14) for more information on the underlying theory of this type of convection. The input for forced convection includes: 

the mass flow rate of the fluid



the diameter of the fluid pipe



the material properties of the fluid

The calculation of the heat transfer coefficient between the fluid and the adjoining wall requires the specification of a film temperature. By default, this temperature will be internally calculated as the average of the temperatures of the fluid and the adjoining wall. Additional forced convection inputs consist of the type of convection relationship used to calculate the energy transport and the method of calculating the heat transfer coefficient at the tube wall. There are two choices with respect to the energy transport. The default method includes advection and streamwise diffusion, and its theoretical basis is the Streamwise-Upwind Petrov-Galerkin method, or SUPG. There are also two choices for picking the method for calculating the heat transfer coefficient that applies between the fluid and the adjacent wall. The default method uses the following equation: h = Coef • Re

Expr

• Pr

Expp

(1-1)

The second method, chosen by picking the alternate formulation option, uses the following equation: k Expr Expp h =  --- • Coef • Re • Pr  d

Main Index

(1-2)

h

=

=the heat transfer coefficient between the fluid and the adjacent wall (internally calculated)

Coef

=

=a constant coefficient

7

8

Patran Interface to MSC Nastran Thermal Thermal Loads and Boundary Conditions

Re

=

=the Reynolds number based on the diameter (internally calculated)

Pr

=

=the Prandtl number (internally calculated)

Expr

=

=the Reynolds number convection exponent

Expp

=

=the Prandtl number convection exponent

k

=

=the fluid conductivity

d

=

=the tube diameter

Radiation to Space Radiation to space is a boundary condition that defines radiant exchange between a surface and blackbody space. The inputs required for radiation to space are the absorptivity and emissivity of the surface, the ambient temperature of space, and the radiation view factor between the surface and space (usually equal to 1.0). The absorptivity and emissivity can both be temperature dependent. The ambient temperature can vary with time. The exchange relationship is defined to be: 4

q = σ • View fac • ( ε e T e – α e T amb )

4

(1-3)

q

=

=the net energy flux in W/m2 (internally calculated)

σ

=

=the Stefan-Boltzmann constant which has the value 5.668x10-8 W/m2 oK4 [0.1714x10-8 Btu/h ft2 oR4]

Viewfac

=

=the view factor

εe

=

= the emissivity

αe

=

=the absorptivity (usually α e = ε e )

Te

=

=the temperature of the element (internally calculated)

Tamb

=

=the ambient temperature of space (user specified)

Calculation of radiation exchange requires that the temperatures be defined on an absolute scale (Kelvin or Rankine). If the temperatures input in a problem involving radiation are either Celsius or Fahrenheit, an internal conversion can be defined.

Radiation Enclosures Radiation Enclosure exchange is similar to the Radiation to Space boundary condition; however, this type of boundary condition takes into account the radiation exchange between discrete surfaces. As a result, subsequent to building a finite element mesh, the geometric relationship (view factor) between individual finite element surfaces must be determined. For enclosure radiation the view factors between surfaces are internally calculated. Also, for enclosure radiation, the absorptivity is taken as being equal to the emissivity (Kirchhoff ’s Identity).

Main Index

Chapter 1: Overview Thermal Analysis

Calculation of the radiation view factors can be the most computationally intensive operation in heat transfer analysis. MSC Nastran has implemented a unique set of algorithms for solving this problem which provides for both reasonable performance while maintaining an accurate calculation. To help facilitate this calculation, the Can Shade and Can Be Shaded options have been added for those situations where the shading is known. These options can help reduce the calculation time for radiation enclosures. Patran also allows you to define multiple radiation enclosures. The view factors within each Radiation Enclosure will be independently calculated from the view factors of the other enclosures. In general, good view factor calculations require a reasonable surface mesh. Since the accuracy of the view factors tends to decrease as the distance between elements is reduced and becomes on the order of the element size, a mesh which prevents this sizing issue is recommended and is generally not too restrictive.

Contact Conduction If contact bodies are present in the model for a SOL 153, 159 or 600 analysis heat transfer will occur between the contact bodies based on the properties defined on the contact bodies or via the contact table accessible from the subcase parameters for. as the bodies get closer the contact changes from radiation to convection to conduction. See the MSC Nastran Quick Reference Guide for more information.

Thermal Analysis Thermal problems can be categorized as steady-state or transient, linear or nonlinear. Transient analyses are characterized by solution evolution over time, and in addition to energy exchange with the environment, involves thermal energy storage. Steady-state analyses are concerned with state point solutions to fixed boundary condition problems. Nonlinearities enter into both steady-state and transient solutions through several areas. The most common nonlinearity is associated with temperature dependent material properties, in particular thermal conductivity and specific heat. Other nonlinearities are introduced from application of boundary conditions principally convection and radiation. All nonlinear analyses necessarily involve solution iteration, error estimation, and some form of convergence criteria. MSC Nastran attempts to do this as efficiently and trouble free as possible.

Steady-State Analysis The most general form of the steady-state heat balance equation is as follows: 4

(1-4)

[ K ] { u } + [ ℜ ] { u + T abs } = { P } + { N }

Main Index

[K]

=

=the heat conduction matrix

[ℜ]

=

=the radiation exchange matrix

{u}

=

=the vector of unknown temperatures

Tabs

=

=the temperature offset from absolute required for radiation calculations (absolute temperature)

9

10

Patran Interface to MSC Nastran Thermal Thermal Analysis

{P}

=

=the vector of constant applied heat flows

{N}

=

=the vector of temperature dependent heat flows

This equation is inherently nonlinear due to the presence of the fourth power law radiation term. In addition to the radiation term, many other nonlinearities may be introduced into this equation through the coefficient matrices and boundary condition terms. Specifically, nonlinearities are introduced by specifying the material properties and boundary conditions as temperature dependent as discussed in the Thermal Material Properties, 3 and Thermal Loads and Boundary Conditions, 5. MSC Nastran applies a Newton-Raphson iteration scheme for the solution of these nonlinear equations. This process leads to the following form of the heat balance equation: i

i

[ K T ] { Δu } = { R }

[ KT ]

i

i

(1-5)

=

=the tangential conductance matrix i

= {R}

i

=

3  δN  i i i i { Δu } ≅ [ K ] + 4 [ R ] { u + T abs } –  -------   δu 

=the residual vector {P}i + {N}i - [K]i {u}i - [R]i {ui + Tabs}4

At each iteration, the left-hand side matrix and the right-hand side vector are computed based on the temperature from the previous iteration ( u i ) . By solving for the unknown vector ( Δu i ) , the new temperatures (u

i+1

)

i

can be determined:

{ Δu } = { u

i+1

i

(1-6)

–u}

or {u}

i+1

= { Δu } + { u }

i

(1-7)

Because of the expense of performing matrix decompositions, MSC Nastran recalculates the residual vector at each iteration, but only recalculates the tangent matrix when convergence is illusive or if it will lead to improvement in the iteration efficiency. MSC Nastran will attempt to achieve an optimum converged solution by balancing various solution aspects such as: load bisection, residual updates, tangent matrix updates, line searches, and BFGS updates. Further description of the methods employed can be found in Reference 2. (p. 14). For steady-state analysis, the defaults for controlling the nonlinear solution should be sufficient for most problems. For those problems where additional control is required, the convergence tolerances for Temperature, Load, and Work can be overridden. See Steady-State and Transient Convergence Criteria, 12 for more information.

Main Index

Chapter 1: Overview Thermal Analysis

Initial Conditions in Steady-State Analysis Since the nonlinear equations are solved by an iterative scheme, careful consideration of the initial conditions can have a significant effect on how quickly a problem will converge, or if it will converge at all. The initial conditions provide the starting point temperatures for the iterative solution method. Clearly, if we were able to exactly guess the solution to our problem, the process would converge on the first iteration, as it must for linear analysis. Although this is highly unlikely, a good initial guess can speed up the convergence process significantly. For highly nonlinear problems, good initial temperature estimates may be required in order to achieve convergence. See Initial Conditions in Transient Analysis, 12 for more information.

Transient Analysis The most general form of the transient heat balance equation is: 4 [ B ] { u· } + [ K ] { u } + [ ℜ ] { u + T abs } = { P } + { N }

(1-8)

where, in addition to the terms already defined in the steady-state equation, we have: [B] = the heat capacity matrix.

(1-9)

du u· = -----dt

(1-10)

Because of its transient behavior, this equation must be integrated over time. The numerical method implemented for performing the time integration is Newmark’s method. As in the steady-state case, this equation also can be extensively nonlinear due to radiation and temperature-dependent material properties and boundary conditions. As a result, nonlinear iterations are also required for the solution of this equation. The iteration is performed within each time step until a converged solution for that time step is achieved (see Reference 2. (p. 14) for more details). Transient analysis requires specifying the total solution time. Solution time is defined by the initial time step size and total number of time steps requested. The total solution time is determined from their product. Because MSC Nastran employs an automatic time stepping scheme (i.e., the time step is varied by the solver as the solution progresses), the actual number of time steps used may ultimately be quite different from the input request. In any event, the total amount of solution time will be approximately equal to the initially calculated product within some small tolerance of the last time step size. The advantage of using the adaptive time step algorithm is the potential for significantly reduced run times. To avoid inaccurate results or unstable solutions, the proper choice of the initial time step is required. A responsible initial time step is dependent on a number of factors, including the spatial size of the element mesh and the thermal diffusivity of the material. The selection criteria is: ρ ⋅ Cp 1 Δt 0 ≅ ------ ⋅ Δx 2 ⋅ -------------10 k

Main Index

(1-11)

Δt 0

=

=the initial time step

Δx

=

=the mesh size

11

12

Patran Interface to MSC Nastran Thermal References

ρ

=

=the density

Cp

=

=the specific heat

k

=

=the conductivity

Initial Conditions in Transient Analysis Initial conditions define the temperature starting point for a transient analysis. Every node in the problem must have an initial temperature explicitly defined. Any node that does not have an initial temperature defined will automatically have a temperature of 0.0 assigned to it. This default temperature can be changed in the Solution Parameters form for the given application, either steady-state or transient analysis. Caution must be exercised when specifying initial conditions relative to any specified temperatures defined via a boundary condition. The initial condition temperature for these nodal points must match the (Implicit and Explicit) boundary condition temperature at time equal to zero. Failure to match these temperatures will cause an initial jump in the solution that can make convergence difficult to achieve. Fortunately, the default analysis setup will automatically enforce these temperatures to be equal at the start of the problem.

Steady-State and Transient Convergence Criteria As discussed previously, the solution of the nonlinear equations requires an iteration scheme. Efficient iteration schemes are highly dependent on convergence criteria and error estimation. Convergence criteria provide a means of measuring solution error relative to some predetermined acceptable level. For each iteration performed during the solution process, error levels are calculated and compared with preset tolerances. Three convergence criteria are available within MSC Nastran that measure error based on temperature, load, and work. These criteria apply to steady-state and transient solutions alike. Four recommendations regarding nonlinear convergence can be made: 1. For most problems, use the default criteria selection with their default tolerance values. 1. If the analysis is transient and involves any time-varying temperature boundary conditions, you must use the temperature convergence criteria. 1. Convergence may be enhanced by increasing the numerical tolerance levels from their default values. 1. For highly nonlinear transient problems, the maximum number of iterations per time step may be increased. The defaults for controlling the nonlinear solution should be sufficient for most problems. However, for those problems requiring additional control, the convergence tolerances for Temperature, Load, and Work can be overridden. (In the solution of heat transfer problems, a convergence criteria based on WORK is realistically just a mathematical construct representing an extension of the equations used in the comparable structural solver.)

References 1. Holman, J. P., Heat Transfer, Sixth Edition, McGraw-Hill Book Company, 1986.

Main Index

Chapter 1: Overview References

2. Chainyk, Mike, MSC/NASTRAN Thermal Analysis User’s Guide, Version 68, The MacNealSchwendler Corporation, 1994. 3. Peterson, Ken (ed.), MSC/NASTRAN Encyclopedia, Online Documentation CD-ROM, The MacNeal-Schwendler Corporation, 1995.

Main Index

13

14

Patran Interface to MSC Nastran Thermal References

Main Index

Chapter 2: Getting Started - A Guided Exercise MSC Nastran Implicit Nonlinear (SOL 600) User’s GuidePatran Interface to MSC Nastran Thermal

2

Main Index

Getting Started - A Guided Exercise 

Introduction



Objectives



Start Patran



Create a Database



Create a Rectangular Geometric Surface



Mesh the Surface with Elements



Modify the Mesh (Reduce the Number of Elements)



Specify Material Properties

24



Assign Element Properties

24



Define the Temperature at the Plate’s Bottom Edge



Apply Heat Flux to the Plate’s Right Edge

29



Apply Convection to the Plate’s Left Edge

32



Perform a Steady-State Thermal Analysis

35



Visualize the Thermal Results (Contour Plot)

16 16 17 18 21

22

36

23

27

16

Patran Interface to MSC Nastran Thermal Introduction

Introduction This guided exercise shows you in step-by-step fashion the basics of MSC Nastran thermal modeling, analysis, and results visualization using Patran. By intention, the geometry is simple, as are the applied loads and boundary conditions. We will create the geometry for a rectangular metal plate, mesh it with quadrilateral elements, specify material and element properties, apply thermal loads and boundary conditions, run a steady-state thermal analysis to determine temperature distributions, and visualize the results using Patran’s postprocessor. Before attempting this exercise, please complete the guided tour provided at the top of the Patran on-line help system. It gives you an overview of the Patran user interface, including the layout of the main form, the various application selections, the use of menus and forms, mouse picking, and basic modeling operations. Although the menu options for thermal analysis differ from those for structural analysis, Patran has a common look-and-feel across both disciplines.

Objectives The objectives in this exercise are to: 

Create a new database defined for MSC Nastran thermal analysis.



Define geometry for a rectangular plate.



Mesh the structure with quadrilateral elements.



Modify the mesh.



Main Index

Define the plate’s material as aluminum. Specify a thermal conductivity of 204 W/m-oC, specific heat of 896 J/kg-oC, and a density of 2707 kg/m3.



Define the plate’s thickness to be 0.1 m.



Clean up the display.



Apply a temperature of 50 oC to the bottom edge of the plate.



Apply heat flux of 5000 W/m2 to the right edge of the plate.



Apply to the left edge of the surface a convection boundary condition with heat transfer coefficient of 10.0 W/m2-oC and ambient temperature of 20 oC.



Perform a steady-state thermal analysis using MSC Nastran within the Patran system.

Chapter 2: Getting Started - A Guided Exercise Start Patran



Visualize the temperature distribution as a contour plot. 1m

Aluminum Plate K = 204 W/m-oC Cp = 896 J/kg-oC

ρ = 2707 kg/m3 h = 10.0 W/m2-oC 3m

q = 5000.0 W/m2

Tamb = 20.0 oC

Thickness = 0.1 m

T = 50 oC

Start Patran To begin the Patran modeling session from your workstation’s XTERM window, enter the command patran or patran & (if you want to run the application in the background).

Main Index

17

18

Patran Interface to MSC Nastran Thermal Create a Database

Create a Database From Patran’s main form, pull down the File menu and select New.

Main Index

Chapter 2: Getting Started - A Guided Exercise Create a Database

A form will appear called New Database. NOTE: If only the MSC Nastran Preference is accessed by the model, the mscnastran_template.db can be used as template database to save disk space.

STEP 2: Click on OK.

STEP 1: Position the cursor inside the New Database Name databox. Type in the word plate.

Main Index

19

20

Patran Interface to MSC Nastran Thermal Create a Database

The New Model Preferences form will appear, which will display MSC Nastran as the default analysis solver.

STEP 3: Toggle the Analysis Type setting to Thermal.

STEP 4: Click on OK.

Main Index

Chapter 2: Getting Started - A Guided Exercise Create a Rectangular Geometric Surface

Create a Rectangular Geometric Surface Click on the Geometry application. The Geometry form will appear.

STEP 1: Change the settings to: Action:Create Object:Surface Method:XYZ

STEP 2: Under Vector Coordinate List, we can enter the desired XYZ dimensions for our surface. Type in the databox. Note: you must use angle brackets to define vectors. You must use square brackets to define coordinates. Make sure to provide a space between each number. STEP 3: Make sure that the Origin Coordinate List is [0 0 0], which is the default. STEP 4: Click on Apply.

Main Index

21

22

Patran Interface to MSC Nastran Thermal Mesh the Surface with Elements

Mesh the Surface with Elements Click on the Finite Elements application. The Finite Elements form will appear.

STEP 1: Toggle the Object setting to Mesh.

STEP 2: Click inside the databox under the heading Surface List. You can now use the mouse to click on the actual surface you want to mesh. Click anywhere on the surface we have made. The Global Edge Length is 0.1, which is the default setting. We will leave this value as is for now. (We will change it later, after we mesh the surface.) The global edge length specifies the physical length of each element. If you are making 10 elements to comprise 1 unit (for example, 1 m) in length, you would specify an edge length of 0.1 to create 300 elements. STEP 3: Click on Apply. A mesh of 300 quadrilateral elements will be generated on the surface with elements automatically numbered.

Main Index

Chapter 2: Getting Started - A Guided Exercise Modify the Mesh (Reduce the Number of Elements)

Modify the Mesh (Reduce the Number of Elements) At this point, we will invoke Patran's undo feature so that we can make a coarser mesh. The mesh we have just created (300 elements) is excessive for our example. Table 2-1 STEP 1: Click on the erasure icon at the top right corner of the Patran main form. The

word undo will appear, and Patran will automatically delete the created mesh (the last specified action).

STEP 2: Click on the paintbrush icon. The words Refresh Graphics will appear, and the geometric surface will be regenerated exactly as it appeared before we applied the mesh.

The resulting mesh (75 elements) is now more to our liking.

STEP 3: Note that the Finite Elements form is still visible. Change the Global Edge Length from 0.1 to 0.2. This will create elements of 0.2 units (meters) in length, which will result in a coarser mesh of 75 quadrilateral elements. Click on Apply.

Main Index

23

24

Patran Interface to MSC Nastran Thermal Specify Material Properties

Specify Material Properties Our material for this exercise will be aluminum. Click on the Materials application. The Materials form will appear with certain default options. STEP 3: The Input Options form will appear. Edit the form to specify a thermal conductivity of 204, specific heat of 896, and a density of 2707.

STEP 1: Type in alum under Material Name. STEP 2: Click on Input Properties.

STEP 4: Click on Apply.

Assign Element Properties Our next task is to specify a thickness of 0.1 to our aluminum elements. Click on the Properties application. The Element Properties form will appear.

Main Index

Chapter 2: Getting Started - A Guided Exercise Assign Element Properties

STEP 1: Click inside the Property Set Name databox. Type in the name plate. STEP 2: Click on Input Properties. STEP 3: The Input Properties form appears. The word alum will appear within the Material Property Sets listbox. Click on this word. The Material Name databox will now appear as m:alum. STEP 4: Type in 0.1 in the Thickness databox.

STEP 5: Click on OK. STEP 6: From the Element Properties form, click on the Select Members databox. Patran will display icons to the left of the Element Properties form. The first icon represents surface or face; the second represents 2D element. The two options allow you to apply properties either on the geometric entity (in this case, the surface) or on the finite elements.

Main Index

25

26

Patran Interface to MSC Nastran Thermal Assign Element Properties

STEP 7: We will apply properties directly on the geometry. Pick the top icon; it will be highlighted when you pick it.

STEP 8: Now click anywhere on the geometric surface. The surface will be highlighted in red. The Select Members databox will now appear as Surface 1. STEP 9: Click on Add at the bottom of the Element Properties form.

STEP 10: Click on Apply.

Main Index

Chapter 2: Getting Started - A Guided Exercise Define the Temperature at the Plate’s Bottom Edge

Define the Temperature at the Plate’s Bottom Edge Click on the Loads/BCs application. The Loads/Boundary Conditions form will appear.

STEP 1: Change the settings to: Object:Temp (Thermal) Type:Nodal

STEP 4: Click in the Boundary Temperature databox and type in 50.

STEP 2: Type in a New Set Name in the databox. We will call it tempbc.

STEP 3: Click on Input Data. The Input Data form will appear.

STEP 6: Click on the Select Application Region. The Select Application Region form will appear.

Main Index

27

28

Patran Interface to MSC Nastran Thermal Define the Temperature at the Plate’s Bottom Edge

STEP 7: Under Geometry Filter, the default setting is Geometry. To the left, five options are given, represented as icons: Geometric entity, Point or Vertex, Curve or Edge, Surface or Face, Solid. STEP 8: Click on Curve or Edge. This icon will be highlighted, indicating that it has been selected.

STEP 9: With your mouse, position the cursor on the bottom edge of the surface. Click on the edge. You will see Surface 1.4 appear in the Select Geometry Entities databox. This means we have selected Edge number 4 in Surface number 1. STEP 10: Click on Add.

STEP 11: Click on OK. You must also click on Apply located on the Loads/Boundary Conditions form.

Note: A label on the bottom of your model will appear showing a boundary condition of 50 oC applied to the desired edge of the surface.

Main Index

Chapter 2: Getting Started - A Guided Exercise Apply Heat Flux to the Plate’s Right Edge

Apply Heat Flux to the Plate’s Right Edge We will now apply heat flux to the model using the Loads/Boundary Conditions form.

STEP 1: Change the settings to: Object:Applied Heat Type:Element Uniform Option:Normal Fluxes

STEP 2: Click inside the New Set Name databox. Type in the name flux. STEP 3: Because the problem is a 2D one, we need to toggle the Target Element Type setting to 2D. Even though we are applying heat flux along an edge, which we normally think of as 1D, our finite element problem is 2D; i.e., we are modeling heat conduction in two dimensions. STEP 4: Click on the Input Data button. The Input Data form will appear.

Main Index

29

30

Patran Interface to MSC Nastran Thermal Apply Heat Flux to the Plate’s Right Edge

STEP 5: Toggle the Surface Option setting from Top to Edge. STEP 6: Click inside the databox under Edge Heat Flux. Type in 5000.

STEP 7: Click on OK.

Main Index

Chapter 2: Getting Started - A Guided Exercise Apply Heat Flux to the Plate’s Right Edge

Next, click on Select Application Region located on the Loads/Boundary Conditions form.

STEP 8: Icon choices will appear, Curve or Edge, Surface or Face, and Solid. Click on Curve or Edge.

STEP 9: Click on Add.

STEP 10: A yellow flag will appear on the right edge of your surface indicating that a heat flux of 5000 W/m2 has been applied along the right edge.

Main Index

31

32

Patran Interface to MSC Nastran Thermal Apply Convection to the Plate’s Left Edge

Apply Convection to the Plate’s Left Edge We will now apply a convection boundary condition to the left edge of the plate--again, using the Loads/Boundary Conditions form.

STEP 1: Change the settings to: Object:Convection Type:Element Uniform Option:To Ambient

STEP 2: Click inside the New Set Name databox and type in conv. STEP 3: Toggle the Target Element Type setting to 2D.

STEP 4: Click on the Input Data button. The Input Data form will appear.

Main Index

Chapter 2: Getting Started - A Guided Exercise Apply Convection to the Plate’s Left Edge

STEP 5: Change the Surface Option setting to Edge.

STEP 6: Click inside the Edge Convection Coef databox and type in 10. STEP 7: Type in an Ambient Temperature of 20.

STEP 8: Click on OK.

Main Index

33

34

Patran Interface to MSC Nastran Thermal Apply Convection to the Plate’s Left Edge

Next, click on Select Application Region located on the Loads/Boundary Conditions form. STEP 9: Icon choices will appear, Curve or Edge, Surface or Face, and Solid. Click on Curve or Edge.

STEP 11: Click on Add.

STEP 10: Position the cursor over the left edge of the surface and click on this edge with the mouse. Patran will insert Surface 1.1 in the databox under Select Surfaces or Edges.

STEP 12: Click on OK. Be sure to click on Apply located on the Loads/Boundary Conditions form.

A green label will appear confirming that you have applied a convection coefficient of 10.0 W/m2-oC at this location of your model.

Main Index

Chapter 2: Getting Started - A Guided Exercise Perform a Steady-State Thermal Analysis

Perform a Steady-State Thermal Analysis We are now ready to submit the model for MSC Nastran steady-state thermal analysis. Click on the Analysis application located on the Patran main form. The Analysis form will appear. STEP 1: Change the settings to: Action:Analyze Object:Entire Model Method:Full Run Note: The Full Run Method will run the job in the background. If Method is changed to Analysis Deck, Patran will translate the MSC Nastran input file but will not run the job.

STEP 2: Make sure that the Job Name setting is plate.

Note: In the background, Patran will submit the needed input data information to the MSC Nastran solver. The heartbeat icon at the top right of Patran main form will turn blue, indicating that Patran’s forward translator and MSC Nastran are active in the background. (In your XTERM windows, from which you launched Patran, you can similarly note a message indicating that MSC Nastran has been executed.) When the analysis is completed, you are ready to visualize the results.

STEP 3: Click on Apply.

Main Index

35

36

Patran Interface to MSC Nastran Thermal Visualize the Thermal Results (Contour Plot)

Visualize the Thermal Results (Contour Plot) MSC Nastran has now finished its processing, and the thermal results are ready to be displayed. To visualize the results in Patran, you must first access the OUTPUT2 results data created by MSC Nastran.

STEP 1: Change the settings to: Action:Read Output2 Object:Result Entities Method:Translate

STEP 2: Make sure that the Job Name setting is plate.

STEP 3: Click on the Select Results File button. A new form will appear called Select File that lists all the available output2 files. (Note that these files all have the extension .op2). STEP 4: Double click on the file called plate.op2. STEP 5: Click on Apply. The heartbeat will change to the color blue, indicating that postprocessing is underway.

Main Index

Chapter 2: Getting Started - A Guided Exercise Visualize the Thermal Results (Contour Plot)

When the heartbeat becomes green again, click on the Results application selection located on the Patran main form. The Results Display form will appear.

STEP 1: In the Results form, make sure the Default, PW Linear: 100% of Load selection is highlighted in the Select Result Cases listbox.

STEP 2: Within the Select Fringe Result listbox, highlight Temperatures.

STEP 3: Click on Apply.

Main Index

37

38

Patran Interface to MSC Nastran Thermal Visualize the Thermal Results (Contour Plot)

A contour plot displaying temperature distributions will appear as follows:

Select the Save and Close operations from the File menu to save your plate.db file. We will perform a transient thermal analysis on this model in Example Problems (Ch. 7). You have now learned the basics of steady-state thermal analysis using Patran and MSC Nastran. Example 1 Transient Thermal Analysis (Ch. 7) builds on this example. The remaining examples in Example Problems (Ch. 7) describe more advanced applications.

Main Index

Chapter 3: Building A Model MSC Nastran Implicit Nonlinear (SOL 600) User’s GuidePatran Interface to MSC Nastran Thermal

3

Main Index

Building A Model



Introduction



Finite Elements



Coordinate Frames



Material Library



Finite Element Properties



Loads and Boundary Conditions



Load Cases

40

98

41 45 45 50 61

40

Patran Interface to MSC Nastran Thermal Introduction

Introduction Building a model for heat transfer analysis can be divided into several steps: Import or create the geometry

You can either import the geometry for your model from a CAD definition or create it within Patran. For a complete description of this process, see Patran Reference Manual, Part 2: Geometry Modeling.

Define the finite element mesh The objective of this step is to subdivide the geometry into nodes and elements. Temperatures are calculated at the nodal points in the analysis. Heat conduction takes place within the elements. This step is described briefly in Finite Elements, 41. For more complete information, see Patran Reference Manual, Part 3: Finite Element Modeling. Define material properties

In a steady-state conduction analysis, the thermal conductivity of one or more materials must be defined. In a transient analysis, the specific heat and density of the materials must also be defined. Sophisticated analyses may also require latent heat or fluid viscosity to be defined. This step is described in Material Library, 45.

Define element properties

The elements that define the heat conduction paths in the body can be characterized geometrically as 1D, 2D, 3D, or axisymmetric. All elements have associated material properties. In addition, one-dimensional elements must have their cross-sectional properties defined, and shell elements must have their thickness defined. This step is described in Finite Element Properties, 50.

Define loads and boundary conditions

Defining loads and boundary conditions is often the most difficult step in building a model for thermal analysis. In a steady-state analysis, fixed temperatures can be specified at any nodal points in the model. This applies to structural nodal points as well as ambient nodal points. In a transient analysis, temperatures specified on nodal points may be fixed or time varying. In addition to specifying temperatures, you can apply numerous other boundary conditions, including several forms of convection and radiation. Applied surface or volumetric heat flux or heat flow are described as thermal loads. Initial temperatures are specified for two primary reasons. In a transient analysis, the full mathematical description of the Fourier problem requires the statement of the initial condition, for heat transfer the beginning temperature. In a nonlinear steady-state analysis, the MSC Nastran solver necessarily employs an iterative scheme in solving the system equations, and it requires a starting temperature to initialize the process. For more information, see Loads and Boundary Conditions, 61.

Main Index

Chapter 3: Building A Model Finite Elements

Finite Elements The Finite Elements Application in Patran provides options for creation of nodes, elements, and multi-point constraints in the thermal finite element model.

For more information on how to create finite element meshes, see Mesh Seed and Mesh Forms (p. 22) in the Reference Manual - Part III. For information on the concepts of multi-point constraints, see the Patran Thermal User’s Guide, Volume 1: Thermal/Hydraulic Analysis.

Nodes Nodes in Patran will translate into unique GRID Bulk Data entries in MSC Nastran. Nodes can be created either directly using the Node object, or indirectly using the Mesh object. Each node has associated Reference (CP) and Analysis (CD) coordinate frames. The ID is taken directly from the assigned node ID. The X1, X2, and X3 fields (Node Location List) are defined in the specified CP coordinate frame. If no reference frame is assigned, the global system is used. The PS and SEID fields on the translated GRID entry are left blank.

Main Index

41

42

Patran Interface to MSC Nastran Thermal Finite Elements

Parameter Coordinate Frame

Description The analysis frame (CD of the GRID) is the ID of the coordinate system in which the loads and boundary conditions are defined. It is also the reference coordinate system for any output in vector format such as temperature gradients and heat fluxes. The coordinate system in which the node location is defined (CP of the GRID) can be the reference coordinate frame, the analysis coordinate frame, or a global reference (blank), depending on the value of the forward translation parameter “Node Coordinates.”

Main Index

Chapter 3: Building A Model Finite Elements

Finite Elements The Finite Elements application in Patran assigns element connectivity, such as Quad/4 (CQUAD4), for standard finite elements. The type of MSC Nastran element to be created is not determined until the element properties are assigned. See the Element Properties Form, 51 for details concerning the MSC Nastran element types. Elements can be created either explicitly using the Element object or implicitly using the Mesh object

Note:

Main Index

Elements not referenced by an element property region that is recognized by the Patran MSC Nastran forward translator will not be translated.

43

44

Patran Interface to MSC Nastran Thermal Finite Elements

Multi-Point Constraints Multi-point constraints (MPCs) can also be created from the Finite Elements menu. These are special element types that define a rigorous algebraic relationship between several specified nodes. The forms for creating MPCs are found by selecting MPC as the Object on the Finite Elements form. For MSC Nastran thermal analysis, the MPC object is used to implement temperature coupling.

Parameter MPC ID

Note:

Main Index

Description Creates an explicit MPC between a dependent grid point and one or more independent grid points. This constraint is used to specify a grid point temperature to be a weighted combination of any number of other grid point temperatures. The dependent term consists of a node ID, while an independent term consists of a coefficient and a node ID. An unlimited number of independent terms can be specified, while only one dependent term can be specified; A1T1+A2T2+....AnTn = 0 where T1 must be defined to be the dependent node temperature.

1. Patran automatically sets the A1 field on the MPC entry to -1.0. 2. When specifying initial temperature conditions, the nodal temperatures associated with the node points in an MPC must identically satisfy the MPC constraint equation.

Chapter 3: Building A Model Coordinate Frames

Coordinate Frames Coordinate frames will generate a unique CORD2R, CORD2C, or CORD2S Bulk Data entry, depending on the specified coordinate frame type. The CID field is defined by the Coord ID assigned in Patran. The RID field may or may not be defined, depending on the coordinate frame construction method used in Patran. The A1, A2, A3, B1, B2, B3, C1, C2, and C3 fields are derived from the coordinate frame definition in Patran. Only Coordinate Frames that are referenced by nodes, element properties, or loads and boundary conditions can be translated. For more information on creating coordinate frames, see Creating Coordinate Frames (p. 447) in the Geometry Modeling - Reference Manual Part 2.

Material Library The Materials form will appear when you select Materials from the main form. The selections made on the Materials menu will determine which material form appears, and ultimately, which MSC Nastran material will be created. The following pages give an introduction to the Materials form and details of all the material property definitions supported by the Patran MSC Nastran Thermal Application Preference. Only material records that are referenced by an element property region will be translated. References to externally defined materials will result in special comments in the MSC Nastran input file, e.g., materials that property values are not defined in Patran. The Patran MSC Nastran forward translator will perform material type conversions when needed. This translation applies to both constant material properties and temperature-dependent material properties.

Main Index

45

46

Patran Interface to MSC Nastran Thermal Material Library

Materials Form This form appears when you select Materials from the main menu. The Materials form provides options for specifying MSC Nastran material data.

Parameter

Main Index

Description

Object

Defines the basic material directionality and can be set to Isotropic, 2D Orthotropic, 3D Orthotropic, 2D Anisotropic, or 3D Anisotropic

Existing Materials

Lists the existing materials with the specified directionality.

Material Name

Defines the material name. A unique material ID will be assigned during translation

Chapter 3: Building A Model Material Library

Parameter

Description

Description

Describes the material that is being created.

Input Properties

Generates a form that is used to define the material properties.

Change Material Status

Generates a form that is used to indicate the active portions of the material model. By default, all portions of a created material model are active.

The following table outlines the material properties for MSC Nastran thermal analysis.

Object Isotropic

Constitutive Model Solid properties

Fluid properties

Phase changes

2D Orthotropic

MAT4, MATT4

MAT4, MATT4

MAT4

Temp Dep

Input Data Thermal Conductivity

yes

Specific Heat

yes

Density

no

Thermal Conductivity

yes

Specific Heat

yes

Density

no

Dynamic Viscosity

yes

Reference Enthalpy

no

Phase Change Temperature

no

Phase Change Temp. Range

no

Latent Heat

no

Heat generation

MAT4, MATT4

Heat Generation Multiplier

yes

Solid properties

MAT5, MATT5

Thermal Conductivity Kx/Kr

yes

Thermal Conductivity Ky/Kz

yes

Specific Heat

yes

Density

no

Heat Generation Multiplier

yes

Heat generation

Main Index

MSC Nastran Bulk Data

MAT5, MATT5

47

48

Patran Interface to MSC Nastran Thermal Material Library

Object 3D Orthotropic

2D Anisotropic

3D Anisotropic

Constitutive Model Solid properties

MAT5, MATT5

Temp Dep

Input Data Thermal Conductivity Kx

yes

Thermal Conductivity Ky

yes

Thermal Conductivity Kz

yes

Specific Heat

yes

Density

no

Heat generation

MAT5, MATT5

Heat Generation Multiplier

yes

Solid properties

MAT5, MATT5

Thermal Conductivity Kxx

yes

Thermal Conductivity Kxy

yes

Thermal Conductivity Kyy

yes

Specific Heat

yes

Density

no

Heat generation

MAT5, MATT5

Heat Generation Multiplier

yes

Solid properties

MAT5, MATT5

Thermal Conductivity Kxx

yes

Thermal Conductivity Kxy

yes

Thermal Conductivity Kxz

yes

Thermal Conductivity Kyy

yes

Thermal Conductivity Kyz

yes

Thermal Conductivity Kzz

yes

Specific Heat

yes

Density

no

Heat Generation Multiplier

yes

Heat generation

Main Index

MSC Nastran Bulk Data

MAT5, MATT5

Chapter 3: Building A Model Material Library

Constitutive Models The material properties for isotropic materials are divided into different categories called constitutive models, as follows: Solid Properties, 49 Fluid Properties, 49 Phase Changes, 49 Heat Generation1, 50

For a single material, you only need to define the constitutive models and properties necessary for the particular analysis. For example, in a steady-state analysis of a simple solid, you need only define the thermal conductivity. The phase changes and heat generation constitutive models need to be defined only when these effects are present in the analysis.

Solid Properties Thermal conductivities may be defined for isotropic, orthotropic, and anisotropic materials. When the 2D orthotropic material is used in an axisymmetric analysis, the conductivity Kr applies to the radial direction and the conductivity Kz is along the axis of symmetry. The conductivities may be defined as functions of temperature by creating temperature-dependent functions in the Fields application and then referencing these functions on the Materials form. Density and specific heat define the heat capacity of the body and are needed only in transient analysis.

Fluid Properties The dynamic viscosity is used in the calculation of the Reynolds (Re) and Prandtl (Pr) number in forced convection/advection applications and applies only to the Flow Tube element. The fluid specific heat, thermal conductivity, and density are also required for the formulation of the advective Streamwise Upwind Petrov Galerkin (SUPG) elements. This is the case even for steady-state analysis.

Recall

Cp μ DVρ Re = ------------ and Pr = ----------μ K

(3-1)

Phase Changes1 To model a phase change, you need to specify the latent heat and a finite temperature range over which the phase change is to occur. You also need to specify the lower boundary of the transition temperature as well as the reference enthalpy. The reference enthalpy is defined as the enthalpy corresponding to a zero temperature if the heat capacity Cp is a constant. If the heat capacity is temperature dependent, then the enthalpy must be defined at the lowest temperature value in the tabular field. 1If

Main Index

you define this constitutive model, you must also define a constitutive model for Solid Properties.

49

50

Patran Interface to MSC Nastran Thermal Finite Element Properties

For pure materials, the temperature range over which the phase change takes place can be quite small, whereas for solutions or alloys the range can be quite large. Numerically, the wider the range the better. It is not recommended to make this range less than a few degrees.

Heat Generation1 The heat generation multiplier allows the definition of a temperature-dependent rate of volumetric heat generation to be defined. Usually a temperature-dependent function will be defined in Fields and selected on the Materials form. The value defined by this field will multiply the rate of heat generation defined on the Applied Heat, Volumetric Generation LBC. If the heat generation is not temperature dependent, only the Volumetric Generation LBC needs to be defined.

Finite Element Properties The Element Properties form appears when you select Properties from the main form. There are several option menus available when creating element properties. The selections made on the Element Properties menu will determine which element property form appears, and ultimately, which MSC Nastran element will be created. The following pages give an introduction to the Element Properties form and details of all the element property definitions supported by the Patran MSC Nastran Thermal Application Preference.

Main Index

Chapter 3: Building A Model Finite Element Properties

Element Properties Form This form appears when you select Element Properties from the main menu. There are four option menus on this form. Each will determine which MSC Nastran element type will be created and which property forms will appear. The individual property forms are documented later in this section. For a full description of this form, see Element Properties Forms (p. 63) in the Patran Reference Manual.

Main Index

51

52

Patran Interface to MSC Nastran Thermal Finite Element Properties

Main Index

Chapter 3: Building A Model Finite Element Properties

Parameter Object

Description Use this option menu to define the element’s dimension. The options are: 0D (point elements) 1D (bar elements) 2D (tri and quad elements) 3D (tet, wedge, and hex elements)

Type

This option menu depends on the selection made in the Dimension option menu. Use this menu to define the general type of element, such as: Shell versus Axisym Solid

General Section

This option is only presented for 1D Beam and Rod elements.

The available element types are described briefly in the table below. Dimension 0D

Main Index

Type

Option

Elem Type

Input Data



Grounded Conductor

CELAS1

Thermal Conductance



Grounded Capacitor

CDAMP1

Thermal Capacitance

53

54

Patran Interface to MSC Nastran Thermal Finite Element Properties

Dimension

Type

1D

Option 

General Section

Elem Type CBAR

Material Name Area

CBEND 

Input Data

Curved w/ General Section

Material Name Center of Curvature Area



CBEND

Beam 

Curved w/ Pipe Section

Material Name Center of Curvature Mean Pipe Radius Pipe Thickness





Tapered Section General Section

CBEAM

Cross Sect. Areas CROD

Rod 

Material Name Area

CTUBE 

Material Name

Material Name Outer Diameter @ Node

Pipe Section

[Outer Diam. @ Node 2] Pipe Thickness



Conductor

CELAS1

Thermal Conductance



Capacitor

CDAMP1

Thermal Capacitance

CHBDYP

Material Name



Flow Tube

Hydraulic Diam. at Node 1 [Hydraulic Diam. at Node 2]

Main Index

Chapter 3: Building A Model Finite Element Properties

Dimension

Type

Option

2D 

Shell

Elem Type

Input Data

CQUAD4,8

Material Name

CTRIA3,6

[Material Orientation] Thickness

CTRIAX6 

[Material Orientation]

Axisym Solid Material Name

3D

CHEXA 

Solid

Material Name

CPENTA CTETRA

Conductors and Grounded Conductors These elements provide a simple conductance link between either two nodes in the model or a node and a zero temperature heat sink. The only property to be defined is the thermal conductance of the link. This value can either be real or a reference to an existing field definition.

Capacitors and Grounded Capacitors These elements provide a simple thermal capacitance link between either two nodes in the model or a node and a zero temperature heat sink. The only property to be defined is the thermal capacitance of the link. This value can either be real or a reference to an existing field definition.

Beam and Rod Elements with General Section These elements provide a simple conductance and capacitance link between two nodes in the model. Heat is conducted only along the length of the element; no heat is transferred across the cross section. The referenced material and cross-sectional area must be defined. Cross-sectional area can be defined either as a real value or as a reference to an existing field definition.

Main Index

55

56

Patran Interface to MSC Nastran Thermal Finite Element Properties

Curved General Section Beam

Parameter

Main Index

Description

Material Name

Defines the material for the element.

Ctr. of Curvature Vector

The center of curvature of the pipe bend can be defined as a vector from the first node to the center or by selecting an existing node located at the center.

Area

Defines the cross-sectional area of the element. This value can be either a real value or a reference to an existing field definition.

Chapter 3: Building A Model Finite Element Properties

Curved Pipe Section Beam

Parameter

Main Index

Description

Material Name

Defines the material for the element.

Ctr. of Curvature Vector

The center of curvature of the pipe bend can be defined as a vector from the first node to the center or by selecting an existing node located at the center.

Mean Pipe Radius

The distance from the centroid of the pipe cross section of the mid-wall of the pipe. This value can either be a real value or a reference to an existing field definition.

Pipe Thickness

Wall thickness of the pipe. This value can either be a real value or a reference to an existing field definition.

57

58

Patran Interface to MSC Nastran Thermal Finite Element Properties

Tapered Section Beam The Tapered Section beam allows different cross-sectional areas at each end of the beam. Both areas are entered in the Cross Sect. Areas databox separated by either spaces or a comma. If only one area is defined, the cross-sectional area is assumed to be constant at that value.

Pipe Section Rod

Parameter Material Name

Main Index

Description Defines the material to be used. When entering data here, a list of all materials currently in the database is displayed. You can either pick one from the list with the mouse, or type the name in.

Chapter 3: Building A Model Finite Element Properties

Parameter Outer Diameter @Node 1 Outer Diameter @Node 2 Pipe Thickness

Description Defines the tube OD at each end of the element. These values can either be real values or references to existing field definitions. The Outer Diameter at Node 1 property is required. The Outer Diameter at Node 2 Property is optional. Specifies the wall thickness of the pipe. This value can be either real or a reference to an existing field definition.

Flow Tube This element defines heat transfer based on 1D fluid flow. A material with the Fluid constitutive model defined must be selected. In addition, the diameters of tube at each end must be defined; if only the diameter at node 1 is defined, the tube diameter is assumed to be constant at that value. The value for the diameter may either be real or a reference to an existing field definition. The Flow Tube elements can be referenced in the Loads/BCs application to support several types of forced convection and advection conditions.

Main Index

59

60

Patran Interface to MSC Nastran Thermal Finite Element Properties

2D Shell Elements These elements provide for conduction and heat capacitance within a planar area. Heat is not transferred through the thickness of the shell.

Parameter

Main Index

Description

Material Name

Defines the material to be used. When entering data here, a list of all materials currently in the database is displayed. You can either pick one from the list with the mouse, or type the name in.

Material Orientation

Defines the basic orientation for any non-isotropic material within the element. There are three ways to assign this definition: (1) reference a coordinate system, which is then projected onto the element, (2) define a vector that will be projected onto the element, or (3) define a constant angle offset from the default element coordinate system. This scalar value can either be a constant value in degrees, a vector, or a reference to an existing coordinate system. This property is optional.

Thickness

Defines the thickness, which will be uniform over each element. This value can either be real or a reference to an existing field definition.

Chapter 3: Building A Model Loads and Boundary Conditions

2D Axisymmetric Solid Elements These elements are used to model heat conduction in a body that is symmetric about a particular coordinate axis. When defining the model with Patran, this axis must be the global z-axis and the radial axis must be the global x-axis (i.e., the elements must lie in the x-z plane). The only element property required is the material. An optional material orientation allows you to define the orientation for any non-isotropic material within the element. You can specify temperature boundary conditions, initial temperatures, and nodal and volumetric heat loads on the element’s boundaries or interior. You can specify exchange type boundary conditions (convection and radiation) on the boundaries of the geometry. With Version 68 of MSC Nastran, if convection or radiation boundary conditions are applied to 6-node triangular axisymmetric elements, the heat flux results associated with these elements cannot be post processed in Patran. To post process boundary heat fluxes, the 3-node triangular axisymmetric elements must be used instead.

3D Solid Elements These elements provide for conduction and heat capacitance within a volume. A material property must be selected to define the thermal conductivity, density, and specific heat.

Loads and Boundary Conditions The Loads and Boundary Conditions form will appear when you select Loads/BCs from the main form. When you create a loads and/or boundary condition, there are several option menus. The selections made on the Loads and Boundary Conditions menu will determine which loads and/or boundary conditions form appears, and ultimately, which MSC Nastran loads and/or boundary conditions will be created. The following pages give an introduction to the Loads and Boundary Conditions form and details of all the loads and boundary conditions supported by the Patran MSC Nastran Thermal Application Preference.

Loads and Boundary Conditions Form This form appears when you select Loads/BCs from the main menu. The Loads/Boundary Conditions form provides options to create the various MSC Nastran loads and/or boundary conditions. For a definition of full functionality, see Loads and Boundary Conditions Form (p. 18) in the Patran Reference Manual

Main Index

61

62

Patran Interface to MSC Nastran Thermal Loads and Boundary Conditions

Main Index

Chapter 3: Building A Model Loads and Boundary Conditions

Parameter

Description

Object

Indicates the category of heat loads or boundary condition. The choices are Temp (Thermal) for prescribing temperatures, Initial Temperature, Boundary Temperature, Applied Heat, Convection, Radiation, and Contact.

Type

The Type options are Nodal, Element Uniform, and Element Variable. Nodal is applied explicitly to nodes. Element Uniform defines a constant value to be applied over an entire element, element face, or element edge. Element Variable defines a value that varies across an entire element, element face, or element edge.

Option

Indicates the specific type for each general category of loads/boundary condition. The choices for each Object are shown on page 63.

Existing Sets

Loads or boundary conditions defined here are associated with the Current Load Case. By default, this is a static (steady-state) load case called Default. To create heat loads or boundary conditions for a transient analysis, you must create a Time-Dependent load case in the Load Cases application.

Input Data

Generates either a Static or Transient Input Data form, depending on the current Load Case Type selected.

Select Application Region

The Application Region is the piece of geometry or set of nodes or elements to which the loads or boundary condition is applied. Most Loads/BCs have a single region. However, options are provided for advanced users to define complex convection or radiation exchange between two application regions.

The following table outlines the options for creating MSC Nastran thermal loads and boundary conditions:

Object

Option

Type

Target Element Type

Region 2



Temp (Thermal)

Nodal

--

--



Initial Temperature

Nodal

--

--

Nodal

--

--

Element Uniform

1D, 2D, 3D

--

Nodal

--

--

Element Uniform

1D, 2D, 3D

--



Normal Fluxes

Element Variable 

Main Index

Applied Heat



Directional Fluxes



Nodal Source

Nodal

--

--



Volumetric Generation

Element Uniform

1D, 2D, 3D

--



Total Heat

Element Uniform

1D, 2D, 3D

63

64

Patran Interface to MSC Nastran Thermal Loads and Boundary Conditions

Object







Convection

Radiation

Contact

Option 

To Ambient



Flow Tube To Ambient

Type

Target Element Type

Region 2

Nodal

--

--

Element Uniform

1D, 2D, 3D

--

Element Uniform

1D

--

Nodal

--

Nodal

Element Uniform

1D, 2D, 3D

Nodal, 1D, 2D, 3D

Element Uniform

1D

Nodal, 1D, 2D, 3D



Coupled



Coupled Flow Tube



Coupled Advection

Element Uniform

1D, 2D, 3D

1D



Duct Flow

Element Uniform

1D

2D, 3D



Ambient Space

Nodal

--

--

Element Uniform

1D, 2D, 3D

--

Nodal

--

Nodal

Element Uniform

1D, 2D, 3D

Nodal 1D, 2D, 3D

Nodal

--

--

Element Uniform

1D, 2D, 3D

--

Element Uniform

1D, 2D, 3D



Ambient Nodes



Enclosures



Deformable



Rigid Body



Body Pair

Input Data Forms--Basic and Advanced Options Many of the input data forms have a Basic format and an Advanced format. The default is the Basic format, but you can change the format to Advanced using the option menu at the top of the form. Many of the advanced forms contain a databox called Control Node ID. If an existing node is selected in this databox, the temperature at this node during the analysis is used as an implicit load multiplier, depending on the exact application. Another advanced option is the Film Node ID that appears on forms for defining convection boundary conditions. This option allows an existing node to be selected. The temperature of this node during the analysis is used to define the temperature of the fluid used in determining the temperature-dependent fluid material properties involved in the calculation of the convection heat transfer coefficient.

Main Index

Chapter 3: Building A Model Loads and Boundary Conditions

Two Application Regions Two application regions provide advanced options for convection and radiation boundary conditions with complex exchange mechanisms. Application Region 1 defines a convecting or radiating surface, while Application Region 2 specifies a set of nodes to which the heat is transferred.

Main Index

65

66

Patran Interface to MSC Nastran Thermal Loads and Boundary Conditions

Parameter

Main Index

Description

Mode

Defines the coupling methods of two application regions. The Patran MSC Nastran Thermal Application Preference ignores this option and always applies a closest approach algorithm to associate the companion region with Application Region 1.

Active Region

Activates the selection of Application Region 1 or 2

Select Entities

Selects geometry or finite element entities by graphical picks or text input to the databox.

Chapter 3: Building A Model Loads and Boundary Conditions

Parameter

Description

Add

Adds geometry or finite element entities to the activated Application Region.

Remove

Removes geometry or finite element entities from the activated Application Region. Note: When applying any of the convection or radiation forms involving two application regions, both regions must use the same geometry filter.

Surface Area The total amount of heat radiated or convected from a surface or input from a heat source depends on the area of the surface. For nodal loads and boundary conditions, the nodal area must be defined explicitly. For faces of 2D or 3D elements, the area is calculated from the relative locations of the nodal points. For the edge of a shell element, the area is calculated from the nodal points location and the shell thickness. For general or tapered beam elements, the rod element, or the curved beam with general section, the area is calculated as: ( 4. • π • cross_sectional_area ) • beam_length

For the rod or curved beam with pipe section, the area is calculated as: 2 • π • radius • beam_length

For directional flux or radiation enclosure on 1D elements, the Patran MSC Nastran forward translator will automatically calculate the projected area based on the normal vector specified for the given elements.

Spatial Dependence Many of the quantities defined on the Loads/BCs forms are allowed to vary as a function of the model’s spatial coordinates. This variation is described by first defining a spatial field using the Fields application and then selecting this field from the Spatial Fields listbox on the Loads/BCs Input Data form. Creation of spatial fields is described in more detail in Fields Forms (p. 191) in the Patran Reference Manual.

Temperature Dependence Many of the quantities defined on the Loads/BCs forms are also allowed to vary as a function of temperature. An example is Convection Coefficient. The convection coefficient can take on different values depending on the surface or fluid temperatures at each point in the model. All quantities that are allowed to vary as a function of temperature have a second databox on the Loads/BCs Input Data form with the *Temperature Function label above it. This indicates that the temperature function multiplies the value in the databox to its immediate left (this value may be a constant or may come from a spatial field). Functions of temperature are described by defining a temperature-dependent field in the Fields application. To create this Field, you must set the Object to Material Property. You may then select the created field from the Temperature Dependent Fields listbox on the Loads/BCs Input Data form. For convenience, if you have specified a temperature-dependent function but do not specify any value in the far left column, Patran will assign a default value of 1.0 to that databox.

Main Index

67

68

Patran Interface to MSC Nastran Thermal Loads and Boundary Conditions

Time Dependence When the Current Load Case is Time Dependent (set from the Load Cases application), a time-dependent field listbox appears on the far right column of the Loads/BCs Input Data form. This column contains databoxes that allow the time dependence of the quantities in the far left column of the Input Data form to be defined. Just as for spatial and temperature dependencies, you must first create a time dependence in the Fields application. To create the field in the Fields application, you must set the Object to Non Spatial and the Method to Tabular Input. You must also define a set of time-load multiplier pairs. This field can then be selected from the Time Dependent Fields listbox on the Loads/BCs Input Data form. For convenience, if you have specified a time-dependent function but do not specify any value in the far left column, Patran will assign a default value of 1.0 to that databox.

Main Index

Chapter 3: Building A Model Loads and Boundary Conditions

Temp(Thermal) Forms associated with the Temp(Thermal) Object allow you to define nodal temperatures that remain constrained during the analysis. The Temp(Thermal) Input Data forms for steady-state (Static) and transient (Time Dependent) load cases are shown below. In a steady-state analysis, you may input a constant value or select a previously created Spatial Field that defines the temperature as a function of location in the model.

In a transient analysis, in addition to the constant value or Spatial Field, you may also select a previously created Time Dependent Field that describes how the temperature changes as an explicit function of time.

Main Index

69

70

Patran Interface to MSC Nastran Thermal Loads and Boundary Conditions

The input option is described in the table below. Input Data

Dependence

Boundary Temperature

spatial, time

Description Defines temperature boundary conditions.

Initial Temperature Initial temperature is required in a time-dependent analysis. In a nonlinear steady-state analysis, initial temperatures are input as an initial guess to improve the convergence rate and often to provide initialization for the nonlinear iterative solution scheme. As a user convenience, if most of the initial nodal temperatures are to be the same, you can define this temperature using the Default Init Temperature databox in the Solution Parameters form invoked from the Analysis application. Any initial temperatures defined using this Initial Temperature option in Loads/BCs will take precedence over the default value defined in the Analysis application. The Input Data form for Initial Temperature is very similar to the form for steady-state temperature shown above. The input option is described in the table below. Input Data Initial Temperature

Main Index

Dependence spatial

Description Defines initial condition temperatures for transient analysis. May also be used to define an initial guess in a nonlinear steady-state analysis.

Chapter 3: Building A Model Loads and Boundary Conditions

Applied Heat--Normal Fluxes This option applies a heat flux either to nodes or elements on the surface of a body. Input Data

Parameter

Main Index

Description

Form Type

If the Form Type is toggled from Basic to Advanced, the Control Node ID databox appears

Heat Flux

For 2D elements, the heat flux can be applied to the top, bottom, or edge of the surface.

71

72

Patran Interface to MSC Nastran Thermal Loads and Boundary Conditions

The following table describes the options for defining a heat flux. Input Data

Dependence

Description

Heat Flux

spatial, time

Defines a heat flux.

[Top Surf, Bottom Surf, Edge] Heat Flux

spatial, time

When the Target Element Type on the main form is set to 2D, this databox appears to define a heat flux applied on the top, bottom, or edge of a boundary surface.

Nodal Area

--

Appears only when the LBC type is Nodal. Defines the area of a boundary surface associated with the node.

Control Node ID

--

An advanced option that defines a control node. See Input Data Forms--Basic and Advanced Options, 64.

Applied Heat--Directional Fluxes This option applies a thermal vector flux from a distant source onto the surface of a body.

Main Index

Chapter 3: Building A Model Loads and Boundary Conditions

Steady-State Analysis

Parameter

Description

Nodal Area

When the load type is Nodal or the target element type is 1D, you must specify a vector defining the “surface normal.”

Spatial Fields

When the load type is Nodal, you must specify the area associated with the node.

Transient Analysis For a time-dependent load case, the Input Data form with the Form Type changed from Basic to Advanced and the Thermal Vec Type changed to Transient is shown below.

Main Index

73

74

Patran Interface to MSC Nastran Thermal Loads and Boundary Conditions

Incident Thermal Vector The incident thermal vector defines the direction from the surface to the heat source. In steady-state analysis, you may use any of the standard Patran vector tools to define this vector. In a transient analysis, two options are available and controlled with the Thermal Vec Type menu: 1. If only the magnitude of the heat flux changes as a function of time in the analysis, you may choose Thermal Vec Type Constant and select a previously defined field in the * Time Function databox to describe this change. 2. If the direction of the vector also changes as a function of time, the Thermal Vec Type menu must be set to Transient. The form changes to display three databoxes titled DirCos ei(t) of Thermal Vec. Separate time-dependent fields can be selected for these three boxes to define the change of direction as a function of time. The following table describes the options for the forms shown on page 73 through page 74. Input Data

Main Index

Dependence

Description

Absorptivity

spatial, temp

Defines the absorptivity of the surface.

[Top Surf, Bottom Surf, Edge] Absorptivity

spatial, temp

When the target element type is 2D, a toggle and databox appear to define the absorptivity of the top, bottom, or edge of a boundary surface.

Heat Flux

spatial, time

Defines the heat flux quantity.

Chapter 3: Building A Model Loads and Boundary Conditions

Input Data

Dependence

Description

[Top Surf, Bottom Surf, Edge] Heat Flux

spatial, time

When the target element type is 2D, a toggle and databox appear to define a heat flux applied on the top, bottom, or edge of a boundary surface.

Incident Thermal Vector

--

Defines the fixed direction incident thermal vector.

DirCos e1(t) of Thermal Vec

time

Defines the time function of the direction cosine e1 of the incident thermal vector.

DirCos e2(t) of Thermal Vec

time

Defines the time function of the direction cosine e2 of the incident thermal vector.

DirCos e3(t) of Thermal Vec

time

Defines the time function of the direction cosine e3 of the incident thermal vector.

Normal Vector

spatial

When the load type is Nodal or the target element type is 1D, a vector defining the “surface normal” must be entered.

Nodal Area

--

When the load type is Nodal, the area associated with the node must be entered.

Control Node ID

--

An advanced option that defines a control node. See Input Data Forms--Basic and Advanced Options, 64.

Applied Heat--Nodal Source This option applies a heat flow directly to one or more nodes in the model. Input Data Nodal Source

Dependence spatial, time

Description Defines the heat applied to the nodes.

Applied Heat--Volumetric Generation This option defines a rate of heat generation within the volume of a conduction solid. This heat generation rate can be made a function of temperature by assigning a temperature field to the Heat Generation Multiplier option of the material associated with this solid. Input Data

Main Index

Dependence

Description

Volumetric Heat Generation spatial, time

Defines the volumetric heat generation in conduction elements.

Control Node ID

An advanced option that defines a control node. See Input Data Forms--Basic and Advanced Options, 64.

--

75

76

Patran Interface to MSC Nastran Thermal Loads and Boundary Conditions

Applied Heat--Total Heat This option defines a rate of heat generation within the volume of a conduction solid. This heat generation rate can be made a function of temperature by assigning a temperature field to the Heat Generation Multiplier option of the material associated with this solid. Input Data

Main Index

Dependence

Description

Total Heat

spatial, time

Defines the total heat (power) applied to a surface or element face. The total heat value given is divided by the total area of the application region (for surface entities). If the application region is geometry, then the value displayed graphically on the geometry is the actual given value. If the application region is FEM (or Geometry, but displayed on the associated FEM) then the value displayed is the given value divided by the total area of the application region. This is the value that will be written to the MSC Nastran QBDY3 entry.

Control Node ID

--

An advanced option that defines a control node. See Input Data Forms--Basic and Advanced Options, 64.

Chapter 3: Building A Model Loads and Boundary Conditions

Convection--To Ambient This option allows for the definition of the most basic form of convection boundary condition. Heat is exchanged between the surface of the body and a surrounding media, the temperature of which is known. The form for a steady-state load case and 2D element type are shown below.

The options for this convection boundary condition are shown in the table below. Input Data

Main Index

Dependence

Description

Convection Coefficient

spatial, temp, time

Defines free convection heat transfer coefficient.

[Top Surf, Bottom Surf, Edge] Convection Coeff

spatial, temp, time

When the target element type is 2D, a toggle and databox appear to define the free convection heat transfer coefficient of the top, bottom, or edge of a boundary surface.

Ambient Temperature

time

Defines ambient temperature.

Nodal Area

--

When the LBC type is Nodal, this databox appears to define the area of the boundary surface.

77

78

Patran Interface to MSC Nastran Thermal Loads and Boundary Conditions

Input Data Formula Type Option

Dependence --

Description An advanced option for defining a customized form of the free convection formula: q = h (Ts-Ta)(expf+1) or q = h (Tsexpf - Taexpf ) By default, the first form is chosen with EXPF equal 0.0.

Convection Exponent

--

An advanced option for defining EXPF in the above equation.

Reference Temperature Option

--

An advanced option for defining the temperature used in calculating the convection coefficient. The options are: average of surface and ambient temperatures, surface temperature, ambient temperature, or temperature at a user-defined node. By default, this reference temperature is taken as the average of surface and ambient temperatures.

Film Node ID

--

An advanced option for selecting an existing node for fluid film temperature.

With MSC.Nastran Version 68, the Patran MSC Nastran Forward Translator will average the values for Surface Temp (Ts) and Ambient Temp (Ta) to acquire the Average Temp (Ts+Ta)/2. Average Temp will be used as the temperature at which the temperature dependent heat transfer coefficient will be determined.

Convection--Flow Tube To Ambient Two basic heat transport mechanisms take place when the Flow Tube element is used. The first involves the transport of heat in the streamwise direction from the upstream fluid elements to the downstream fluid elements. We refer to this as heat transport due to advection. The second heat transfer mechanism involves heat transport into or out of the working fluid along the fluid tube boundary. We refer to this as heat transfer due to forced convection. The transport of heat energy by advection is a function of the mass flow rate (mdot) and the specific heat of the fluid. In the typical case we can ignore the small amount of heat transfer resulting from conduction in the fluid1; energy is then transported at the rate: mdot * Cp * T. The heat transfer at the stream tube boundary, then, must be equal to (mdot * Cp * T)in - (mdot * Cp * T)out, where in and out refer to the inlet and exit states of the fluid stream. Typically, the inlet temperature is specified and the exit temperature is determined as part of the solution. The forced convection part of the problem allows the fluid stream tube to communicate with the surrounding environment. You can determine the heat transfer coefficient for a particular problem externally, or use the generalized correlations available through the preference and MSC Nastran heat transfer solver. The particular application has a lot to do with the viability of either approach. 1MSC

Main Index

Nastran does not ignore the component of heat transfer in the fluid due to conduction.

Chapter 3: Building A Model Loads and Boundary Conditions

A practical example of the use of Flow Tube to Ambient is the situation of analyzing a flow tube in a free stream of large mass flow and essentially constant temperature. A flow tube in an automobile radiator is a good example where the flow tube models the flow stream in the tubing (engine coolant) and the ambient environment is that of the air rushing across the tubes at the local air temperature. Physical Model

Flow out

Flow in

Ambient Flow Stream At Temperature T∞ = Constant

Finite Element Representation Forced convection resistance T∞

.

1 Res = ------hA

m cp

Tin

Main Index

Tout

79

80

Patran Interface to MSC Nastran Thermal Loads and Boundary Conditions

The Input Data form for a transient load case is shown below.

The following table describes the options for defining this convection boundary condition. Input Data

Dependence

Description

Mass Flow Rate

time

Defines mass flow rate within the flow tube element.

Ambient Temperature

time

Defines ambient temperature.

Heat Transfer Coefficient

--

Defines the constant coefficient used for forced convection. A default value 1.e-20 will be defined if this data is not specified.

Formula Type Option

--

An advanced option to define forced convection formula type: h=coef*Reexpr*Prexpp or h=coef*Reexpr*Prexpp*k/d By default, the first form is chosen with EXPR and EXPP equal to 0.0.

Main Index

Chapter 3: Building A Model Loads and Boundary Conditions

Input Data

Dependence

Description

Reynolds Exponent

--

An advanced option to define the Reynolds number convection exponent EXPR.

Prandtl Exponent, Heat In

--

An advanced option to define the Prandtl number convection exponent EXPPI for heat transfer into the working fluid.

Prandtl Exponent, Heat Out

--

An advanced option to define the Prandtl number convection exponent EXPPO for heat transfer out of the working fluid.

Reference Temperature Option

--

An advanced option for defining the temperature used in calculating material properties for the fluid. The options are: average of surface and ambient temperatures, surface temperature, ambient temperature, or temperature at a user-defined node. By default, this reference temperature is taken as the average of surface and ambient temperatures.

Film Node ID

--

An advanced option for selecting an existing node for fluid film temperature.

With MSC.Nastran Version 68, the Patran MSC Nastran Forward Translator will average the values for Surface Temp (Ts) and Ambient Temp (Ta) to acquire the Average Temp (Ts+Ta)/2. Average Temp will be used as the temperature at which the temperature dependent heat transfer coefficient will be determined.

Convection--Coupled This advanced option for applying a convection boundary condition allows for the explicit definition of the convecting surface (Application Region 1) and a set of nodes (Application Region 2) between which heat is exchanged by convection. Mathematically, the exchange mechanism is similar to that for Convection to Ambient, except here Application Region 2 may be something other than basic ambient fluid points and their temperatures need not be specified in the description of the problem. The temperatures in Application Region 2 may be part of the solution. In addition, there does not need to be a one-to-one correspondence

Main Index

81

82

Patran Interface to MSC Nastran Thermal Loads and Boundary Conditions

between nodal points in Region 1 and those in Region 2. The Input Data form for a steady-state load case is shown below.

Application Region 2

Application Region 1

The input options for coupled convection are shown in the table below. Input Data

Main Index

Dependence

Description

Convection Coefficient

spatial, temp, time

Defines free convection heat transfer coefficient.

[Top Surf, Bottom Surf, Edge] Convection Coeff

spatial, temp, time

When the target element type is 2D, a toggle and databox appear to define the free convection heat transfer coefficient of the top, bottom, or edge of a boundary surface.

Nodal Area

--

When the LBC type is Nodal, this databox appears to define the area of the boundary surface.

Chapter 3: Building A Model Loads and Boundary Conditions

Input Data Formula Type Option

Dependence --

Description An advanced option for defining a customized form of the free convection formula: q = h (Ts-Ta)(expf+1) or q = h (Tsexpf - Taexpf ) By default, the first form is chosen with EXPF equal 0.0.

Convection Exponent

--

An advanced option for defining EXPF in the above equation.

Reference Temperature Option

--

An advanced option for defining the temperature used in calculating the convection coefficient. The options are: average of surface and ambient temperatures, surface temperature, ambient temperature, or temperature at a user-defined node. By default, this reference temperature is taken as the average of surface and ambient temperatures.

Film Node ID

--

An advanced option for selecting an existing node for fluid film temperature.

With MSC.Nastran Version 68, the Patran MSC Nastran Forward Translator will average the values for Surface Temp (Ts) and Ambient Temp (Ta) to acquire the Average Temp (Ts+Ta)/2. Average Temp will be used as the temperature at which the temperature dependent heat transfer coefficient will be determined.

Convection--Coupled Flow Tube This is an advanced extension of the Convection, Flow Tube to Ambient boundary condition. In this application, the advection flow tube is attached to nodal points associated with a structure as opposed to simply an ambient environment. The flow tube in this application transports energy downstream in the mdot * Cp * T sense. Flow tube relations related to forced convection heat transfer at the tube boundaries are associated with this model. In this case, the convection area is the area associated with the flow tube perimeter, and it is the user’s responsibility to coordinate this area with that of the attached structure. It is important to realize that if the flow tube relationships are used (as opposed to a user-supplied h), the tube input diameters

Main Index

83

84

Patran Interface to MSC Nastran Thermal Loads and Boundary Conditions

are used in the calculation of the Reynolds number and subsequently in calculating the heat transfer coefficient.

Application Region 1 (Flow Tube) mdot

1 Res = ------hA Convection Resistance

Application Region 2 (Structure)

When this capability is applied, there must be general correspondence (one flow tube element for every structural element grid point pair) between the flow tube node points in Application Region 1 and the

Main Index

Chapter 3: Building A Model Loads and Boundary Conditions

structural node points in Application Region 2. The Input Data form for a steady-state load case is shown below.

The input options for coupled flow tube convection are described in the table below. Input Data

Dependence

Description

Mass Flow Rate

time

Defines mass flow rate in the Flow Tube element.

Heat Transfer Coefficient

--

Defines the constant coefficient used for forced convection. A default value 1.e-20 will be defined if this data is not specified.

Formula Type Option

--

An advanced option to define forced convection formula type: h=coef*Reexpr*Prexpp or h=coef*Reexpr*Prexpp*k/d By default, the first form is chosen with EXPR and EXPP equal to 0.0.

Reynolds Exponent

Main Index

--

An advanced option for defining the Reynolds number convection exponent EXPR in the above equation.

85

86

Patran Interface to MSC Nastran Thermal Loads and Boundary Conditions

Input Data

Dependence

Description

Prandtl Exponent, Heat In

--

An advanced option for defining the Prandtl number convection exponent EXPPI for heat transfer into the working fluid.

Prandtl Exponent, Heat Out

--

An advanced option for defining the Prandtl number convection exponent EXPPO for heat transfer out of the working fluid.

Reference Temperature Option

--

An advanced option for defining the temperature used in calculating material properties for the fluid. The options are: average of surface and ambient temperatures, surface temperature, ambient temperature, or temperature at a user-defined node. By default, this reference temperature is taken as the average of surface and ambient temperatures.

Film Node ID

--

An advanced option for selecting an existing node for fluid film temperature.

With MSC.Nastran Version 68, the Patran MSC Nastran Forward Translator will average the values for Surface Temp (Ts) and Ambient Temp (Ta) to acquire the Average Temp (Ts+Ta)/2. Average Temp will be used as the temperature at which the temperature dependent heat transfer coefficient will be determined.

Convection--Coupled Advection This advanced option enables the connection between an advection stream and a structural surface. For this capability, the forced convection tube relationships are essentially turned off by setting the constant coefficient for forced convection to 1.E-20. The convection connection between the flow stream and the surface is determined from basic convection; Q = h * A * (T1 - T2). Here the internally calculated area A is the area associated with the structural surface elements. The user must specify the value of the heat transfer coefficient, h. In steady-state analysis, the flow tube diameters are of little consequence for this capability since no Reynolds Numbers or heat transfer coefficients are determined internally. In transient analysis, the fluid speed needs to be produced by the correct choice of fluid properties and tube diameter. There need not be any particular correspondence between the nodes on the flow tube and those on the surface elements; Patran

Main Index

Chapter 3: Building A Model Loads and Boundary Conditions

uses a closest approach algorithm to associate the surface elements with the stream tube elements. The Input Data form for a steady-state load case is shown below.

Main Index

87

88

Patran Interface to MSC Nastran Thermal Loads and Boundary Conditions

T = 0.0

Res → ∞

Flow Tube

1 Res = ------hA

In MSC Nastran terms, the flow tube ambient points are brought together and set to 0.0 degrees temperature. The forced convection resistance is set to a large number (negligible heat transfer coefficient). The connection between the fluid and structure is affected through basic convection with a user-specified heat transfer coefficient. The input options are described in the table below. Input Data

Main Index

Dependence

Description

Convection Coefficient

spatial, temp, time

Defines free convection heat transfer coefficient.

[Top Surf, Bottom Surf, Edge] Convection Coeff

spatial, temp, time

When the target element type is 2D, a toggle and databox appear to define the free convection heat transfer coefficient of the top, bottom, or edge of a boundary surface.

Mass Flow Rate

time

Defines the mass flow rate of the flow tube elements.

Nodal Area

--

When the LBC type is Nodal, this databox appears to define the area of the boundary surface.

Chapter 3: Building A Model Loads and Boundary Conditions

Input Data Formula Type Option

Dependence --

Description An advanced option for defining a customized form of the free convection formula: q = h (Ts-Ta)(expf+1) or q = h (Tsexpf - Taexpf ) By default, the first form is chosen with EXPF equal 0.0.

Convection Exponent

--

An advanced option for defining EXPF in the above equation.

Reference Temperature Option

--

An advanced option for defining the temperature used in calculating the convection coefficient. The options are: average of surface and ambient temperatures, surface temperature, ambient temperature, or temperature at a user-defined node. By default, this reference temperature is taken as the average of surface and ambient temperatures.

Film Node ID

--

An advanced option for selecting an existing node for fluid film temperature.

With MSC.Nastran Version 68, the Patran MSC Nastran Forward Translator will average the values for Surface Temp (Ts) and Ambient Temp (Ta) to acquire the Average Temp (Ts+Ta)/2. Average Temp will be used as the temperature at which the temperature dependent heat transfer coefficient will be determined.

Convection--Duct Flow This feature enables the user to associate a 1D fluid stream with a surface or duct composed of 2D or 3D (shell or solid) elements. When specifying the duct flow attributes, the target element type is 1D and the region-2 specification will be 2D or 3D. It would be good modeling practice to provide flow stream element discretization level of approximately the same level as the adjoining structure with respect to the streamwise direction. Fluid connections can only be made between the flow tube and 3 noded triangular elemental surfaces or 4 noded quadrilateral elemental surfaces. The structural surface may represent a physically more complex geometry composed of surface fins. The increased area associated with extended surfaces can be accounted for in duct flow by using the Extended Surface Multiplier on the Input Data menu. The actual convection surface area will equal the area calculated by the code from the elemental areas times this surface multiplier. On this same menu, mass flow rate refers to the duct mass flow rate (total flow). The proper treatment of the heat transfer coefficient relationship depends on the input for the flow tube diameters, defined in this application as the hydraulic diameters (DH). The flow tube hydraulic diameter is the dimension used in internally calculating the Reynolds Number. It will also automatically be used as the diameter in the Input Data, Formula Type Option equation for the heat transfer coefficient. With this formulation, the advection flow heat transfer coefficient is based on the gross dimensions of the structure and is input to the code through the input of hydraulic diameter. It is the user’s responsibility to determine an

Main Index

89

90

Patran Interface to MSC Nastran Thermal Loads and Boundary Conditions

appropriate DH. The mass flow rate and fluid material properties represent the actual total/real flow characteristics for the duct. The actual elemental surface area flow attachment is accounted for internally through the triangle and quadrilateral surface element area calculations and may be enhanced by the extended surface multiplier to represent a finned surface.

Input Data

Dependence

Description

Mass Flow Rate

time

Defines mass flow rate in the Flow Tube element.

Heat Transfer Coefficient

--

Defines the constant coefficient used for forced convection. A default value 1.e-20 will be defined if this data is not specified.

Extended Surface Multiplier

--

Defines extended area factor for surface fins.

Formula Type Option

--

An advanced option to define forced convection formula type: h=coef*Reexpr*Prexpp or h=coef*Reexpr*Prexpp*k/d By default, the first form is chosen with EXPR and EXPP equal to 0.0.

Main Index

Chapter 3: Building A Model Loads and Boundary Conditions

Input Data

Main Index

Dependence

Description

Reynolds Exponent

--

An advanced option for defining the Reynolds number convection exponent EXPR in the above equation.

Prandtl Exponent, Heat In

--

An advanced option for defining the Prandtl number convection exponent EXPPI for heat transfer into the working fluid.

Prandtl Exponent, Heat Out

--

An advanced option for defining the Prandtl number convection exponent EXPPO for heat transfer out of the working fluid.

Reference Temperature Option --

An advanced option for defining the temperature used in calculating material properties for the fluid. The options are: average of surface and ambient temperatures, surface temperature, ambient temperature, or temperature at a user-defined node. By default, this reference temperature is taken as the average of surface and ambient temperatures.

Film Node ID

An advanced option for selecting an existing node for fluid film temperature.

--

91

92

Patran Interface to MSC Nastran Thermal Loads and Boundary Conditions

Radiation--Ambient Space This option defines a boundary condition for a surface exchanging radiant energy with an ambient temperature in space. The Input Data form for 3D element types is shown below.

Input Data

Main Index

Dependence

Description

Emissivity

spatial, temp

Defines surface emissivity.

[Top Surf, Bottom Surf, Edge] Emissivity

spatial, temp

When the target element type is 2D, a toggle and databox appear to define the emissivity of the top, bottom, or edge of a boundary surface.

Absorptivity

spatial, temp

Defines surface absorptivity.

[Top Surf, Bottom Surf, Edge] Absorptivity

spatial, temp

When the target element type is 2D, a toggle and databox appear to define the absorptivity of the top, bottom, or edge of a boundary surface.

Ambient Temperature

time

Defines ambient temperature.

View Factor

spatial, time

Defines radiation view factor between the surface and the ambient space. The default value is 1.0.

Nodal Area

--

When the LBC type is Nodal, this databox appears to define the area of the boundary surface.

Chapter 3: Building A Model Loads and Boundary Conditions

Radiation--Ambient Nodes This is an advanced option for applying a radiation boundary condition to a surface. You select both the surface (Application Region 1) and a set of nodes that define the temperature to which the surface is exchanging heat by radiation (Application Region 2). Input Data

Main Index

Dependence

Description

Emissivity

spatial, temp

Defines surface emissivity.

[Top Surf, Bottom Surf, Edge] Emissivity

spatial, temp

When the target element type is 2D, a toggle and databox appear to define the emissivity of the top, bottom, or edge of a boundary surface.

Absorptivity

spatial, temp

Defines surface absorptivity.

[Top Surf, Bottom Surf, Edge] Absorptivity

spatial, temp

When the target element type is 2D, a toggle and databox appear to define the absorptivity of the top, bottom, or edge of a boundary surface.

View Factor

spatial, time

Defines radiation view factor between the surface and the ambient nodes. The default value is 1.0.

Nodal Area

--

When the LBC type is Nodal, this databox appears to define the area of the boundary surface.

93

94

Patran Interface to MSC Nastran Thermal Loads and Boundary Conditions

Radiation--Enclosures This option defines a radiation boundary among a set of surfaces making up a cavity or enclosure. Each surface is defined independently using the form below. The surfaces are grouped to form an enclosure by specifying the same Enclosure ID (integer) on all surfaces making up the enclosure.

Input Data

Main Index

Dependence

Description

Enclosure ID

--

Defines the ID number of the radiation enclosure.

Emissivity

spatial, temp

Defines surface emissivity.

[Top Surf, Bottom Surf, Edge] Emissivity

spatial, temp

When the target element type is 2D, a toggle and databox appear to define the emissivity of the top, bottom, or edge of a boundary surface.

Surface Can Shade

--

Specifies if the face can shade other faces in the enclosure (default=yes).

Surface Can Be Shaded

--

Specifies if the face can be shaded by other faces in the enclosure (default=yes).

Normal Vector

spatial

When the load type is Nodal or the target element type is 1D, a vector defining the “surface normal” must be entered.

Nodal Area

--

When the LBC type is Nodal, this databox appears to define the area of the boundary surface.

Chapter 3: Building A Model Loads and Boundary Conditions

Input Data

Dependence

Description

Third Body Shading

--

Controls third body shading calculation (default=yes). When set at “no,” third body shadowing calculations will be ignored.

Complete Enclosure

--

In an enclosure that is not fully closed, energy may be radiated to entities outside the enclosure. Toggling this option from “no” (default) to “yes” specifies that all energy not exchanged among the surfaces of the enclosure will be radiated to a user-defined ambient temperature. When creating an enclosure it is sometimes not feasible to model everything that will be generating or receiving heat from a model. The user models everything that is of interest, and then simply wants to close the remainder of the his model with a single ambient element that will allow his view factors to sum to 1.0. This is done with a RADCAV card and can be accomplished by selecting the complete enclosure toggle. The ambient temperature of the open space is then entered, and now the analysis is able to complete with a total view factor of 1.0.

Ambient Temperature

--

This databox appears when the Complete Enclosure option is toggled to “yes” and is used to define the external temperature to which energy is exchanged with the enclosure.

Cavity 1

Cavity 2

Figure 3-1 Multiple Cavity Example

Main Index

95

96

Patran Interface to MSC Nastran Thermal Loads and Boundary Conditions

Can Be Shaded, but cannot shade

Can Shade, but cannot be shaded (Third Body Shadowing) Figure 3-2 Single Cavity Example

Main Index

Can Be Shaded, but cannot shade

Chapter 3: Building A Model Loads and Boundary Conditions

Body Pair This option defines the parameters for a new LBC called Contact Body Pair. The Contact Body Pair is made of two contact bodies that form a pair. The Input Data form contains three tabs: Geometric Contact Parameters, Physical Contact Parameters, and Contact Options. Only Physical Contact Parameters of thermal analysis differ from that of the structural analysis, while Geometric Contact Parameters and Contact Options are same in both structural and thermal analyses and are described in the Body Pair (Ch. 2) in the Patran Interface to MSC Nastran Preference Guide.

Main Index

97

98

Patran Interface to MSC Nastran Thermal Load Cases

Input Data

Description

Near Contact DistTol. (DQNEAR)

Distance below which thermal contact behavior occurs for heat transfer analysis only.

Heat Transfer Coeff. (HTC)

Contact heat transfer coefficient. Can reference a temperature dependent non-spatial field. Default = 0.0 or 1.0E6 in a thermal/mechanical analysis when glue option is activated.

Near Field Conv. Coeff. (HCV)

Convection coefficient for near field behavior. Can reference a temperature dependent non-spatial field.

Distance Dep. Conv. Coeff. (HBL)

Separation distance dependent thermal convection coefficient. Can reference a temperature dependent non-spatial field.

Natural Conv. Coeff. (HNC)

Natural convection coefficient for near field behavior. Can reference a temperature dependent non-spatial field.

Natural Conv. Exp. (BNC)

Exponent associated with the natural convection coefficient for near field behavior. Can reference a temperature dependent non-spatial field.

NL Heat Trans. Coeff. (HNL)

Heat transfer coefficient for nonlinear convective heat flow for near field behavior. Can reference a temperature dependent non-spatial field.

NL Heat Trans. Exp. (BNL)

Exponent associated with the nonlinear convective heat flow for near field behavior. Can reference a temperature dependent non-spatial field.

Emissivity (EMISS)

Emissivity for radiation to the environment for near thermal radiation. Can reference a temperature dependent non-spatial field.

Thermal Glue Option (HGLUE)

Flag to activate the thermal glue option. If OFF, thermal contact conditions treated by convective heat transfer between bodies. If ON, temperature fields of bodies are tied as soon as they come in contact and there is no convective heat transfer over the body interfaces.

Load Cases Load cases in Patran enable you to group a series of load sets into one load environment for your model. Load cases are selected when defining an analysis job. The usage within MSC Nastran is similar. Patran uses the selected load cases to create the necessary SUBCASE commands in the Case Control Section of the NASTRAN input file. For information on how to define multiple static and/or transient load cases, see Load Cases Application (Ch. 5) in the Patran Reference Manual.

Main Index

Chapter 4: Running a Thermal Analysis MSC Nastran Implicit Nonlinear (SOL 600) User’s GuidePatran Interface to MSC Nastran Thermal

4

Main Index

Running a Thermal Analysis



Introduction



Review of the Analysis Form



Translation Parameters



Solution Types



Direct Text Input



Subcases



Subcase Select

100

108 114

115 129

105

100

100

Patran Interface to MSC Nastran Thermal Introduction

Introduction To run a thermal analysis, you use the procedure described below. Select the solution type

The solution type can be either steady-state or transient analysis.

Define the solution related input data

The purpose of this step is to change the default settings of job-related input data, such as Maximum Run Time, Default Initial Temperature, Radiation Parameters, and options for view factor calculations.

Define the subcase data

Similar to the previous step, the defaults for nonlinear iteration controls, time increments, and output requests can be altered in the Subcase Create section of the Analysis menu form.

Select load cases

This step selects load case(s) for an analysis job.

Submit the job

When a job is ready for analysis, the MSC Nastran solver can be retrieved by clicking on the Apply button on the main Analysis form. You can modify the default settings of translation parameters, or you can insert additional data entries using the Direct Text Input form before submitting your analysis job.

Read the analysis results

The analysis results must be read into the Patran database by invoking the Read Output2 Action on the Analysis form. The results can then be processed by selecting the Results toggle on the Patran application selections.

To submit a single load case, steady-state analysis job to MSC Nastran, you need only click on the Apply button on the main Analysis form. Patran will automatically control the appropriate default settings and other related selections. In the Patran MSC Nastran Interface, a subcase can be thought of as a Patran load case with some additional parameters (e.g., Output Requests) associated with it. This association is further strengthened since the default subcases are created for each load case and have the same name as their associated load case. In this document, the terms “load case” and “subcase” are used interchangeably. When a specific form is referenced, Load case and Subcase are capitalized.

Review of the Analysis Form The Analysis form appears when you select Analysis from the main form. To run an analysis, or to create an NASTRAN input file, select Analyze as the Action on the Analysis form. Other forms brought up by the Analysis form are used to define translation parameters, solution types, solution parameters, output requests, and load cases. These forms are described on the following pages. For further information, see The Analysis Form (p. 6) in the Patran Reference Manual.

Main Index

Chapter 4: Running a Thermal Analysis Review of the Analysis Form

Analysis Form This form appears when you select Analysis from the main menu. When preparing for an analysis run, select Analyze as the Action./

Main Index

101

102

Patran Interface to MSC Nastran Thermal Review of the Analysis Form

Parameter Action

Description Actions can be set to: Analyze Read Output2 (p. 125) Read Input File (p. 583) in the Patran Interface to MSC Nastran Preference Guide (support is limited for thermal analysis) Delete (Ch. 6) in the Patran Interface to MSC Nastran Preference Guide Monitor (Ch. 5) in the Patran Analysis Manager User’s Guide Abort (Ch. 6) in the Patran Analysis Manager User’s Guide

Main Index

Analysis Code

Indicates the selected Analysis Code and Analysis Type, as defined in the Preferences>Analysis (p. 388) in the Patran Reference Manual.

Available Jobs

List of already existing jobs. If you select one of these jobs, the name will appear in the Job Name listbox and all input data for this job will be retrieved from the database. You can submit an existing job again simply by selecting it and clicking on Apply. It is often convenient to select an existing job, modify the input data as desired, and click on Apply to submit the new job.

Job Name

Name of job. Patran will use this name as the base filename for all resulting MSC Nastran files and message files.

Chapter 4: Running a Thermal Analysis Review of the Analysis Form

Parameter

Main Index

Description

Label

Patran uses this text to generate the TITLE statement in the MSC Nastran Executive Control Section.

Solution Type

Opens a form that allows you to choose either steady-state analysis or transient analysis and to specify settings for controlling the overall analysis job.

Direct Text Input

Opens the Direct Text Input form; this form allows you to enter data directly for the File Management, Executive Control, Case Control, and Bulk Data sections of the NASTRAN input file.S

Subcases

Selects one or more subcases for the analysis job.

Subcase Select

Opens the Patran Analysis Manager form.

103

104

Patran Interface to MSC Nastran Thermal Review of the Analysis Form

The following table outlines the selections for the Analyze action. Object Entire Model

Method Full Run Check Run Analysis Deck Model Only

Current Group

Full Run Check Run Analysis Deck Model Only

Existing Deck

Full Run

The Object indicates which part of the model is to be analyzed. There are three choices for thermal analysis: Entire Model, Current Group, and Existing Deck. Entire Model

Indicates that the whole model is to be analyzed.

Current Group

Indicates that only part of the model is to be analyzed. To do this, you create a group of that part, confirm that it is the current group, then select Current Group as the Object. For more information, see The Group Menu (p. 225) in the Patran Reference Manual.

Existing Deck

Means that you wish simply to submit an existing input file to MSC Nastran. To form the input filename, Patran appends the suffix “.bdf ” to the jobname appearing in the Job Name listbox. This file must reside in the current directory.

The Method indicates how far the translation is to be taken.The methods are as follow:

Main Index

Full Run

Is the selected type if an Analysis Deck translation is performed, and the resulting input file is submitted to MSC Nastran for complete analysis.

Check Run

Is the selected type if an Analysis Deck translation is performed, and the resulting input file is submitted to MSC Nastran for a check run only.

Analysis Deck

Is the selected type if the Model Deck translation is performed, plus all load case, analysis type and analysis parameter data are translated. A complete input file, ready for MSC Nastran, will be generated.

Model Only

Is the selected type if a Bulk Data file is created that contains only the model data including node, element, coordinate frame, element property, material property, and loads and boundary conditions data. The translation stops at that point.

Chapter 4: Running a Thermal Analysis Translation Parameters

Translation Parameters This subordinate form appears when you click on the Translation Parameters button on the Analysis form.

Parameter Tolerances

Description Defines various tolerances used during translation. Division is used to prevent division-by-zero errors. Numerical is used to determine if two real values are equal. Writing is used to determine if a value is approximately zero when generating a Bulk Data entry field.

Main Index

105

106

Patran Interface to MSC Nastran Thermal Translation Parameters

Bulk Data Format: Card Format

Defines what type of fields are to be used in the Bulk Data entry. Entry format can be set to small, large, or either. If either is selected, the Minimum Significant Digits value is used to determine whether the values on a particular Bulk Data entry can be placed in small fields or whether large fields are required. The small-field format consists of Bulk Data entry fields 8 columns wide; the large field format is 16 columns wide.

Node Coordinates

Defines which coordinate frame is to be used when generating the grid coordinates. The options are reference frame, analysis frame, or global. This setting should not affect the analysis. It only changes the method used in the grid creation. It also determines which coordinate frame is referenced in the CP field of the GRID Bulk Data entry.

MSC Nastran Version

Defines which version of MSC Nastran is to be used. The version indicated here serves two purposes: to create the full name of the ALTER file to be used and to determine which Solution Sequence to be used. Be sure to specify only whole numbers and letters; e.g., 2015 or 2016.

Write Properties on Element Entries

Writes CELAS2, CDAMP2, and CONROD Bulk Data entries instead of CELAS1, CDAMP1, and CROD entries.

Numbering Options

Brings up a subordinate form, Numbering Options, 106, which defines automatic numbering offsets and possible syntaxes for encoded IDs.

Bulk Data Include File

Brings up a standard file select form which allows you to select a file to be included in the Bulk Data Section of the NASTRAN input file.

Note:

Do not turn ON this option if your model has time varying temperature boundary conditions or conductor/capacitor elements.

Numbering Options Patran allows you to define numbering offsets for IDs associated with model entities. To invoke this feature, you click on the Numbering Options button on the Translation Parameters form

Main Index

Chapter 4: Running a Thermal Analysis Translation Parameters

.

s:

Parameter

Main Index

Description

Automatic Numbering Offsets

Indicates offsets for all IDs to be automatically assigned during translation. For example, if you type 100 into the Element Properties Offset box, the numbering of element properties in the resulting NASTRAN input file will begin at 101.

Begin Contin. Marker

Specifies the continuation mnemonic format used on multiple line Bulk Data entries.

IDs Encoded in Names

Activates recognition of IDs encoded into the name of any named entry, such as a material.

Number Only

Recognizes and uses an ID if, and only if, the name of the entity is an actual number, such as “105.” This option is ON by default.

107

108

Patran Interface to MSC Nastran Thermal Solution Types

Beginning Number

Recognizes an ID if the number begins the name, such as “52_shell_property.” This option is OFF by default.

Trailing Number

Recognizes an ID if it tails the name, such as “shell_property_52.” This option is OFF by default.

Encoded Syntax

Recognizes an ID if it directly follows the first occurrence of the specified syntax. For example, with this option activated and the specified syntax set to “.”, the ID assigned to a material given the name “Steel_1027.32” would be 32.

Note that both the Patran Neutral file reader and the Patran MSC Nastran input file reader preserve the IDS of named entities with a “.” syntax, so that an MSC Nastran PSHELL entry of ID 12 will be assigned the name “PSHELL.12.” This last option allows great continuity between input model data and output model data. This option is ON by default, and the default Syntax Marker is “.” Note:

“The Encoded IDs” option currently only works for element properties and material properties.

Solution Types Three solution types are supported in the Patran MSC Nastran thermal interface: steady state, transient, and linear structural. The two thermal (only) analysis types employ nonlinear solution algorithms so that nonlinear material properties or boundary conditions can be included in the model. The linear structural analysis type (STRUCTURAL HEAT ANALYSIS) performs first a linear steady-state thermal analysis (SOL 153), then it performs a linear structural analysis (SOL 101) using the results of the thermal analysis as loading on the structural model. Use the form shown below to select the solution type. By default, a steadystate thermal analysis is requested

Main Index

Chapter 4: Running a Thermal Analysis Solution Types

.

Parameter

Main Index

Description

Steady State Analysis

Performs linear or nonlinear steady-state thermal analysis using MSC Nastran Solution Sequence 153.

Transient Analysis

Performs linear or nonlinear transient thermal analysis using MSC Nastran Solution Sequence 159

Structural Heat Analysis

Performs linear structural analysis using MSC Nastran Solution Sequence 101, and the temperature results from a linear steady-state thermal analysis

Solution Parameters

Brings up a form that controls various settings that pertain to the overall analysis process.

Solution Sequence

Displays the MSC Nastran Solution Sequence number.

109

110

Patran Interface to MSC Nastran Thermal Solution Types

Solution Parameters The solution parameter form contains options and subordinate forms for defining parameters that affect the overall analysis. The Subcase Parameter forms, described below, are used for setting input data that control the analysis only within a single subcase. You should always review the settings on both forms before submitting an analysis .

Parameter

Main Index

Description

Automatic Constraints

Requests that the model singularities be constrained automatically.

Solution Sequence

Select the Solution Sequence. If a static analysis is being performed (SOL 153) the choices are SOL 153, 400, or 600. If a transient analysis is being performed (SOL 159) the choices are SOL 159, 400, or 600.

Data Deck Echo

Controls whether or not the input file is printed to the Nastran output file (f06).

Maximum Printed Lines

Maximum number of lines to be written to the Nastran output file (f06).

Maximum Print Time

Maximum number of CPU minutes the analysis job is allowed to run. The job will terminate when this limit is reached.

Default Init Temperature

Defines the default initial temperature for all node points which have not been given an initial temperature by the Initial Temperature object of Loads/BCs.

Chapter 4: Running a Thermal Analysis Solution Types

Radiation Parameters View Factor Parameters Results Output Form

Buttons to bring up subordinate forms for additional parameters needed for radiation analysis. Select this button to specify what is to be output from the analysis.

Radiation Parameters Figure 4-1

Parameter

Description

Absolute Temperature Scale The value of “absolute temperature scale” may be entered directly or selected from the menu. Stefan-Boltzmann Constant The value of the Stefan-Boltzmann constant must be input in units that are consistent with the rest of the model definition. Values in several different combinations of units are available for selection in the menu, or you can enter the value directly.

View Factor Parameters This subordinate form defines parameters and output options to calculate view factors. For all the radiation enclosures selected, the Patran MSC Nastran forward translator automatically enables the Gaussian integration view factor calculation method by applying the terminology defined here. A more detailed description of the calculation of view factors can be found in the MSC Nastran Thermal Analysis User’s Guide.

Main Index

111

112

Patran Interface to MSC Nastran Thermal Solution Types

Parameter

Main Index

Description

View Factor Scale

Defines the view factor sum that the enclosure will be set to if the view factor summation of the enclosure is greater than 1.0. No scaling is performed if this databox is left blank.

Gaussian Int Order (3rd Body Shading)

Defines Gaussian integration order for calculating net effective view factors in the presence of third-body shading.

Gaussian Inter Order (Self Shading)

Defines Gaussian integration order for calculating net effective view factors in the presence of self shading.

Discretization Level

Defines the discretization level used in the semi-analytic contour integration method.

Error Tolerance

Defines the error tolerance above which a corrected view factor is calculated using the semi-analytic contour integration method.

Assumed Level of Calculation

Defines the assumed level of calculation below which the numbers are considered to be zero.

Assumed Level of Warpage

Defines the assumed degree of warpage above which the actual value of Fii will be calculated. (For a flat surface Fii = 0.0)

Chapter 4: Running a Thermal Analysis Solution Types

Diagnostic Output Requests

Defines diagnostic output request options for the radiation exchange surfaces. The output will be written to the NASTRAN output (f06) file.

View Factor Calculation Diagnostic

Defines the output device options (Both, Print, Punch, None) for printing or punching view factors onto RADLST/RADMTX entries. The printed view factors are written to the NASTRAN output (f06) file, while the punched view factors are written to a punch file, job_name.pch. If the FEM mesh and the application regions of loads and boundary conditions are not changed in subsequent runs, the lengthy view factor calculations may be skipped by including the RADLST/RADMTX punch files, which can be retrieved from the Bulk Data Include File menu in the Translation Parameters form.

Note:

See the MSC Nastran Thermal Analysis User’s Guide for a description of error estimators for view factor calculation.

Solution Parameters for Transient Analysis

Main Index

113

114

Patran Interface to MSC Nastran Thermal Direct Text Input

Parameter

Description

Print Out Singularities

Controls the printout of model singularities.

Data Deck Echo

Controls whether or not the input file is printed to the NASTRAN output (f06) file.

Maximum Printed Lines

Maximum number of lines to be written to the NASTRAN output (f06) file.

Maximum Run Time

Maximum number of CPU minutes the analysis job is allowed to run. The job will terminate when this limit is reached.

Default Init Temperature

Defines the default initial temperature for all grid points which have not been given an initial temperature by the Initial Temperature Object of Loads/BCs.

Radiation Parameters

The radiation and view factor input data forms are identical to those shown above for steady-state analysis.

Direct Text Input This form allows you to enter entries directly in the File Management, Executive Control, Case Control, and Bulk Data sections of the NASTRAN input file. The input file reader1 also creates these entries for any unsupported entries in the input file. If the data is entered by the user, the Write to Input file toggle default setting is ON. If the data comes from the input file reader, the default for the Input file toggle is OFF. A good practice is to review and edit the MSC Nastran input entries. If they should be written to any input files subsequently created by the interface, the appropriate Write to Input file toggle should be set to ON. Text entered into the Case Control section is written to the input file before the first subcase. The Direct Text Input option on the Subcase Create form should be used to enter text directly within a subcase definition. The current input file reader provides limited support for thermal analysis.

1

Main Index

Chapter 4: Running a Thermal Analysis Subcases

.

Parameter

Description

Bulk Data Section

Switches to determine which data section the MSC⁄ NASTRAN input would be sent.

OK

Saves the current setting and data for the four sections and closes the form.

Clear

Clears the current form.

Reset

Resets the form back to the data values it had at the last OK.

Cancel

Resets all four forms back to its previous value and closes the form

Subcases This form appears when you select the Subcase Create button on the Analysis form. The subcase is the MSC Nastran mechanism for associating loads and boundary conditions, output requests, and various other input data to be used during part of a complete run. The Patran MSC Nastran interface automatically associates default parameters and output requests with each Patran load case to create a subcase with the same name as the load case. You can access the Subcase Parameters and Output Requests forms to view or modify these defaults

Main Index

115

116

Patran Interface to MSC Nastran Thermal Subcases

Parameter

Main Index

Description

Available Subcases

Displays all the available subcases associated with the current Solution Sequence.

Subcase Name

Displays the subcase name that is being created, modified, or deleted. You can type in the subcase name or pick it from the Available Subcases listbox.

Chapter 4: Running a Thermal Analysis Subcases

Available Loadcases

Displays all the available loadcases in the current database. Only one loadcase can be selected per subcase.

Subcase Options

These buttons bring up subordinate forms for additional input associated with the subcase.

Note about Structural Heat Analysis: 

There can be only two subcases. • First subcase has only thermal Loads/BCs (Case Control LOAD and SPC entries) and thermal

Output Requests (Case Control THERMAL entry). • Second subcase has only structural Loads/BCs (Case Control LOAD and SPC entries) and

structural Output Requests (Case Control STRESS entry). The temperatures from the thermal analysis (first subcase) are a part of the structural Loads/BCs (Case Control TEMPERATURE(LOAD) = ID (ID of the first subcase) entry). 

Both thermal (Bulk Data MAT4 entry) and structural (Bulk Data MAT1 entry) material properties must exist. The IDs of the MAT4 and MAT1 entries must be equal.



PARAM, HEATSTAT, YES in written to the Bulk Data section to enable this type of analysis.

To set up and perform a chained thermal-structural analysis in one run using SOL 101. The procedure is to: 1. With Patran Preferences set to MSC Nastran, Structural, create and set up your structural LBCs and load case 1. Change the Patran Preferences to MSC Nastran, Thermal, create and set up your thermal LBCs and load case 1. Set the Solution Type to STRUCTURAL HEAT ANALYSIS 1. Set up two Subcases, one referencing the structural load case and the other referencing the thermal load case. 1. Select the two Subcases in the order: Thermal, Structural 1. Submit the job The Nastran run is submitted as a SOL 101 with two Subcases. The first subcase is the heat transfer run to determine the temperature loading. The temperature results from the first subcase are used along with any other structural LBCs called out in the second subcase, which is a SOL 101 run. PARAM, HEATSTAT, YES is written to the input file.

Subcase Parameters The controls and parameters set on the Subcase Parameters forms apply to a single MSC Nastran subcase within the overall analysis run.

Main Index

117

118

Patran Interface to MSC Nastran Thermal Subcases

Steady-State Subcase This subordinate form appears when the Subcase Parameters button is selected on the Subcase Create form and the solution type is Steady State. This form provides for the definition of the input data that controls the solution of the nonlinear equations. Occasionally, when solving a set of nonlinear equations, it may not be possible to obtain a solution directly with the total heat load applied. Instead, the solution is obtained by applying the loading in increments, solving the system equations for the current fraction of the total load, and using that solution as the starting point for the next increment of load. This process continues until the desired total heat load is applied. It should be mentioned that the number of load increments has no effect on the accuracy of the solution-- it is merely a computational technique to aid in obtaining the solution efficiently. In linear or mildly nonlinear problems, a single increment is usually applied. In highly nonlinear problems, dozens of increments may be required to obtain a converged solution. This incremental procedure is only applicable with respect to applied heat loads and specified temperature boundary conditions. There is no incremental provision for convection or radiation boundary conditions. As a result, it is more common with highly nonlinear boundary conditions to exceed the nonlinear iteration limit. This defaults to 25 currently, but can be increased.

Main Index

Chapter 4: Running a Thermal Analysis Subcases

Parameter

Description

Number of Load Increments

Number of increments over which the heat load is applied.

Matrix Update Method

These parameters control aspects of the nonlinear equation solving process. For more information, see table on page 121.

Number of Iterations Per update Allowable Iterations per Increment

Main Index

Convergence Criteria

The convergence criteria are used to determine when the solution is sufficiently accurate to be considered “converged.” See page 121 for more information.

Contact Table

See the next page for the contact table form.

119

120

Patran Interface to MSC Nastran Thermal Subcases

Thermal Contact Table

This data can optionally be defined for each individual contact pair (which is selected by clicking on the cell of the above contact body matrix) and is written to the BCTABLE bulk data entry. See the MSC Nastran Quick Reference Guide for more information.

Main Index

Chapter 4: Running a Thermal Analysis Subcases

The parameters controlling the steady-state solution process are discussed more fully in the table below. More extensive information can be found in the MSC Nastran Thermal Analysis User’s Guide. Parameter Name Matrix Update Method

This option determines the strategy used to determine how often to update (reform) the nonlinear conductance and radiation matrices. The three options are Automatic, Semi-Automatic, and Controlled Iters. The optimum strategy would result in the lowest computational cost. When the Automatic option is selected, MSC Nastran tries to select the most efficient strategy based on convergence rates. If Controlled Iters is selected, the matrices are updated after a prescribed number of iterations (determined by the Number of Iterations per Update parameter).

Number of Iterations per Update

When the Matrix Update Method is set to Controlled Iters, this is the number of iterations before the matrices are reformed.

Allowable Iterations per Increment

This parameter specifies the maximum number of allowed iterations in a load increment. If this number is exceeded, the load increment is halved and the iteration process repeated.

Convergence Criteria

The convergence criteria provide for the comparison of user-requested maximum levels of error and the error in the solution as estimated numerically. In this sense, the convergence criteria determine when the solution is sufficiently accurate to be considered converged. Any or all of the three convergence criteria listed below can be selected. When more than one criteria is selected, each one must be satisfied for convergence to be achieved.

Temperature Error

Indicates whether a temperature convergence criterion should be used. If Temperature Error is selected, the Temperature Tolerance field becomes active. A norm of the temperature increment vector calculated in the iteration must be less than this tolerance for a converged solution.

Temperature Tolerance

Load Error Load Tolerance

Work Error Work Tolerance

Main Index

Description

Indicates whether a load convergence criteria should be used. If Load Error is selected, the Load Tolerance field becomes active. A norm of the residual heat load vector must be less than this tolerance for a converged solution. Indicates whether a work convergence criteria should be used. If Work Error is selected, the Work Tolerance field becomes active. The incremental work associated with the iteration must be less than this tolerance for a converged solution.

121

122

Patran Interface to MSC Nastran Thermal Subcases

Transient Subcase Parameters This subordinate form appears when you select the Subcase Parameters button on the Subcase Create form and the solution type is Transient. This form provides for the definition of the input data that controls the solution of the nonlinear time-dependent equations. The integration in time is carried out using Newmark’s method with variable time steps. An initial time step and the number of time steps must be input. Since the time increment is adjusted during the analysis, the actual number of time steps may not be equal to the input value. However, the total time duration will be close to the product of the input values.

Parameter Initial Time Step

Main Index

Description Initial time increment for the Newmark method.

Chapter 4: Running a Thermal Analysis Subcases

Number of Time Steps

This number is used along with the initial time step to calculate the total time duration.

Number of Bisections Per Update

Defines the maximum number of time step bisections to be used in each matrix update.

Allowable Iterations per Time Step

The maximum number of allowed iterations in a time step.

Convergence Criteria

The convergence criteria are described above for the steady-state case. The temperature convergence criteria must be selected if the analysis involves any time varying temperature boundary conditions.

Fixed Time Steps

Directs MSC Nastran to use the initial time step for all time steps. This disables the automatic time stepping mechanism.

Exit on Failure to Convergence

If this toggle is ON, the run will terminate if the converge criteria are not met for any time step. If OFF, the run continues to the next time step.

Structural Heat Subcase Parameters This subordinate form appears when you select the Subcase Parameters button on the Subcase Create form and the solution type is Structural Heat. This form provides for the definition of the input data that controls the solution of the linear structural equations. The parameters that can be set have to do with 1) Default Load Temperature, 2) Rotor Dynamics, 3) Contact Table, and 4) Solvers/Options..

Main Index

123

124

Patran Interface to MSC Nastran Thermal Subcases

Parameter

Description

Default Load Temperature

Default Load Temperature is for specifying the temperature at nodes for which the temperature has not been specified using Loads/BCs.

Enable Rotor Dynamics

By clicking Enable Rotor Dynamics, and clicking Specify Rotor Speed, several things are to be specified. They are 1) Reference Rotor, 2) the units of the speed, and 3) Rotor Speed.

Contact Table

Clicking the Contact Table button displays the Contact Table form. This form is used to specify what and how contact bodies are to be in contact. For example, rubber seal (flexible) contacts door (rigid). See Thermal Contact Table, 120

Solver / Options

Clicking the Solvers / Options button displays the Solvers / Options form that is used to specify the Solver Type (for example, Nastran Default or an iterative method), a Preconditioner method (for example, Cholesky), Maximum Number of Iterations, and other parameters.

Output Requests The output requests forms allow you to define what result quantities will be written to the MSC Nastran print file for viewing and the OUTPUT2 file for import into Patran. A reasonable set of default result quantities are predefined. The simplest way to change these is to use the Basic Output Requests form.More control over output quantities is provided for sophisticated users by changing the Form Type menu from Basic to Advanced. The Basic form is shown below.

Main Index

Chapter 4: Running a Thermal Analysis Subcases

Parameter

Main Index

Description

Solution Sequence

The available output requests depend on the active Solution Sequence as indicated by this value.

Form Type

This option menu is used to switch between the advanced and basic versions of this form.

125

126

Patran Interface to MSC Nastran Thermal Subcases

Select Result Types

Displays the appropriate result types that may be selected for the solution sequence indicated at the top of the form. The output requests are selected one at a time by clicking.

Output Requests

Displays the selected output requests for the subcase shown at the top of the form.

Delete

Deletes the output request highlighted in the Output Requests listbox

Note:

The OK button accepts the output requests and closes the form. The Defaults button deletes all output requests and replaces them with defaults. The Cancel button closes the form without saving the output requests.

When the Form Type is set to Advanced, the Output Requests form expands to the form below. The same result types are available in the Select Result Type listbox, but more options are available to control these .

Main Index

Chapter 4: Running a Thermal Analysis Subcases

Parameter

Description

Select Group/SETS

This listbox is used to select the group of nodes or elements to which the output requests relate.

Select Result Type

Use this listbox to select the result type to be created.

Options

These options are appropriate for the highlighted result type. They also indicate the options that were selected for a highlighted output request. See Table 4-1.

Output Requests

Use this listbox to select output requests that are to be modified or deleted.

Title

Creates output requests for highlighted result types. It also modifies highlighted output requests. The button label changes to reflect the operation.

Note:

The ALL FEM set must be selected to request the heat flux output associated with loads and boundary conditions. Table 4-1 Output Request Form Options

Options Sorting

Label

Descriptions

By Node/Element

No

Output is presented as tabular listing of nodes/elements for each load step or time.

By Time/Load Step

No

Output is presented as tabular listing of load step/time for each node or element type.

No

Requests that the output be written to the NASTRAN output (f06) file.

Punch

No

Requests that the output be written to the punch file (job_name.pch).

Both

No

Requests that the output be written to the NASTRAN output (f06) file and the punch file (job_name.pch).

Output Device Print Options

Main Index

Multiple Select Allowed

127

128

Patran Interface to MSC Nastran Thermal Subcases

Options

Label

Multiple Select Allowed

Descriptions

IntermediateO Yes utput Options

Once per subcase

Intermediate outputs are requested for every computed load increment. Applicable for steadystate analysis only.

No

Once per subcase

Intermediate outputs are requested for the last load of the subcase. Applicable for steady-state analysis only.

All

Once per subcase

Intermediate outputs are requested for every computed and user-specified load increment. Applicable for steady-state analysis only.

--

Once per subcase

An integer ‘n’ that specifies the percentage of intermediate outputs to be presented for transient analysis. Default = 100.

Percent of Step Output

Direct Text Input This form is used to directly enter entries into the Case Control section for the defined subcase.

Parameter

Description

Write at the Start of Subcase Directly entered entries may potentially conflict with those created by the interface. Writing these entries to the file can be controlled with this toggle. Write ar the End of Subcase

Main Index

Chapter 4: Running a Thermal Analysis Subcase Select

OK

Saves the current setting and data and closes the form.

Clear

Clears the current form.

Reset

Resets the form back to the data values it had at the last OK.

Cancel

Resets the form back to its previous value and closes the form.

Subcase Select This form appears when you select the Subcase Select button on the Analysis form. It allows you to select a sequence of subcases associated with an analysis job. The Default subcase is selected automatically. If multiple subcases are selected, the subcases selected must contain identical sets of convection, radiation boundary conditions, and fixed value temperature boundary conditions because these boundary conditions are not subcase selectable in MSC Nastran thermal analysis

Parameter

Main Index

Description

129

130

Patran Interface to MSC Nastran Thermal Subcase Select

Subcases for Solution Sequence

Displays all the available subcases for the current solution sequence. The current solution sequence is displayed at the top of the form.

Subcases Selected

Displays all subcases that have been associated with the current jobname.

Note:

Main Index

Within the current Patran MSC Nastran design, only those boundary conditions referred to as loads are subcase selectable. All heat flux types and temperature boundary specifications are defined as thermal loads, whereas all occurrences of convection and radiation are defined as boundary conditions and are not subcase selectable. As a result, the use of multiple subcases in MSC Nastran thermal analysis has limited utility and in general is not recommended.

Chapter 5: Results Processing and Visualization MSC Nastran Implicit Nonlinear (SOL 600) User’s GuidePatran Interface to MSC Nastran Thermal

5

Main Index

Results Processing and Visualization 

Overview



Reading Thermal Analysis Results



Results Visualization Options

132

143

132

132

Patran Interface to MSC Nastran Thermal Overview

Overview Before postprocessing of thermal results can occur, the MSC Nastran analysis results must be loaded into the Patran database through the Read Output2 or Attach XDB Action on the Analysis form. You can then display, sort, or retrieve the results using the following options: Contour Plots (Fringe Plots)

Contour Plots can be made for temperatures (isotherms), temperature gradients, and heat fluxes. Since temperature gradients and heat fluxes are vector quantities, plotting their values on the geometry requires selecting the desired result quantity; magnitude, x-component, y-component, or zcomponent. Contour plots can be made for any steady-state solution, and any temporal solution state in a transient analysis.

XY Plots

The most common XY plot for heat transfer is the representation of nodal temperature versus time. On an elemental basis, temperature gradients and heat fluxes may also be represented as functions of time. In a general sense, the following XY plot types are available: 

Results versus Global Variables



Results versus Another Result



Results versus Distances



Global Variables versus Global Variable



Result in Local System



Result in Arbitrary Path

Global variables include time and percent of load*. Results include: temperature, temperature gradients, and heat fluxes. * Percent of load refers to the nonlinear extreme solution technique of determining the result by incrementing the load toward its full level from a reduced initial condition or load.

Reading Thermal Analysis Results The Analysis form will appear when you select Analysis from the main form.

There are currently two Actions--Read Output2 and Attach XDB--for importing results. Selecting Read Output2 as the Action on the Analysis form allows the model and⁄or results data to be read into the Patran database from an NASTRAN OUTPUT2 file. Subordinate forms of the Analysis form will define translation parameters, which control the data to be translated, and the OUTPUT2 file from which to translate. The

Main Index

Chapter 5: Results Processing and Visualization Reading Thermal Analysis Results

OUTPUT2 data files are created by placing a PARAM,POST,-1 entry in the MSC Nastran Bulk Data section. Selecting Attach XDB as the Action on the Analysis form allows the results data from a MSC.Access database (an .xdb file) to be accessed. In this case the results are not read directly into the Patran database but instead remain in the MSC.Access database. Only what is termed as meta data is read into the Patran database. Meta data consists of the Result Case names, their associated subcases, primary and secondary result types, global variables, and the file location of the MSC.Access database or .xdb file. The Meta data is used to translate results when the user attempts to postprocess the model. Subordinate forms of the Analysis form will define translation parameters, which control the data to be accessed on attachment. MSC.Access databases are created by placing a PARAM,POST,0 entry in the MSC Nastran Bulk Data section.

Parameter

Description

Attach HDF5

See following sections

Attach XDB

See following sections

Read Output 2

See following sections

Attach MASTER

Use this option if results are to be attached using MASTER/DBALL direct results access.

Attach T16/T19

Use this option if SOL 600 results are to be attached using T16/19 direct results access.

Attach HDF5 This form appears when you select Analysis from the main menu. Attach HDF5, as the selected Action, defines the type of data to be read from the MSC Nastran h5 results file into Patran. The Object choices are Result Entities, Model Data, or Both.

Main Index

133

134

Patran Interface to MSC Nastran Thermal Reading Thermal Analysis Results

Parameter Object

Main Index

Description When the Object selected is Result Entities, the model data must already exist in the database. No results can be read into Patran if the associated node or element does not already exist. Model Data only reads the model data that exists in the results file. Both will first read the model data, then the result entities. If Model Data or Both are selected, you must ensure that there will not be any ID conflicts with existing model entities.

Chapter 5: Results Processing and Visualization Reading Thermal Analysis Results

Job Name

Defines the jobname to be used for this job. The same jobname used for the Analyze Action should be used for the Read Output2 Action. This will allow Patran to load the results directly into the load cases that were used for the analysis.

Select Result File

Selects the results file (*.h5) to be read. The form that is called up lists all files recognized as being MSC Nastran results files. Even if there is only one h5 file, it must be explicitly selected.

Translation Parameters

Begins the translation of NASTRAN HDF5 results into the Patran database for postprocessing.

HDF5 Formats This is a MSC Nastran HDF5 Result (.h5) file containing results from SOL 101 runs. The h5 file is created by including the MDLPRM,HDF5,1 entry in the bulk data section of the input deck. Include this in Direct Text Input, 114 when creating/running a job. As an alternative way, the system cell 702 can be given in command line as the following: nastran example.dat sys702=1 Import of Model data also supported only for nodes and elements from h5 file thus it is recommended to import the corresponding input deck to get the complete model data before importing the h5 file for result entities. Supported HDF5 Result Quantities

All the result quantities supported through XDB, new OUTPUT2 and MASTER are supported in HDF5 and the new support through HDF5 includes:

Main Index



Acoustic Pressure



Acoustic Intensity



Acoustics/Velocity



Acoustic Accelerations



Complex Forces in Bars both translation and rotation



Complex CFAST Forces both translation and rotation



CWELD Moments



Strain Energy



CBAR axial and bending strain and stress



CBAR complex axial and bending strain and stress



CBEND axial and bending strain and stress



CBEND complex axial and bending strain and stress



CHEX 20 – Nonlinear strains and stresses

135

136

Patran Interface to MSC Nastran Thermal Reading Thermal Analysis Results

Read Output2 Form This form appears when you select Analysis from the main menu. Read Output2, as the selected Action, defines the type of data to be read from the MSC Nastran results file into Patran. The Object choices are Result Entities, Model Data, or Both.

Main Index

Chapter 5: Results Processing and Visualization Reading Thermal Analysis Results

Parameter

Description

Object

When the Object selected is Result Entities, the model data must already exist in the database. No results can be read into Patran if the associated node or element does not already exist. Model Data only reads the model data that exists in the results file. Both will first read the model data, then the result entities. If Model Data or Both are selected, you must ensure that there will not be any ID conflicts with existing model entities.

Job Name

Defines the jobname to be used for this job. The same jobname used for the Analyze Action should be used for the Read Output2 Action. This will allow Patran to load the results directly into the load cases that were used for the analysis.

Select Result File

Selects the results file (*.op2) to be read. The form that is called up lists all files recognized as being MSC Nastran results files. Even if there is only one .op2 file, it must be explicitly selected.

Translation Parameters

Begins the translation of NASTRAN OUTPUT2 results into the Patran database for postprocessing.

Results File Formats The Patran MSC Nastran interface supports several different OUTPUT2 file formats. The interface, running on any platform can read a binary format OUTPUT2 file produced by MSC Nastran running on any of these same platforms. For example, a binary OUTPUT2 file produced by MSC Nastran running on an IBM RS/6000 can be read by Patran running on DEC Alpha. Patran may be able to read binary format OUTPUT2 files from other platforms if they contain 32 bit, IEEE format entities (either Big or Little Indian). For platforms that do not produce OUTPUT2 files in these formats, Patran can read OUTPUT2 files created with the FORM=FORMATTED option in MSC Nastran. This option can be selected from the Analyze/Translation Parameters form in Patran Analysis menu and directs MSC Nastran to produce an ASCII format OUTPUT2 file that can be moved between any platforms. The Patran MSC Nastran interface detects this format when the OUTPUT2 file is opened, automatically converts it to the binary format, and then reads the model and/or results into the Patran database. An OUTPUT2 file is created by MSC Nastran by placing a PARAM,POST,-1 entry in the Bulk Data portion of the input file. The formatted or unformatted OUTPUT2 file is specified in the FMS section using an ASSIGN OUTPUT2 = filename, UNIT=#, FORM=FORMATTED (or UNFORMATTED) command. See Translation Parameters, 105.

Supported OUTPUT2 Results The following table indicates all the possible results quantities that can be loaded into the Patran database during results translation from MSC Nastran. The Primary and Secondary Labels are items selected from the postprocessing menus. The Type indicates whether the results are Scalar or Vector and determines which postprocessing techniques are available to view the results quantity. Data Block indicates which NASTRAN

Main Index

137

138

Patran Interface to MSC Nastran Thermal Reading Thermal Analysis Results

OUTPUT2 datablock the data comes from. The Description gives a brief discussion about the results quantity, such as whether it is a nodal or elemental result, and what type of output request will generate this datablock. Primary Level

Secondary Level

Type

Data Block

Description

Temperatures

S

OUGV1

Nodal temperatures

Applied Linear Loads

S

OPG1

Nodal applied linear loads

Heats of Constraint

S

OQG1

Nodal heats of constraint

Applied Load

S

OEF1

Heat flows from applied surface loads

Free Conv

S

OEF1

Heat flows from free convection

Forced Conv

S

OEF1

Heat flows from forced convection

Radiation

S

OEF1

Heat flows from radiation

Total

S

OEF1

Total heat flows into surface elems

Temperature Gradients

V

OEF1

Conduction element temperature gradients

Heat Fluxes

V

OEF1

Conduction element heat fluxes

Enthalpies

S

OUGV1

Nodal enthalpies

Rate of Change of Enthalpies

S

OUGV1

Rate of change of nodal enthalpies

Heat Flows

Heats of Constraint are the mathematical (non-physical) heat flow into or out of a nodal point which is associated with a user-specified temperature. In real-world analysis, we generally do not know the structural temperatures, but we do know something about the heat loads, convection and radiation boundaries, etc. We then invoke MSC Nastran to calculate the temperatures. However, suppose we have results of an experiment in which a thermocouple is used to measure the boundary temperature. This temperature could then be applied as a boundary condition in the finite element model. In the experimental test, there may well be heat flow into or out of the boundary, but we have not made any attempt to qualify or quantify the heat flow mechanism because we actually measured the temperature. When the MSC Nastran thermal analysis is performed, the heat of constraint output represents the heat flow that must occur at the physical boundary to support or maintain the measured temperature.

Main Index

Chapter 5: Results Processing and Visualization Reading Thermal Analysis Results

In addition to standard results quantities, several Global Variables can be created. This table outlines Global Variables that may be created. Global Variables are results quantities where one value is representative of the entire model: Label

Type

Data Block

Description

Time

S

Oxxx

Time value of the time step

Percent of Load

S

Oxxx

Percent of load value for a nonlinear steady-state analysis

When reading model data from an NASTRAN OUTPUT2 file by selecting the Model Data Object, all the data that will be created in the Patran database and the location in the OUTPUT2 file from where it is derived are described in the following table: Item Nodes

Block GEOM1

Description Node ID Nodal Coordinates Reference Coordinate Frame Analysis Coordinate Frame

Coordinate Frames

GEOM1

Coordinate Frame ID Transformation Matrix Origin Can be Rectangular, Cylindrical, or Spherical

Elements

GEOM2

Element ID Topology (e.g., Quad4 or Hex20) Nodal Connectivity

Attach XDB Form This form appears when you select Analysis from the main menu. Attach XDB, as the selected Action, defines the type of data to be read from the MSC Nastran results file into Patran. The Object choices are Result Entities, Model Data, or Both.

Main Index

139

140

Patran Interface to MSC Nastran Thermal Reading Thermal Analysis Results

Parameter Method

Main Index

Description The Method can currently only be set to Local. This means that the MSC.Access database exists locally, or via NFS, somewhere on the machine that Patran is running on.

Chapter 5: Results Processing and Visualization Reading Thermal Analysis Results

Object

When the Object selected is Result Entities, the model data must already exist in the Patran database. Only metadata or catalog information such as Result Cases/Types, Global Variables, and file connection is read into the Patran database. The results data remains in the XDB file. The Model Data Object only imports Nodes, Elements, and Coordinate Systems. The Both selection will first read the model data, then the result entities. If Model Data or Both are selected, you must ensure that there will not be any ID conflicts with existing model entities.

Job Name

Defines the jobname to be used for this job. The same jobname used for the Analyze Action should be used for the Attach XDB Action. This will allow Patran to load the results directly into the load cases that were used for the analysis.

Select Result File

Selects the results file (MSC.Access database or xdb file) to be read. The form that is called up lists all files recognized as being MSC Nastran results files. By default, all files with an xdb extension are listed on them. This can be changed with the filter. One may attach up to 20 .xdb files simultaneously.

Translation Parameters

Begins the reading of the meta data from the MSC Nastran xdb file for postprocessing.

Results File Formats The same basic issues exist for MSC.Access databases as for OUTPUT2 files. For example, the MSC.Access database (xdb file) may be exchanged between computer systems that have binary compatibility. That is, an XDB file generated on a SUN Machine may be used on an IBM or SGI computers. However, in order to exchange the XDB file on binary incompatible machines, one needs to use the TRANS and RECEIVE utilities delivered with every installation of MSC Nastran. TRANS converts an XDB file generated by MSC Nastran to an “equivalent” character, i.e. ASCII, file which can be transported to another computer across the network via ftp or rcp. RECEIVE converts the character file back into the XDB format for postprocessing. For more information on TRANS and RECEIVE utilities, please consult the “Configuration and Operations Guide” for V70 of MSC.Nastran. A MSC.Access XDB database is created by MSC Nastran by placing a PARAM,POST,0 entry in the Bulk Data portion of the input file. See Translation Parameters, 105. In this release, it is assumed that the geometry, loads, and results ouput all reside in the same physical XDB file. That is, "split" XDB databases are not supported.

Supported MSC.Access Results The following tables list the currently supported quantities from the MSC.Access database (xdb file). The Primary and Secondary Labels are items selected from the postprocessing menus. The Type indicates whether the results are Scalar or Vector and determines which postprocessing techniques are available to view the results quantity. The Object indicates which MSC.Access object the data comes from. The Description gives

Main Index

141

142

Patran Interface to MSC Nastran Thermal Reading Thermal Analysis Results

a brief discussion about the results quantity, such as whether it is a nodal or elemental result, and what type of output request will generate this datablock. To get further information on the MSC.Access, i.e. XDB, objects supported in Patran, please use the ddlprt and ddlqry utilities delivered with every installation of MSC Nastran. ddlprt is MSC.Access' on-line documentation. ddlqry is MSC.Access’ Data Definition Language (DDL) browser. See “Configuration and Operations Guide” for MSC.Nastran V70. Primary Level

Type

Object

Description

Temperatures

S

THERR

Nodal temperatures

Applied Linear Loads

S

HTFLR

Nodal applied linear loads

Heats of Constraint

S

HTFFR

Nodal heats of constraint

Applied Load

S

QHBDY

Heat flows from applied surface loads

Free Conv

S

QHBDY

Heat flows from free convection

Forced Conv

S

QHBDY

Heat flows from forced convection

Radiation

S

QHBDY

Heat flows from radiation

Total

S

QHBDY

Total heat flows into surface elems

V

QBARR, Conduction element QBEMR,QCON temperature gradients R, QHEXR,QPENR , QQD4R, QQD8R, QRODR, QTETR, QTUBR, QTX6R

Heat Flows

Temperature Gradients

Main Index

Secondary Level

Chapter 5: Results Processing and Visualization Results Visualization Options

Primary Level

Secondary Level

Type

Object

Description

Heat Fluxes

V

QBARR, Conduction element QBEMR, heat fluxes QCONR, QHEXR,QPENR , QQD4R, QQD8R, QRODR, QTETR, QTUBR, QTX6R

Enthalpies

S

ENTHR

Nodal enthalpies

Rate of Change of Enthalpies

S

ENRCR

Rate of change of nodal enthalpies

Heats of Constraint are the mathematical (non-physical) heat flow into or out of a nodal point which is associated with a user-specified temperature. In real-world analysis, we generally do not know the structural temperatures, but we do know something about the heat loads, convection and radiation boundaries, etc. We then invoke MSC Nastran to calculate the temperatures. However, suppose we have results of an experiment in which a thermocouple is used to measure the boundary temperature. This temperature could then be applied as a boundary condition in the finite element model. In the experimental test, there may well be heat flow into or out of the boundary, but we have not made any attempt to qualify or quantify the heat flow mechanism because we actually measured the temperature. When the MSC Nastran thermal analysis is performed, the heat of constraint output represents the heat flow that must occur at the physical boundary to support or maintain the measured temperature.

Results Visualization Options The Results or XY Plot toggle, located on the Patran application selections, may be chosen to visualize thermal analysis results. The Results application displays contour plots and XY plots that can be sorted or grouped by various kinds of variables. The XY Plot application creates and manages the definitions of XY windows, curves, and titles. It also manages the display of XY plot information.

The following pages describe how to process basic thermal results. For more information on postprocessing results, see Postprocessing Results and XY Plotting.

Main Index

143

144

Patran Interface to MSC Nastran Thermal Results Visualization Options

Contour Plots Thermal contours can be plotted using the Quick Plot object (default) selected from the Results application. If advanced features or XY plots are desired, the Fringe or Graph object must be used.

Main Index

Chapter 5: Results Processing and Visualization Results Visualization Options

Parameter

Description

Select Result Cases

Selects the desired result case. This will fill out the Select Fringe Result listbox below. If this listbox is empty, no results exist in the database. Results can be imported from the Analysis application or with Import in the FIle pulldown menu.

Select Fringe Result

After selecting a result case, the plot options are displayed. This listbox is used to select a desired contour plot.

Select Deformation Result

Ignores this listbox for thermal analysis.

Apply

Click on Apply to create the contour plot.

To create a contour plot: 1. Select the results case from the first listbox. 1. Select the fringe result from the second listbox. 1. If the fringe result is a vector quantity, select the scalar quantity (Magnitude, X component, Y component, or Z component) to be derived for the fringe. 1. Click on Apply.

Vector Output Definitions Thermal vector results include temperature gradients and heat fluxes for conduction elements. Their result quantities are as follows: Result Quantity

Temperature Gradients 2

2

2 1/2

Heat Fluxes

Magnitude

{(dT/dx) + (dT/dy) + (dT/dz) }

X Component

dT/dx

{ qx + qy2 + qz2 } 1/2 qx = -k dT/dx

Y Component

dT/dy

qy = -k dT/dy

Z Component

dT/dz

qz = -k dT/dz

2

The sign convention for heat flow is as follows. Positive heat flow takes place as energy is transferred from a region of high relative temperature to a region of low relative temperature. Similarly, heat flux into the surface of a body is a positive quantity.

Main Index

145

146

Patran Interface to MSC Nastran Thermal Results Visualization Options

For example, T=100.

K = Constant

T=0

L=10. T=100. y

1

2

X=4.

X=6.

T=60. T=40. x T=0. X=0.

X=L=10.

T2 – T1 dT = -------------------– 60.- = – 2. -------------= 40. -------------------(Negative Gradient) dx 1 – 2 X2 – X1 6. – 4. qx

dT = = – k -----------dx 1 – 2 1–2

2⋅k

(Positive Flux)

XY Plots In transient thermal analysis, XY plotting is frequently applied to track the temperature-time history of grid points. You select this capability from the Results application using the Graph object. You can also use the Fringe object and the Report object for advanced features of contour plots and text report generation.

Main Index

Chapter 5: Results Processing and Visualization Results Visualization Options

Turns the Abbreviate Subcases toggle OFF if more than one subcase exists for a Result Case.

Parameter Method

Main Index

Description Toggles the form to select the result case(s) from the first list box. This is the default form for the Graph object.

147

148

Patran Interface to MSC Nastran Thermal Results Visualization Options

Select Results Cases

Selects result cases for results postprocessing. NOTE: If nothing appears in this listbox, then the results are not successfully loaded into the database. Go back to the Analysis menu or pull down File Import to read in analysis results.

Y: Result

Selects the Y-axis value.

Select Y Results

Lists result types for each selected load case. This listbox is used to select a result for postprocessing.

Position

Selects the layer if more than one layer is associated with the result.

X: Global Variable

Selects the X-axis value.

Variable

Selects a Global Variable.

The Target Entities form shown below is used to select target entities

Main Index

Chapter 5: Results Processing and Visualization Results Visualization Options

Parameter

Main Index

Description

Toggle Entity

Toggles the form to select the entities for which you wish to create an XY plot.

Target Entity

Selects entity type.

Select Nodes

Select (pick or type) entities.

149

150

Patran Interface to MSC Nastran Thermal Results Visualization Options

To create a fundamental XY plot of temperature versus time:

STEP 1: Select Graph object. STEP 4: Press the Target Entities icon to toggle the form to select target entities.

STEP 2: For XY Plotting, we need a series of results data, such as the temperature results over a period of time from a transient analysis. You can select the result cases with a mouse click and drag over the time states of interest.

STEP 3: Choose Temperatures from the Select Y Result listbox.

Main Index

Chapter 5: Results Processing and Visualization Results Visualization Options

STEP 5: Select Nodes as the target entity. STEP 6: Select (pick or type) Node IDs.

STEP 7: Click on Apply to create an XY plot.

Main Index

151

152

Patran Interface to MSC Nastran Thermal Results Visualization Options

Delete an XY Window

STEP 2: Select the Delete option.

STEP 3: Select the desired window(s) to delete from the XYWindow List listbox.

STEP 4: Click on Apply.

Main Index

Chapter 6: Read Input File MSC Nastran Implicit Nonlinear (SOL 600) User’s GuidePatran Interface to MSC Nastran Thermal

6

Main Index

Read Input File



Review of Read Input File Form



Data Translated from the NASTRAN Input File



Conflict Resolution

162

154 162

154

Patran Interface to MSC Nastran Thermal Review of Read Input File Form

Review of Read Input File Form The Analysis form will appear when the Analysis toggle, located on the Patran main menu, is chosen.

Read Input File as the selected Action on the Analysis form allows much of the model data from a NASTRAN input file to be translated into the Patran database. A subordinate File Selection form allows the user to specify the NASTRAN input file to translate. This form is described on the following pages.

Main Index

Chapter 6: Read Input File Review of Read Input File Form

Read Input File Form This form appears when the Analysis toggle is selected on the main menu. Read Input File, as the selected Action, specifies that model data is to be translated from the specified NASTRAN input file into the Patran database.

Parameter Code: Nastran Type: Thermal

Main Index

Description Indicates the selected Analysis Code and Analysis Type, as defined in the Preferences>Analysis (p. 388) in the Patran Reference Manual.

155

156

Patran Interface to MSC Nastran Thermal Review of Read Input File Form

Main Index

Available Jobs

List of already existing jobs.

Job Name

Name assigned to current translation job. This job name will be used as the base file name for the message file.

Entity Selection

Activates a subordinate Entity Selection form which allows the user to specify the specific entry types to be read. Also defines ID offset values to be used during import.

Select Input File

Activates a subordinate File Select form which allows the user to specify the NASTRAN input file to be translated.

Chapter 6: Read Input File Review of Read Input File Form

Entity Selection Form This subordinate form appears when the Entity Selection button is selected on the Analysis form and Read Input File is the selected Action. It allows the user to specify which MSC Nastran entity types to import.

Parameter

Main Index

Description

Entity Packets

Highlighted entity types will be imported.

Define Offsets

Activates the form to define ID offsets.

157

158

Patran Interface to MSC Nastran Thermal Review of Read Input File Form

The following table shows the relation between the entity types listed above and the actual MSC Nastran entry types effected. If an entity type is filtered out, it is treated as if those entries did not exist in the original input file. Entity Type

MSC Nastran Entries

Nodes

GRID, GRDSET, SPOINT

Elements

BAROR, BEAMOR, CBAR, CBEAM, CBEND, CDAMP1, CDAMP2, CDAMP3, CDAMP4, CELAS1, CELAS2, CELAS3, CELAS4, CGAP, CHEXA, CMASS1, CMASS2, CMASS3, CMASS4, CONM1, CONM2, CONROD, CPENTA, CQUAD4, CQUAD8, CQUADR, CROD, CSHEAR, CTETRA, CTRIA3, CTRIA6, CTRIAR, CTRIAX6, CTUBE, CVISC, PLOTEL

Material Properties

MAT1, MAT2, MAT3, MAT8, MAT9

Element Properties

PBAR, PBCOMP, PBEAM, PBEND, PCOMP, PDAMP, PELAS, PGAP, PMASS, PROD, PSHEAR, PSHELL, PSOLID, PTUBE, PVISC

Coordinate Frames

CORD1C, CORD1R, CORD1S, CORD2C, CORD2R, CORD2S

Load Sets

FORCE, GRAV,MOMENT, PLOAD1, PLOAD2, PLOAD4, PLOADX1, RFORCE, TEMP, TEMPP1, TEMPRB, SPC, SPC1, SPCD

Subcases

LOAD, SPCADD, Case Control Section

MPC Data

MPC, RBAR, RBE1, RBE2, RBE3, RROD, RSPLINE, RTRPLT

It should be noted that since the GRID entry is controlled with the Nodes filter, the grid.ps load set with the permanent single point constraint data will also be controlled by the Nodes filter.

Main Index

Chapter 6: Read Input File Review of Read Input File Form

Define Offsets Form This subordinate form appears when the Define Offsets button is selected on the Entity Selection form. It allows the user to specify the ID offsets used when reading a NASTRAN input file.

Parameter

Description

Automatic Offset

If selected, the value in the Maximum column will be used as the offset for the selected rows.

Existing ID Range in Db

Minimum and Maximum IDs currently found in the Patran database.

New ID

ID offset value to be used during import. The new ID value will be the ID found in the NASTRAN input file plus this offset value.

Maximum/Offset

All offset data boxes can be selected at once by selecting this column header.

All references made in the input file will also be offset. If a node references a particular CID as its analysis frame, then the reference will be offset as well. If the coordinate frame is defined in the same input file, the proper references should be maintained. The preference will be properly maintained. If the coordinate frame

Main Index

159

160

Patran Interface to MSC Nastran Thermal Review of Read Input File Form

existed in the file prior to the import, then it needs to be the offset CID. If a coordinate frame with that CID is not found in the database, an error message will be issued. To determine which offset effects a particular MSC Nastran entry type, refer to the table in the previous section. For Patran entities identified by integer IDs (nodes, elements, coordinate frames, and MPCs), the offset value is simply added to the MSC Nastran ID to generate the Patran ID. For Patran entities identified by text names (materials, element properties, load sets, and load cases), the offset value is first added to the MSC Nastran ID. The new integer value is then used to generate the Patran name per the naming conventions described in later sections.

Selection of Input File This subordinate form appears when the Select Input File button is selected on the Analysis form and Read Input File is the selected Action. It allows the user to specify which NASTRAN input file to translate.

Main Index

Chapter 6: Read Input File Review of Read Input File Form

Summary Data Form This form appears after the import of the NASTRAN input file has completed. It displays the number of entities imported correctly, imported with warnings, or not imported due to errors. These figures reflect the number of Patran entities created. In some cases, there is not a one-to-one relation between the original MSC Nastran entities and the generated Patran entities. For example, when material orientations on several CQUAD4s are defined using references to varying MCIDs while still referencing the same PID, Patran needs to create a unique property set for each different MCID reference. When the OK button is selected, the newly imported data will be committed to the Patran database, and can not be undone. If there is any question as to whether or not this import was desired, review the graphics data prior to selecting OK on this form. If the import was not correct, select the undo button on the main menu bar before selecting OK on this form.

Reject Card Form During import of the NASTRAN input file, some entriess types might not be understood by Patran. Those entries are brought into Patran in the direct text input data boxes. Selecting the Reject Entries button on the Summary Data form will bring up this Reject Card Form. You can review these entries here

Main Index

161

162

Patran Interface to MSC Nastran Thermal Data Translated from the NASTRAN Input File

.

Only card types not supported by Patran are sent to the reject card blocks. (This includes comments.) Entries which are otherwise recognized, but can not be imported due to syntax or invalid data errors are not sent to the reject blocks.

Data Translated from the NASTRAN Input File For more information about which specific MSC Nastran entry types can currently be read into Patran, see Data Translated from the NASTRAN Input File (p. 594) in the Patran Interface to MSC Nastran Preference Guide.

Conflict Resolution If an entity can not be imported into Patran because another entity already exists with that ID or name, then the conflict resolution logic is used. For more information, see Conflict Resolution (p. 606) in the Patran Interface to MSC Nastran Preference Guide.

Main Index

Chapter 7: Example Problems MSC Nastran Implicit Nonlinear (SOL 600) User’s GuidePatran Interface to MSC Nastran Thermal

7

Example Problems



Overview



Example 1 - Transient Thermal Analysis



Example 2 - Free Convection on Printed Circuit Board



Example 3 - Forced Air Convection on Printed Circuit Board



Example 4 - Thermal Contact Resistance



Example 5 - Typical Avionics Flow

232



Example 6 - Radiation Enclosures

253



Example 7 - Axisymmetric Flow in a Pipe



Example 8 - Directional Heat Loads



Example 9 - Thermal Stress Analysis from Directional Heat Loads



Example 10 - Thermal Stress Analysis of a Bi-Metallic Plate

163 164 190 203

222

263

279 291

299

Overview This chapter provides ten examples that illustrate popular capabilities in Patran’s interface to the MSC Nastran thermal solver. The first example, which describes transient thermal analysis, is an extension of the steady state modeling exercise given in Getting Started - A Guided Exercise (Ch. 2). This example contains stepby-step descriptions of the menu picks involved in the modeling process.

Main Index

164

Patran Interface to MSC Nastran Thermal Example 1 - Transient Thermal Analysis

Examples 2 through 10 are in easy to follow tutorial format. The actual menu structures are not shown since the expectation is for the user to follow along interactively with the Patran modeling system. The session files of the example problems described in this chapter are delivered with the software. To run an example problem: 1. Start Patran by entering the command p3. 1. From Patran’s main form, pull down the File menu and select Session -- Play. A Play Session File form will appear. 1. Select nastherm_exn.ses from the Session File List listbox. 1. Click on Apply. Patran will execute the modeling process and show you how to build the model.

Example 1 - Transient Thermal Analysis Objectives The objectives of this exercise are as follows:

Main Index



Open the database created in Getting Started - A Guided Exercise (Ch. 2).



Define time dependent functions using the Field application.



Create a transient load case. Add two existing load sets (temperature and convection boundary conditions) to this transient load case.



Apply time varying heat flux to the right edge of the plate.



Apply a transient volumetric heat generation inside the shaded area of the plate.



Select solution type as transient analysis.



Specify the default initial temperature.



Define time steps.



Select a transient load case.



Perform a transient thermal analysis using MSC Nastran within the Patran system.

Chapter 7: Example Problems Example 1 - Transient Thermal Analysis



Postprocess the transient results (Contour and XY plots). 0.4 m 1m

Aluminum Plate k = 204 W/m-oC Cp = 896 J/kg-oC

ρ = 2707 kg/m3 h = 10.0 W/m2-oC

3m

o

Tamb = 20.0 C

q = qvol(t) W/m3

q = qflux(t) W/m2

Thickness = 0.1 m T0 = 50 oC

T = 50 oC

Main Index

165

166

Patran Interface to MSC Nastran Thermal Example 1 - Transient Thermal Analysis

Open the Database Created in Chapter 2

STEP 1: From Patran’s main form, pull down the File menu and select Open. A form will appear called Open Database.

STEP 2: Within the Database List listbox, highlight plate.db. The database name will appear inside the Existing Database Name databox.

STEP 3: Click on OK.

Define Time Dependent Functions Before applying time varying loads and boundary conditions, we need to define time dependent functions using the Field application. In this model, two time fields are defined, one for applied heat flux and one for volumetric heat generation.

Main Index

Chapter 7: Example Problems Example 1 - Transient Thermal Analysis

Click on the Fields application. The Fields form will appear.

STEP 1: Toggle the Object setting to Non Spatial.

STEP 2: Click inside the Field Name databox and type in flux_time.

STEP 3: Click on the Input Data button.

Main Index

167

168

Patran Interface to MSC Nastran Thermal Example 1 - Transient Thermal Analysis

STEP 4: Fill in the table with the following values using the RETURN or ENTER key.

Time

Value

0

1 1.25 1.75 2 2

10 30 50 100

STEP 5: Click on OK. You must also click on APPLY located on the Fields form.

Main Index

Chapter 7: Example Problems Example 1 - Transient Thermal Analysis

Similarly, a time dependent function for volumetric heating is defined as follows.

STEP 6: Click inside the Field Name databox and type in qvol_time.

STEP 7: Click on the Input Data button. Fill in the table with the following values using the RETURN or ENTER key.

Time

Value

0

10000 12000 13000 14000 14000

10 30 50 100

STEP 8: Click on OK. You must also click on APPLY located on the Fields form.

Main Index

169

170

Patran Interface to MSC Nastran Thermal Example 1 - Transient Thermal Analysis

Create a Transient Load Case Our next task is to create a transient load case. Click on the Load Cases application. The Load Cases form will appear.

STEP 1: Click inside the Load Case Name databox. Type in the name transient. STEP 2: Toggle the Load Case Type setting to Time Dependent. Since the temperature and convection boundary conditions are not changed from the Getting Started example, we can associate these two load sets with the new load case directly.

STEP 3: Click Input Data.

Main Index

Chapter 7: Example Problems Example 1 - Transient Thermal Analysis

STEP 4: Highlight Conve_conv and Temp_tempbc within the Assigned Load/BCs Sets listbox.

STEP 5: Click Apply on the Load Cases form.

Main Index

171

172

Patran Interface to MSC Nastran Thermal Example 1 - Transient Thermal Analysis

Apply Time Varying Heat Flux to the Plate’s Right Edge At this point, we will impose a transient flux load on the plate’s right edge. The magnitude of this flux load is 5000 W/m2 multiplied by the time dependent function flux_time defined earlier under the Fields application. Click on the Loads/BCs application.

STEP 1: Change the settings to: Action:Create Object:Applied Heat Method:Element Uniform Option:Normal Fluxes

STEP 2: Click inside the New Set Name databox. Type in the name tran_flux. STEP 3: Toggle the Target Element Type setting to 2D.

STEP 4: Click on the Input Data button. The Input Data form will appear.

Main Index

Chapter 7: Example Problems Example 1 - Transient Thermal Analysis

Next, click on Select Application Region located on the Loads and Boundary Conditions form. We want to apply an internal heat generation inside a section of the plate from x=0.0 m to x=0.4 m. This application region will be selected by graphical cursor using the FEM geometry filter. STEP 7: Click on FEM under the Geometry Filter. Use the mouse cursor to drag a rectangle covering the elements located between x=0.0 m and x=0.4 m. Release the mouse cursor. The first two columns of the elements will turn red indicating the selection. Also, a list of elements will appear in the Select 2D Elements databox.

STEP 8: Click on Add.

STEP 9: Click on OK. Be sure to click on Apply located on the Load/Boundary Conditions form.

Note: A square yellow marker will appear on the center of the selected element indicating that a volumetric heating has been applied on this element.

Main Index

173

174

Patran Interface to MSC Nastran Thermal Example 1 - Transient Thermal Analysis

STEP 7: Click on the flux_time in the Time Dependent Fields listbox. The *Time Function databox will now appear as f:flux_time.

STEP 5: Toggle the Surface Option setting from Top to Edge.

STEP 6: Click inside the databox under Edge Heat Flux. Type in 5000.

STEP 8: Click on OK.

Next, click on Select Application Region located on the Loads and Boundary Conditions form.

Main Index

Chapter 7: Example Problems Example 1 - Transient Thermal Analysis

STEP 9: Icon choices will appear, Surface and Edge. Click on the icon, Curve or Edge.

STEP 10: Position the cursor over the right edge of the surface and click on this edge with the mouse. Patran will insert Surface 1.3 in the databox under the heading Select Surfaces or Edges. STEP 11: Click on Add.

STEP 12: Click on OK. Be sure to click on Apply located on the Load/Boundary Conditions form.

Note: A yellow marker will appear on the surface’s right edge indicating that a heat flux load has been applied along the right edge.

Apply Transient Volumetric Heat Generation Inside the Plate The volumetric heating can be applied in a similar way, using the Loads and Boundary Conditions form as follows

Main Index

175

176

Patran Interface to MSC Nastran Thermal Example 1 - Transient Thermal Analysis

.

STEP 1: Change the settings to: Type:Element Uniform Option:Volumetric Generation

STEP 2: Click inside the New Set Name databox. Type in the name tran_qvol. STEP 3: Toggle the Target Element Type setting to 2D. STEP 4: Click on the Input Data button. The Input Data form will appear.

Main Index

Chapter 7: Example Problems Example 1 - Transient Thermal Analysis

STEP 5: Click on the qvol_time in the Time Dependent Fields listbox. The *Time Function databox will now include f:qvol_time. Note: The scale factor of the volumetric heating will be set to 1.0 by default if no data is input in the Volumetric Heat Generation databox.

STEP 6: Click on OK.

Main Index

177

178

Patran Interface to MSC Nastran Thermal Example 1 - Transient Thermal Analysis

Main Index

Chapter 7: Example Problems Example 1 - Transient Thermal Analysis

Select Solution Type Now we are ready to set the analysis controls for transient thermal analysis. Click on the Analysis application. The Analysis form will appear.

STEP 1: Change the settings to: Action:Analyze Object:Entire Model Method:Full Run

STEP 2: Click inside the Job Name databox and change the job name to plate_tran. STEP 3: Click on Solution Type. The Solution Type form will appear.

STEP 4: Click on the TRANSIENT ANALYSIS.

STEP 5: Click on Solution Parameters to specify the default initial temperature.

Main Index

179

180

Patran Interface to MSC Nastran Thermal Example 1 - Transient Thermal Analysis

Specify the Default Initial Temperature For transient thermal analysis, we have to employ a starting temperature from which the solution evolves. If the initial temperature distribution is uniform, a default initial temperature is sufficient to specify the initial state. Otherwise, the Initial Temperature object in Loads and BCs application must be used to define initial nodal temperatures explicitly. See Initial Temperature, 70 for information.

STEP 1: Click inside the Default Init Temperature databox and change the value to 50.0.

STEP 2: Click on OK. Be sure to click on OK located on the Solution Type form.

Define Time Steps We must now create a subcase. Click on Subcase Create located on the Analysis form. The Subcase Create form will appear

Main Index

Chapter 7: Example Problems Example 1 - Transient Thermal Analysis

. STEP 1: Within the Available Subcase listbox, highlight transient. The word transient will appear inside the Subcase Name databox. STEP 2: Click on the Subcase Parameters button. The Subcase Parameters form will appear. STEP 3: Change the Initial Time Step to 10. Make sure the Number of Time Steps settings is 100. Thus, the total analysis time is 1000 seconds.

STEP 4: Click on OK. Click on APPLY.

Main Index

181

182

Patran Interface to MSC Nastran Thermal Example 1 - Transient Thermal Analysis

Select a Transient Load Case Our last task on specifying analysis controls is to select the load case for the analysis. Click on Subcase Select located on the Analysis form. The Subcase Select form will appear.

STEP 1: Click on transient within the Subcases for Solution Sequence: 159 listbox. The word transient will appear inside the Subcases Selected listbox.

STEP 2: Click on Default in the Subcases Selected listbox to remove the load case Default.

STEP 3:Click on OK.

Perform a Transient Thermal Analysis To submit the job for MSC Nastran thermal analysis, simply click on the Apply button on the Analysis form. It will take a while for the MSC Nastran solver to perform a transient thermal analysis in the background. When the analysis is completed, the model is ready for result processing.

Main Index

Chapter 7: Example Problems Example 1 - Transient Thermal Analysis

Read the Analysis Results into Database

STEP 1: Change the settings to: Action:Read Output2 Object:Result Entities Method:Translate

STEP 2: Make sure that the Job Name setting is plate_tran.

STEP 3: Click on the Select Results File button and double click on the file called plate_tran.op2.

STEP 4: Click on Apply.

Note: The heartbeat will change to the color blue, indicating that reading process is underway. When the heartbeat turns green again, the results are ready for postprocess.

Visualize the Transient Results (Contour Plot)

Main Index

183

184

Patran Interface to MSC Nastran Thermal Example 1 - Transient Thermal Analysis

We will create a contour plot of temperature distributions at time=700 sec using the Results Display form.

STEP 1: Scroll down the vertical scroll bar of the Select Results Cases listbox, and click on transient, Time=700.

STEP 2: Within the Select Fringe Result listbox, highlight Temperatures.

STEP 3: Click on Apply.

Main Index

Chapter 7: Example Problems Example 1 - Transient Thermal Analysis

Visualize the Transient Results (XY Plot) Now we will apply XY plotting to visualize the temperature-time history of Nodes 49 to 54.

STEP 1: Set the Object setting to Graph.

STEP 4: Press the Target Entities icon to toggle the form to select target entities.

STEP 2: In the Select Result Case(s) listbox, click and drag mouse to select the time states from transient, Time=0. to transient, Time=1020.

STEP 3: Within the Select Y Result listbox, highlight Temperatures.

Main Index

185

186

Patran Interface to MSC Nastran Thermal Example 1 - Transient Thermal Analysis

STEP 5: Select Nodes as the target entity. STEP 6: Click inside the Select Nodes databox. Use the mouse cursor to drag a rectangle covering nodes 49 to 54. A list of nodes, Node 49:54, will appear in the Node IDs databox.

STEP 7: Click on Apply to create an XY plot.

Main Index

Chapter 7: Example Problems Example 1 - Transient Thermal Analysis

Modify the XY Plot At this point, we will modify the Y scale of the XY plot and display grid lines in the Y direction by clicking on the XY Plot application.

STEP 1: Change the settings to: Action:Modify Object:Axis

STEP 2: Toggle the Active Axis setting to Y. STEP 3: Click on Scale. The Axis Scale form will appear.

Main Index

187

188

Patran Interface to MSC Nastran Thermal Example 1 - Transient Thermal Analysis

STEP 4: Toggle the Assignment Method to Range.

STEP 5: Change the data under Enter Lower and Upper Values to 45 70. STEP 6: Change the data under Number of Primary Tick Marks to 6.

STEP 8: Click on Cancel.

STEP 7: Click on Apply.

Main Index

Chapter 7: Example Problems Example 1 - Transient Thermal Analysis

Next, you must click on Grid Lines located on the XY Plot form. The Grid Lines form will appear.

STEP 9: Click on Primary under the Display selection.

STEP 10: Click on Apply.

Main Index

189

190

Patran Interface to MSC Nastran Thermal Example 2 - Free Convection on Printed Circuit Board

Example 2 - Free Convection on Printed Circuit Board Y 9.0 in 1.0 in 1.0 in

1.0 in

6.0 in 1.0 in 4.0 in

1.5 in

1.0 in 2.0 in 1.0 in

1.0 in X

4.0 in 5.5 in

q = 5.0 W/in2

Kpcb = 0.066 W/in-oC Kchip = 2.24 W/in-oC

0.25 in 0.1 in h = 0.02 W/in2-oC Tamb = 20.0 oC

Figure 7-1 Printed Circuit Board Assembly

Problem Description Figure 7-1 depicts a printed circuit board (PCB) assembly which has three significant chip devices mounted

on it. Each chip is generating heat at a rate that is consistent with the application of a heat flux of 5.0 W/in2 over each device surface area. Heat is dissipated by thermal conduction within the chips and underlying board. Free convection to the ambient environment provides the ultimate heat sink. The ambient temperature for convection is assumed to be 20.0 oC, and a heat transfer coefficient of 0.02 W/in2-oC is used to apply convection to the entire assembly surface. We will analyze the printed circuit board to determine the device temperatures so that they can be compared to manufacturer allowables.

Main Index

Chapter 7: Example Problems Example 2 - Free Convection on Printed Circuit Board

Modeling This example demonstrates the modeling of a printed circuit board with multiple components. We will create surfaces for PCB and electronic devices, extrude the surfaces to generate 3D solids, specify properties, apply thermal loads and boundary conditions, and then perform a steady-state analysis.

Main Index

191

192

Patran Interface to MSC Nastran Thermal Example 2 - Free Convection on Printed Circuit Board

Create the Surfaces of Printed Circuit Board and Electronic Components

Main Index

Chapter 7: Example Problems Example 2 - Free Convection on Printed Circuit Board

Table 7-1

u Geometry

PCB Action:

Create

Object:

Surface

Method:

XYZ

Table 7-2 Surface ID List

1

Vector Coordinates List

Origin Coordinates List

[000]

-Apply-

Chip 1 Surface ID List

2

Vector Coordinates List

< 1 1.5 0 >

Origin Coordinates List

[110]

-Apply-

Chip 2 Surface ID List

3

Vector Coordinates List

Origin Coordinates List

[440]

-Apply-

Chip 3 Surface ID List

4

Vector Coordinates List

Origin Coordinates List

[ 5.5 2 0 ]

-Apply-

Main Index

193

194

Patran Interface to MSC Nastran Thermal Example 2 - Free Convection on Printed Circuit Board

Extrude the Surfaces to Create Solids Create the PCB solid by extruding surface 1 by -0.1 inch in the Z direction. Extrude surfaces 2,3 and 4 in the Z direction by 0.25 inches. Table 7-3

u Geometry

PCB Action:

Create

Object:

Solid

Method:

Extrude

Table 7-4 Solid ID List

1

Translation Vector

< 0 0 -0.1 > If the Auto Execute is ON, you do not need to click on -Apply-

Auto Execute Surface List

Surface 1 -Apply-

Chips 1, 2, 3 Solid ID List

2

Translation Vector

Surface List

Surface 2:4 -Apply-

Main Index

You can use the Auto Execute instead of clicking on -Apply-

Chapter 7: Example Problems Example 2 - Free Convection on Printed Circuit Board

Mesh the Solids You will now create the model’s finite elements. Table 7-5

uFinite Elements

Action:

Create

Object:

Mesh

Type:

Solid

Global Edge Length

0.25

Element Topology

Hex8

Solid List

Solid 1:4

Highlight

-ApplyTo obtain a clearer view, select the isometric view by clicking on the Iso 1 View icon

Main Index

195

196

Patran Interface to MSC Nastran Thermal Example 2 - Free Convection on Printed Circuit Board

Specify Materials For this model we will assume that the PCB and chips are manufactured from isotropic materials having constant conductivities: Kpcb = 0.066 W/in-oCKchip = 2.24 W/in-oC PCB

u Materials Action:

Create

Object:

Isotropic

Method:

Manual Input

Table 7-6 Material Name

pcb

Input Properties... Thermal Conductivity =

0.066

-ApplyChips 1, 2, 3

u Materials Action:

Create

Object:

Isotropic

Method:

Manual Input

Table 7-7 Material Name

chip

Thermal Conductivity =

2.24

-Apply-

Main Index

Since we are preforming a steadystate analysis, specific heat and density are not required.

Chapter 7: Example Problems Example 2 - Free Convection on Printed Circuit Board

Main Index

197

198

Patran Interface to MSC Nastran Thermal Example 2 - Free Convection on Printed Circuit Board

Define Element Properties For a solid model element properties are used to assign the materials to the various parts of the model. PCB

u Properties Action:

Create

Dimension:

3D

Type:

Solid

Table 7-8 Property Set Name

pcb

Input Properties... Material Name

m:pcb

Select from Material Property Sets

OK Select Members

Solid 1 Add -Apply-

Chips 1, 2, 3 Property Set Name

chip

Input Properties... Material Name

m:chip

Select from Material Property Sets

OK Select Members

Solid 2:4 Add -Apply-

To verify that the correct material properties have been defined and assigned to the correct model locations, c the Action option to Show and create a scalar plot of the model’s materials. Table 7-9

u Properties

Action:

Show

Table 7-10 Select Property

Material Name

Display Method

Scalar Plot

Select Groups

uCurrent Viewport default group -Apply-

Main Index

Highlight

Highlight

Chapter 7: Example Problems Example 2 - Free Convection on Printed Circuit Board

Merge the Common Nodes The duplicate nodes located at the PCB and chip interfaces must be merged. Merging establishes and simulates the physical connection between the PCB and chip components. In Patran equivalencing the model performs node merging.

u Finite Elements Action:

Equivalence

Object:

All

Method:

Tolerance Cube

Table 7-11 Equivalencing Tolerance

0.005

-Apply-

Verify the Free Edges To check the equivalence process you should verify the element boundaries. If the model has been equivalenced properly you should see a wireframe rendering of your model where only the free edges are components of the wireframe image. Display the view to ensure that the model has no cracks between elements.

u Finite Elements Action:

Verify

Object:

Element

Test:

Boundaries

Table 7-12 Display Type -Apply-

Main Index

uFree1 Edges

199

200

Patran Interface to MSC Nastran Thermal Example 2 - Free Convection on Printed Circuit Board

Apply a Head Load on Each Device A heat flux will now be applied to the exposed plan form face of the chips.

u Load/Boundary Conditions Action:

Create

Object:

Applied Heat

Type:

Element Uniform

Table 7-13 Option:

Normal Fluxes

New Set Name

flux

Target Element Type:

3D

Input Data... Heat Flux

5 OK

Select Application Region Geometry Filter

uGeometry

Select Solid Faces

Solid 2.6 3.6 4.6

Or select with mouse using the Select icon. Use the Free Face Select icon to help you pick the exposed chip faces.

Add OK -Apply-

Main Index

Chapter 7: Example Problems Example 2 - Free Convection on Printed Circuit Board

Apply a Convection Boundary Condition on the PCB . The convection boundary condition will now be applied to the back side of the PCB (side opposite the chips). Table 7-14

u Load/Boundary Conditions

Action:

Create

Object:

Convection

Type:

Element Uniform

Table 7-15 Option:

To Ambient

New Set Name

conv

Target Element Type:

3D

Input Data... Convection Coefficient

0.02

Ambient Temperature

20

OK Select Application Region Geometry Filter

uGeometry

Select Solid Faces

Solid 1.6

Or select with mouse using the Select icon. Use the Free Face Select icon to help you pick the back face of the PCB.

Add OK -Apply-

Main Index

201

202

Patran Interface to MSC Nastran Thermal Example 2 - Free Convection on Printed Circuit Board

Perform the Analysis

Table 7-16

u Analysis

Action:

Analyze

Object:

Entire Model

Method:

Full Run

Table 7-17 Job Name

ex2

Solution Type...

u STEADY STATE ANALYSIS

Solution Type:

OK -Apply-

Read in the Analysis Results

Table 7-18

u Analysis

Action:

Read Output2

Object:

Result Entities

Method:

Translate

Table 7-19 Job Name

ex2

Select Results File... ex2.op2 OK -Apply-

Main Index

Highlight

Chapter 7: Example Problems Example 3 - Forced Air Convection on Printed Circuit Board

203

Display the Results

u Results Object:

Quick Plot

Table 7-20 Select Results Cases

Default, PW Linear: 100. % of Load

Highlight

Select Fringe Result

Temperatures

Highlight

-Apply-

Discussion of Results The heat generated by the electronic devices is conducted to the printed circuit board, and then spread on the ep glass PCB. The cooling mechanism is provided by a free convection heat exchange between the backside of th PCB and the ambient fluid that is maintained at 20 oC. As a result, the largest electronic device has the highe temperature. Because of their identical size, the other two electronic chips possess nearly the same temperatur distribution.

Example 3 - Forced Air Convection on Printed Circuit Board Figure 7-2 Z

q = 20.0 W/in2

X

. m=

8.33E-3 lbm/sec

Tin = 20.0 oC

Main Index

h = h(T) W/in2-oC

Air

9.0 in

X

204

Patran Interface to MSC Nastran Thermal Example 3 - Forced Air Convection on Printed Circuit Board

Problem Description This is an extension of the previous analysis (Example 2). The geometry is unchanged; however, the applied heat flux is increased to 20.0 W/in2. In place of free convection to an ambient environment, an advective flow will traverse the surface. The coolant stream travels in the X-direction with the inlet located at X=0 and the outlet positioned at X=L=9.0 inches. The mass flow rate is constant at any X location with a value of 0.5 lbm/min (8.33E-03 lbm/sec). The inlet temperature is set at 20 oC. Associated with the advection flow which transports energy streamwise, is the heat transfer that takes place between the fluid stream and the PCB. In this problem, energy passes from the PCB into the fluid stream. The convection behavior for this transport is specified with a temperature dependent heat transfer coefficient. In the absence of any film node specification, the look up temperature for this heat transfer coefficient defaults to the average temperature between the PCB surface element and its ambient points, in this case, the nodal points in the advected fluid stream.

Modeling We will model the previous PCB thermal analysis with forced air convection over the flat plate, using the Coupled Advection feature. The air temperature rises in the X direction as the fluid stream traverses the circuit board. The temperature dependency of the convection coefficient will be defined using a temperature dependent field.

Main Index

Chapter 7: Example Problems Example 3 - Forced Air Convection on Printed Circuit Board

Create the Geometry

Table 7-21

u Geometry

Action:

Create

Object:

Surface

Method:

XYZ

Table 7-22 Vector Coordinates List

Origin Coordinates List

[000]

-ApplyVector Coordinates List

< 1 1.5 0 >

Origin Coordinates List

[110]

-ApplyVector Coordinates List

Origin Coordinates List

[440]

-ApplyVector Coordinates List

Origin Coordinates List

[ 5.5 2 0 ]

-Apply-

Main Index

205

206

Patran Interface to MSC Nastran Thermal Example 3 - Forced Air Convection on Printed Circuit Board

Extrude the Solid

Table 7-23

u Geometry

Action:

Create

Object:

Solid

Method:

Extrude

Table 7-24 Translation Vector

< 0 0 -0.1> If the Auto Execute is ON, you do not need to click on -Apply-

Auto Execute Surface List

Surface 1 -Apply-

Translation Vector

< 0 0 0.25 >

Surface List

Surface 2:4 You can use the Auto Execute instead of clicking on -Apply-

-Apply-

Mesh the Solids

Table 7-25

uFinite Elements

Action:

Create

Object:

Mesh

Type:

Solid

Table 7-26 Global Edge Length

0.25

Element Topology

Hex8

Solid List

Solid 1:4 -Apply-

Main Index

Highlight

Chapter 7: Example Problems Example 3 - Forced Air Convection on Printed Circuit Board

Merge the Common Nodes

Table 7-27 Finite Elements Action:

Equivalence

Object:

All

Method:

Tolerance Cube

Table 7-28 Equivalencing Tolerance

0.005

-Apply-

Verify the Element Boundaries

Table 7-29

u Finite Elements

Action:

Verify

Object:

Element

Test:

Boundaries

Display Type

Free Edges

-Apply-

Main Index

207

208

Patran Interface to MSC Nastran Thermal Example 3 - Forced Air Convection on Printed Circuit Board

Specify Materials

Table 7-30 Materials Table 7-31 Action:

Create

Object:

Isotropic

Method:

Manual Input

Table 7-32 Material Name

chip

Input Properties... Constitutive Model:

Solid properties

Thermal Conductivity =

2.24

-ApplyMaterial Name

pcb

Constitutive Model:

Solid properties

Thermal Conductivity =

0.066

-Apply-

Main Index

Chapter 7: Example Problems Example 3 - Forced Air Convection on Printed Circuit Board

Define Element Properties

Table 7-33 Properties Action:

Create

Dimension:

3D

Type:

Solid

Table 7-34 Property Set Name

chip

Input Properties... Material Name

m:chip

Select from Material Property Sets

OK Select Members

Solid 2:4 Add -Apply-

Property Set Name

pcb

Input Properties... Material Name

m:pcb OK

Select Members

Solid 1 Add -Apply-

Main Index

Select from Material Property Sets

209

210

Patran Interface to MSC Nastran Thermal Example 3 - Forced Air Convection on Printed Circuit Board

Define Temperature Dependent Field

Table 7-35 Fields Action:

Create

Object:

Material Property

Method:

Tabular Input

Table 7-36 Field Name

conv_temp

Active Independent Variables

Temperature (T)

Input Data... Input Scalar Data

Hit Enter Key T 0 100 200

OK -Apply-

Main Index

Value 0.2 0.3 0.35

Chapter 7: Example Problems Example 3 - Forced Air Convection on Printed Circuit Board

Select Two Nodes to Create a Curve

Table 7-37

u Geometry

Action:

Create

Object:

Curve

Method:

Point With the mouse select the Node icon. Click on the nodes located at the center of the left edge and the center of the right edge.

Starting Point List

Node 938

Ending Point List

Node 1838

-Apply-

Define the Location of the Air Stream

Table 7-38

u Geometry

Action:

Transform

Object:

Curve

Method:

Translate

Table 7-39 Translation Vector

< 0 0 -1.0 >

Curve List

Curve 1 -Apply-

Main Index

211

212

Patran Interface to MSC Nastran Thermal Example 3 - Forced Air Convection on Printed Circuit Board

Mesh the Air Stream Preferably, the mesh size should be the same on the air stream as on the PCB. Table 7-40

u Finite Elements

Action:

Create

Object:

Mesh

Type:

Curve

Table 7-41 Global Edge Length

.25

Element Topology

Bar2

Highlight

Curve List

Curve 2

Curve 2 was the result of translating Curve 1

-ApplyNote: The identical mesh size is not required, but may provide the most accurate model. The Closest Approach method will select the nearest neighboring structure and fluid nodes.

Main Index

Chapter 7: Example Problems Example 3 - Forced Air Convection on Printed Circuit Board

Specify the Materials Properties of Air

Table 7-42

u Materials

Action:

Create

Object:

Isotropic

Method:

Manual Input

Table 7-43 Material Name

air

Input Properties... Constitutive Model: Thermal Conductivity =

6.66e-4

Specific Heat =

456.2

Density =

5.01e-5

Dynamic Viscosity =

1.03e-6

-Apply-

Main Index

Fluid properties

213

214

Patran Interface to MSC Nastran Thermal Example 3 - Forced Air Convection on Printed Circuit Board

Define Flow Tube Properties

Table 7-44

u Properties

Action:

Create

Dimension:

1D

Type:

Flow Tube

Table 7-45 Property Set Name

flow_tube

Input Properties... Material Name

m:air

Diameter at Node 1

1.0 OK

Select Members

Curve 2 Add -Apply-

Main Index

Select from Material Property Sets

Chapter 7: Example Problems Example 3 - Forced Air Convection on Printed Circuit Board

Main Index

215

216

Patran Interface to MSC Nastran Thermal Example 3 - Forced Air Convection on Printed Circuit Board

Apply Forced Air Convection We will use the Coupled Advection feature to simulate the forced air convection on the back surface of PCB. Table 7-46

u Load/Boundary Conditions

Action:

Create

Object:

Convection

Type:

Element Uniform

Table 7-47 Option: New Set Name

Coupled Advection flow_by_plate

There are two application regions: 

The Structure Region (Application Region 1) can be 1D, 2D, or 3D. In this case we have a 3D structure, and the appropriate Target Element Type is 3D.



The Second Application Region must be 1D, which represents the airflow over the flat plate. In this case, select the curve along the X direction. Patran will then couple the fluid to the structure locally by the Closest Approach method.

Target Element Type:

3D

Region 2:

1D Input Data...

*Temperature Function

f:conv_temp

Mass Flow Rate

8.33e-3

Select from Temperature Dependent Fields

OK Select Application Region Geometry Filter

uGeometry

Select Solid Faces

Solid 1.6 Add For the Companion Region (the second one)

Active List Select Curves

Curve 2 Add OK -Apply-

Main Index

Highlight

Chapter 7: Example Problems Example 3 - Forced Air Convection on Printed Circuit Board

Apply a Heat Flux on Each Device

Table 7-48

u Load/Boundary Conditions

Action:

Create

Object:

Applied Heat

Type:

Element Uniform

Table 7-49 Option:

Normal Fluxes

New Set Name

heat_flux

Target Element Type:

3D

Input Data... Heat Flux

20 OK

Select Application Region Geometry Filter

uGeometry

Select Solid Faces:

Solid 2.6 3.6 4.6 Add OK

-Apply-

Main Index

With the mouse select the top surfaces of the threechips

217

218

Patran Interface to MSC Nastran Thermal Example 3 - Forced Air Convection on Printed Circuit Board

Define the Inlet Temperature of the Fluid

Table 7-50

u Load/Boundary Conditions

Action:

Create

Object:

Temp (Thermal)

Type:

Nodal

Table 7-51 New Set Name

inlet_temp

Input Data... Boundary Temperature

20

OK Select Application Region Geometry Filter

uGeometry

Select Geometry Entities

Point 35

Add OK -Apply-

Main Index

Pick the initial point on the airstream curve

Chapter 7: Example Problems Example 3 - Forced Air Convection on Printed Circuit Board

Define the Default Initial Temperature and Perform the Analysis

Table 7-52

u Analysis

Action:

Analyze

Object:

Entire Model

Method:

Full Run

Table 7-53 Job Name

ex3

Solution Type... Solution Parameters... Data Deck Echo:

Sorted

Examine the input data in the F06 file

Default Init Temperature

100

Define the default initial temperature

OK OK -Apply-

Main Index

219

220

Patran Interface to MSC Nastran Thermal Example 3 - Forced Air Convection on Printed Circuit Board

Read in the Analysis Results

Table 7-54

u Analysis

Action:

Read Output2

Object:

Result Entities

Method:

Translate

Table 7-55 Job Name

ex3

Select Results File... ex3.op2 OK -Apply-

Main Index

Highlight

Chapter 7: Example Problems Example 3 - Forced Air Convection on Printed Circuit Board

Display the Results

Table 7-56

u Results

Object:

Quick Plot

Table 7-57 Select Results Cases Select Fringe Result

Default, PW Linear: 100. % of Load Temperatures

Highlight Highlight

-Apply-

Discussion of Results With the advection flow attached to the printed circuit board’s back surface, the resulting temperature profile exhibits significantly different behavior than in the prior example where free convection provided the heat transfer mechanism between the printed circuit board and a surrounding fluid maintained at a constant temperature (20 oC). In this example, the attached flow receives energy as it moves downstream along the PCB. Since the inlet flow is maintained at 20 oC, the edge of the board which coincides with X=0 is the coolest and the trailing edge (X=L) is necessarily warmer. Similarly, the most distant device in a stream wise sense has the highest peak temperature.

Main Index

221

222

Patran Interface to MSC Nastran Thermal Example 4 - Thermal Contact Resistance

Example 4 - Thermal Contact Resistance Figure 7-3 Y

5.0 in

2.0 in

2.0 in 5.0 in Kpwb = 0.6 W/in-oC Kchip = 1.34 W/in-oC 2.0 in

X

2.0 in q = 10.0 W/in2

Z

Contact Coefficient = 1.2 W/in2-oC

0.25 in 0.5 in

X T = 20.0 oC

Problem Description The dimension of the chip is 2 x 2 inches with a thickness of 0.25 inches. The printed wiring board is 5 x 5 inches with a thickness of 0.5 inches.

Main Index

Chapter 7: Example Problems Example 4 - Thermal Contact Resistance

Thermal conductivity properties for the chip and wiring board are, respectively, 1.34 and 0.6 W/in-oC. A heat flux of 10 W/in2 is imposed on the top of the chip component. A thermal conductance value of 1.2 W/in2-oC is applied between the chip and the printed wiring board. The bottom of the printed wiring board is held at a constant temperature of 20 oC.

Modeling In this example we will model the contact resistance between two solids--in this case, the contact between an electronic component and a printed wiring board (PWB)--to determine the maximum temperature at the top of the chip and the temperature drop to the bottom of the wiring board. Creating the Geometry

Table 7-58

u Geometry

Action:

Create

Object:

Solid

Method:

XYZ

Table 7-59 Solid ID List

1

Vector Coordinates List

< 5 5 .5 >

Origin Coordinates List

[000]

-ApplySolid ID List

2

Vector Coordinates List

< 2 2 .25 >

Origin Coordinates List

[221]

-Apply-

Main Index

223

224

Patran Interface to MSC Nastran Thermal Example 4 - Thermal Contact Resistance

Mesh the Solids

Table 7-60

u Finite Elements

Action:

Create

Object:

Mesh

Type:

Solid

Table 7-61 Global Edge Length

0.25

Element Topology

Hex8

Solid List

Solid 1:2

Highlight

-ApplyTo obtain a clearer view, select the isometric view by clicking on the Iso 1 View icon.

Merge the Common Nodes

Table 7-62

u Finite Elements

Action:

Equivalence

Object:

All

Method:

Tolerance Cube

Table 7-63 Equivalencing Tolerance 0.005 -Apply-

Main Index

Chapter 7: Example Problems Example 4 - Thermal Contact Resistance

Specify Materials

Table 7-64

u Materials

Action:

Create

Object:

Isotropic

Method:

Manual Input

Table 7-65 Material Name

pwb

Input Properties... Constitutive Model: Thermal Conductivity

Solid properties 0.6

-ApplyMaterial Name

chip

Constitutive Model: Thermal Conductivity

-Apply-

Main Index

Solid properties 1.34

225

226

Patran Interface to MSC Nastran Thermal Example 4 - Thermal Contact Resistance

Define Element Properties

Table 7-66

u Properties

Action:

Create

Dimension:

3D

Type:

Solid

Table 7-67 Property Set Name

pwb

Input Properties... Material Name:

m:pwb

Select from Material Property Sets

OK Select Members

Solid 1 Add -Apply-

Property Set Name

chip

Input Properties... Material Name:

m:chip OK

Select Members

Solid 2 Add -Apply-

Main Index

Select from Material Property Sets

Chapter 7: Example Problems Example 4 - Thermal Contact Resistance

Apply Coupled Convection Contact resistance is modeled in Patran using the Convection-Coupled menu operation (select the bottom of the chip surface and the top of the printed wiring board to specify the thermal conductance between the two surfaces). This technique enables you to apply a connection through convection between two solid geometric faces without connecting the structures with finite elements. One advantage of this method is that mesh sizes between the two regions need not be congruent. Patran will automatically find the ambient points closest to the thermal contact area. (The same technique can be used to model thermal contacts directly from 2D to 1D geometric entities, or even from solid faces to nodal ambient points.) However, this convenience is not intended as a replacement for responsible modeling practices. Table 7-68

u Load/Boundary Conditions

Action:

Create

Object:

Convection

Type:

Element Uniform

Table 7-69 Option:

Coupled

New Set Name

coup_conv

Target Element Type:

3D

Region 2:

3D

Select the Coupled Option before defining the Element Uniform Type

Input Data... Convection Coefficient:

1.2

OK Select Application Region Geometry Filter

uGeometry

Select Solid Faces

Solid 2.5 Add For the Companion Region (the second one)

Active List Select Solid Faces

Solid 1.6 Add OK

-ApplyNote: Arrows should be pointing downward into the printed wiring board.

Main Index

227

228

Patran Interface to MSC Nastran Thermal Example 4 - Thermal Contact Resistance

Apply a Heat Flux on the Top Surface of the Chip

Table 7-70

u Load/Boundary Conditions

Action:

Create

Object:

Applied Heat

Type:

Element Uniform

Table 7-71 Option:

Normal Fluxes

New Set Name

heat_flux

Target Element Type:

3D

Input Data... Heat Flux

10 OK

Select Application Region Geometry Filter

uGeometry

Select Solid Faces

Solid 2.6

Or select with mouse using the Select icon Using the mouse, select the Free Face of a Solid icon

Add OK -Apply-

Main Index

Chapter 7: Example Problems Example 4 - Thermal Contact Resistance

Apply a Temperature Boundary Condition on the Back Side of the PWB

Table 7-72

u Load/Boundary Conditions

Action:

Create

Object:

Temp (Thermal)

Type:

Nodal

Table 7-73 New Set Name

tempbc

Input Data... Boundary Temperature

20

OK Select Application Region Geometry Filter

uGeometry

Select Geometry Entities

Solid 1.5

Or select with mouse using the Select icon Using the mouse, select the Surface or Face icon

Add OK -Apply-

Perform the Analysis

Main Index

229

230

Patran Interface to MSC Nastran Thermal Example 4 - Thermal Contact Resistance

Table 7-74

u Analysis

Action:

Analyze

Object:

Entire Model

Method:

Full Run

Table 7-75 Job Name

ex4

-Apply-

Read in the Analysis Results

Table 7-76

u Analysis

Action:

Read Output2

Object:

Result Entities

Method:

Translate

Table 7-77 Job Name

ex4

Select Results File... ex4.op2

Highlight

OK -Apply-

Display the Results

u Results Object:

Quick Plot

Table 7-78 Select Results Cases

Main Index

Default, PW Linear: 100. % of Load

Highlight

Chapter 7: Example Problems Example 4 - Thermal Contact Resistance

Select Fringe Result

Temperatures

Highlight

-Apply-

Discussion of Results Due to the simple geometry, a hand calculation can be performed to provide an estimate of the maximum temperature at the chip surface: Layer Resistance ≅ Thickness / ( K * A cross section) Contact Resistance ≅ 1 / ( h * A contact) Material Chip Thermal Contact PWB (5x5) PWB (2x2) Total Resistance

Thermal Resistance (C/Watt) 0.046642 0.208333 0.03333 0.208333 0.2883 < R < 0.4633

For a total heat load of 40 W, the maximum temperature can be estimated as: Q = ΔT / Total Resistance Then, Tmax = 20.0 + 40.0 * (Total Resistance) or 31.53 oC < Tmax < 38.53 oC The finite element calculation determined the maximum temperature as 36.51 oC, which is rational considering the hand calculation and the approximation inherent in that solution.

Main Index

231

232

Patran Interface to MSC Nastran Thermal Example 5 - Typical Avionics Flow

Example 5 - Typical Avionics Flow Figure 7-4 Y

X

Z

q = 20 W/in2

0.5 in

10.0 in 5.0 in

Aluminum Plate K = 4.0 W/in-oC

Tin = 20.0 oC

.

m=

DH = 0.5333 in

Air

0.8 in

8.333E-3 * 5 lbm/sec

0.4 in

0.5 in

h = 0.3 W/in2-oC 1.0 in

K = 6.66E-4 W/in-oC Cp = 456.2 J/lbm-oC

ρ = 5.01E-5 lbm/in3 μ = 1.03E-6 lbm/in-sec

Problem Description Forced air convection is a very efficient method of removing heat in a limited space. In electronic packaging, forced air convection is used to remove heat in a compact heat exchanger. Modeling this problem within the Patran MSC Nastran system requires building a structural model and a fluid model, and connecting them in an appropriate fashion. Patran can associate the structure nodes with the fluid nodes using a technique called the Closest Approach method. This method allows the analyst an option to specify non-coincident mesh sizes on the structure and the fluid nodes. However, it is recommended that you use an identical mesh size for a regular isoparametric rectangular mesh, as demonstrated in this example.

Modeling The compact heat exchanger dimensions are 0.5 inch high, 5.0 inches wide, and 10 inches long. The heat exchanger has a total of five rectangular ducts. Each duct has a dimension of 0.8 inch in width and 0.4 inch

Main Index

Chapter 7: Example Problems Example 5 - Typical Avionics Flow

233

in height. The inlet temperature of the fluid is at 20 oC. The power density is applied to one side of the heat sink at 20 W/in2. The mass flow rate per channel is 0.5 lbm/min (0.008333 lbm/sec). The fluid properties of the air are evaluated at 25 oC.

Main Index

234

Patran Interface to MSC Nastran Thermal Example 5 - Typical Avionics Flow

Create the Geometry

Table 7-79

u Geometry

Action:

Create

Object:

Curve

Method:

XYZ

Table 7-80 Curve ID List

1

Vector Coordinates List

Origin Coordinates List

[000]

-Apply-* Table 7-81

u Geometry

Action:

Transform

Object:

Curve

Method:

Translate

Table 7-82 Curve ID List

2

Translation Vector

< 0 0.5 0 > If the Auto Execute is ON you do not need to click on -Apply-

Auto Execute Curve List

Curve 1 -Apply-*

Table 7-83

Main Index

u Geometry

Action:

Create

Object:

Curve

Method:

Point

Table 7-84 Curve ID List

3

Starting Point

Point 1

Chapter 7: Example Problems Example 5 - Typical Avionics Flow

Main Index

235

236

Patran Interface to MSC Nastran Thermal Example 5 - Typical Avionics Flow

Table 7-85

u Geometry

Action:

Create

Object:

Surface

Method:

Extrude

Table 7-86 Translation Vector

< 0 0 -10 >

Curve List

Curve 1:4 -ApplyUse Iso 4 View icon to obtain 3D view

Table 7-87

u Geometry

Action:

Create

Object:

Curve

Method:

XYZ

Table 7-88 Vector Coordinates List

< 0 0 -10 >

Origin Coordinates List

[ 0.5 0.25 0 ]

-ApplyTable 7-89

u Geometry

Action:

Transform

Object:

Surface

Method:

Translate

Table 7-90 Translation Vector

Repeat Count

4 Click on the Surface icon

Surface List

Surface 1 2 4 -Apply-

Main Index

Chapter 7: Example Problems Example 5 - Typical Avionics Flow

Ending Point

Point 3 You can use the Auto Execute instead of clicking on -Apply-

-ApplyCurve ID List

4

Starting Point

Point 2

Ending Point

Point 4 You can use the Auto Execute instead of clicking on -Apply-

-ApplyTable 7-91 Translation Vector

Repeat Count

4 If the Auto Execute is ON you do not need to click on -Apply-

Auto Execute

Click on the Curve icon Curve List

Curve 5 -Apply-

Table 7-92

Main Index

u Geometry

Action:

Transform

Object:

Curve

Method:

Translate

237

238

Patran Interface to MSC Nastran Thermal Example 5 - Typical Avionics Flow

Create Finite Elements Mesh Surfaces 1 to 16 to create QUAD4 elements with global edge length 0.25. Similarly, mesh Curves 5 to 9 with Bar2 elements using a Global Edge Length of 0.25. Table 7-93

u Finite Elements

Action:

Create

Object:

Mesh

Type:

Surface

Table 7-94 Global Edge Length

.25

Element Topology Surface List

Quad 4

Highlight

Surface 1:16 -Apply-

Table 7-95

u Finite Elements

Action:

Create

Object:

Mesh

Type:

Curve

Table 7-96 Global Edge Length

.25

Element Topology Curve List

Curve 5:9 -Apply-

Main Index

Bar 2

Highlight

Chapter 7: Example Problems Example 5 - Typical Avionics Flow

Merge the Common Nodes

Table 7-97

u Finite Elements

Action:

Equivalence

Object:

All

Method:

Tolerance Cube

Equivalencing Tolerance -Apply-

Main Index

0.005

239

240

Patran Interface to MSC Nastran Thermal Example 5 - Typical Avionics Flow

Special Material Properties

Table 7-98

u Materials

Action:

Create

Object:

Isotropic

Method:

Manual Input alum

Material Name Input Properties... Constitutive Model: Thermal Conductivity

Solid properties 4.0

-Apply-

air

Material Name Constitutive Model: Thermal Conductivity

6.66e-4

Specific Heat

456.2

Density

5.01e-5

Dynamic Viscosity

1.03e-6

-Apply-

Main Index

Fluid properties

Chapter 7: Example Problems Example 5 - Typical Avionics Flow

Main Index

241

242

Patran Interface to MSC Nastran Thermal Example 5 - Typical Avionics Flow

Define Element Properties The thickness of the four side walls that separate fluid channels is 0.1 inch. The other walls have a thickness of 0.05 inch. For flow tube elements, the equivalent hydraulic diameter is: Dh = 4 * Cross-Sectional Area / Perimeter = 4 * 0.32 / 2.4 = 0.5333 inch. Table 7-99

u Properties

Action:

Create

Object:

2D

Type:

Shell

Table 7-100 Property Set Name

outside_walls

Input Properties... Material Name:

m:alum

Thickness

0.05

Select from Material Property Sets

OK Using mouse click on Front View icon to choose walls Select Members

Surface 1:3 5 6 8 9 11 12 14:16 Add -Apply-

Property Set Name

inner_walls

Input Properties... Material Name:

m:alum

Thickness

0.1 OK

Select Members

Surface 4:13:3 Add -Apply-

Main Index

Select from Material Property Sets

Chapter 7: Example Problems Example 5 - Typical Avionics Flow

Table 7-101

u Properties

Action:

Create

Object:

1D

Type:

Flow Tube

Table 7-102 Property Set Name

air_flow

Input Properties... Material Name:

m:air

Diameter at Node 1

0.5333 OK

Select Members

Curve 5:9 Add -Apply-

Main Index

Select from Material Property Sets

243

244

Patran Interface to MSC Nastran Thermal Example 5 - Typical Avionics Flow

Apply a Heat Load on the Top Surface

Table 7-103

u Load/Boundary Conditions

Action:

Create

Object:

Applied Heat

Type:

Element Uniform

Table 7-104 Option:

Normal Fluxes

New Set Name

flux

Target Element Type

2D

Input Data... Surface Option:

Top

Top Surf Heat Flux

20 OK

Select Application Region Geometry Filter

uGeometry

Select Surfaces or Edges

Surface 2 6:15:3

Add OK -Apply-

Main Index

Or select with mouse using the Select icon

Chapter 7: Example Problems Example 5 - Typical Avionics Flow

Define the Inlet Temperature of the Fluid

u Load/Boundary Conditions

Table 7-105 Action:

Create

Object:

Temp (Thermal)

Type:

Nodal inlet_temp

New Set Name Input Data... Boundary Temperature

20

OK Select Application Region

uGeometry

Geometry Filter

Click on the Point or Vertex icon

Select Geometry Entities Add OK -Apply-

Main Index

Point 9 27:33:2

245

246

Patran Interface to MSC Nastran Thermal Example 5 - Typical Avionics Flow

Main Index

Chapter 7: Example Problems Example 5 - Typical Avionics Flow

Apply Coupled Advection Five load sets, one for each channel, are defined for the fluid-structure coupling.

u Load/Boundary Conditions

Table 7-106 Action:

Create

Object:

Convection

Type:

Element Uniform

Table 7-107 Option:

Coupled Advection

New Set Name:

conv1

Target Element Type:

2D

Region 2:

1D Input Data...

Surface Option:

Top

Top Surf Convection Coef

0.3

Mass Flow Rate

8.333e-3 OK

Select Application Region

uGeometry

Geometry Filter

Change the view to Front View Select Surfaces or Edges

Surface 1:4

For the Application Region

Add For the Companion Region (the second one)

Active List Select Curves

Curve 5 Add OK -Apply-

Do the same for the remaining four (4) channels.

Main Index

247

248

Patran Interface to MSC Nastran Thermal Example 5 - Typical Avionics Flow

Main Index

Chapter 7: Example Problems Example 5 - Typical Avionics Flow

For the Companion Region

Active List Select Curves

Curve 6 Add OK -Apply-

New Set Name:

conv3

Select Application Region

uGeometry

Geometry Filter

For the Application Region

Active List Select Surfaces or Edges

Surface 7:10

Add For the Companion Region

Active List Select Curves

Curve 7 Add OK -Applyconv4

New Set Name: Select Application Region

uGeometry

Geometry Filter

For the Application Region

Active List

Select Surfaces or Edges

Surface 10:13

Add For the Companion Region

Active List

Curve 8

Select Curves Add OK -Apply-

Main Index

249

250

Patran Interface to MSC Nastran Thermal Example 5 - Typical Avionics Flow

Table 7-108 New Set Name:

conv2

Select Application Region

uGeometry

Geometry Filter

For the Application Region

Active List Select Surfaces or Edges

Surface 4:7

Add

conv5

New Set Name: Select Application Region

uGeometry

Geometry Filter

For the Application Region

Active List

Select Surfaces

Surface 13:16 Add For the Companion Region

Active List

Select Curves

Curve 9 Add OK -Apply-

Main Index

Chapter 7: Example Problems Example 5 - Typical Avionics Flow

Perform the Analysis Perform the analysis. Table 7-109

u Analysis

Action:

Analyze

Object:

Entire Model

Method:

Full Run

Job Name

ex5 -Apply-

Read in the Analysis Results

Table 7-110

u Analysis

Action:

Read Output2

Object:

Result Entities

Method:

Translate

Job Name

ex5 Select Results File... ex5.op2 OK -Apply-

Main Index

Highlight

251

252

Patran Interface to MSC Nastran Thermal Example 5 - Typical Avionics Flow

Display the Results Display the results.

u Results Object:

Quick Plot

Table 7-111 Select Results Cases

Default, PW Linear: 100. % of Load

Highlight

Select Fringe Result

Temperatures

Highlight Change the view to Iso1 View

-Apply-

Discussion of Results The heat flux is imposed on the top of the plate with power density of 20 W/in2. The heat is then spread throughout the aluminum heat sink, and is carried away by the forced air convection inside the channels. The inlet temperature is at 20 oC. There will be a temperature rise in the fluid due to the imposed surface heat flux. The maximum temperature, 101.2 oC, occurs near the exhaust of the module. The exit air temperature is at 71.82 oC. We can check the energy balance on the fluid as follows: Total heat = 20*5*10=1000 W The specific heat is 456.2 J/lbm-oC. The mass flow rate is 0.008333 * 5 = 0.04167 lbm/sec ΔT = 1000/(0.04167*456.2) = 52.6 oC Exit air temperature = 20 + 52.6 = 72.6 oC We can see the exit temperature (71.82oC) calculated by MSC Nastran is very close to the hand calculation of 72.6 oC.

Main Index

Chapter 7: Example Problems Example 6 - Radiation Enclosures

Example 6 - Radiation Enclosures

I

II

III

Cavity 1

Cavity 2

Aluminum Plate k = 204 W/m-oK

ε = 1.0

1 1/2 m

3m

Thickness = 0.001 m

q=2000 W/m2 2m

Y X

1m

Z

2m

3m

Problem Description Three plates are in radiative equilibrium with a zero-degree ambient environment. Each plate measures 2 m by 3 m, and are arranged as shown in the figure above. The center plate (II) has a heat flux applied to it with a magnitude of 2000 W/m2 in the central region, as illustrated. The emissivity of all surfaces is chosen as 1.0, representing perfect blackbodies. The plate thicknesses are all 0.001 m, and the material is aluminum. Temperature distribution for each plate will be determined.

Modeling Each plate is meshed with sixteen QUAD8 elements. Two radiation cavities are defined. Cavity 1 includes all the elements on Plates I and II that view each other. These elements also communicate with zero-degree space. The second cavity is comprised of the elements on Plates II and III, which see each other, and they also communicate with zero-degree space. By defining two separate cavities, we have eliminated any of the shadowing calculations that would be required on a single-cavity model. The non-cavity sides of Plates I and III are treated as adiabatic surfaces (i.e., perfectly insulated). The normal heat flux is applied to one side of the centermost four elements of Plate II, for a total heat load of 3000 W.

Main Index

253

254

Patran Interface to MSC Nastran Thermal Example 6 - Radiation Enclosures

Create the Geometry

Table 7-112

u Geometry

Action:

Create

Object:

Surface

Method:

XYZ

Vector Coordinates List

Origin Coordinates List

[000]

-Apply-

Table 7-113

u Geometry

Action:

Transform

Object:

Surface

Method:

Translate

Translation Vector:

If the Auto Execute is ON, you do not need to click on -Apply-

Auto Execute Surface List

Surface 1 -ApplyChange the view to Iso 2 View

Translation Vector:

Surface List

Surface 2 -Apply-

Main Index

You can use the Auto Execute instead of clicking on -Apply-

Chapter 7: Example Problems Example 6 - Radiation Enclosures

Mesh the Plates Mesh the plates. Table 7-114

uFinite Elements

Action:

Create

Object:

Mesh Seed

Type:

Uniform

uNumber of Elements Number=

4

Curve List

Surface 1.1 1.2 2.1 2.2 3.1 3.2 -Apply-

Table 7-115

uFinite Elements

Action:

Create

Object:

Mesh

Type:

Surface

Global Edge Length

1

Element Topology

Quad8

uIsoMesh Surface List

Surface 1:3 -Apply-

Main Index

Highlight

255

256

Patran Interface to MSC Nastran Thermal Example 6 - Radiation Enclosures

Specify Materials Specify the materials to be used. Table 7-116

u Materials

Action:

Create

Object:

Isotropic

Method:

Manual Input

Material Name

alum

Input Properties... Constitutive Model

Solid properties

Thermal Conductivity

204

-Apply-

Main Index

Chapter 7: Example Problems Example 6 - Radiation Enclosures

Define Element Properties Define the element properties. Table 7-117

u Properties

Action:

Create

Dimension:

2D

Type:

Shell

Property Set Name

alum

Input Properties... Material Name

m:alum

Thickness

0.001 OK

Select Members

Surface 1:3 Add -Apply-

Main Index

Select from Material Property Sets

257

258

Patran Interface to MSC Nastran Thermal Example 6 - Radiation Enclosures

Main Index

Chapter 7: Example Problems Example 6 - Radiation Enclosures

Select Application Region Geometry Filter

uGeometry

Select Surfaces or Edges

Surface 2

Add OK -Apply-

New Set Name:

encl_2

Input Data... Surface Option:

Top

Enclosure ID

2

Top Surf Emissivity

1.0 OK

Select Application Region Geometry Filter

uGeometry

Select Surfaces or Edges

Surface 2

Add OK -Apply-

New Set Name:

encl_2a

Input Data... Surface Option:

Bottom

Enclosure ID

2

Bottom Surf Emissivity

1.0

OK Select Application Region Geometry Filter

uGeometry

Select Surfaces or Edges

Surface 3

Add OK -Apply-

Main Index

259

260

Patran Interface to MSC Nastran Thermal Example 6 - Radiation Enclosures

Apply a Heat Flux

Table 7-118

u Load/Boundary Conditions

Action:

Create

Object:

Applied Heat

Type:

Element Uniform

Option:

Normal Fluxes

New Set Name

heat_flux

Target Element Type:

2D

Input Data... Surface Option:

Top

Top Surf Heat Flux

2000 OK

Select Application Region Geometry Filter

uFEM

Select 2D Elements or Edges

Elm 22 23 26 27

Add OK -Apply-

Main Index

Chapter 7: Example Problems Example 6 - Radiation Enclosures

Set Default Initial Temperature and Perform the Analysis Since radiation heat transfer, by definition, makes our problem highly nonlinear, we need to consider the Default Initial Temperature setting if we hope to achieve a converged solution with the MSC Nastran thermal solver. Table 7-119

u Analysis

Action:

Analyze

Object:

Entire Model

Type:

Full Run

Job Name:

ex6 Solution Type....

Solution Parameters... Default Init Temperature=

500

Radiation Parameters.... Stefan-Boltzmann Constant: OK OK OK -Apply-

Main Index

5.6696E-8

Click on Stefan-Boltzmann Constant for list in various units

261

262

Patran Interface to MSC Nastran Thermal Example 6 - Radiation Enclosures

Read in the Analysis Results

u Analysis Action:

Read Output2

Object:

Result Entities

Method:

Translate

Table 7-120 Job Name

ex6

Select Results File... ex6.op2

Highlight

OK -Apply-

Display the Results

u Results Object:

Quick Plot

Table 7-121 Select Results Cases

Default, PW Linear: 100. % of Load

Highlight

Select Fringe Result

Temperatures

Highlight

-Apply-

Discussion of Results The center plate has the highest and the lowest temperature for the problem. Since the heat flux is applied to this plate, we expect the maximum temperature to occur here. But what about the minimum temperature? Recall that our model includes a good deal of radiation exchange with a space environment. The outer plates (I and III) are insulated on their non-cavity sides. Therefore, only the cavity-facing side can “see” the space environment. The center plate with the heat flux load, however, can

Main Index

Chapter 7: Example Problems Example 7 - Axisymmetric Flow in a Pipe

view space from both sides, allowing it to be twice as effective in loosing energy to space. This accounts for the minimum temperature condition on the edges of the plate. Additionally, plate I has a higher temperature than Plate III due to its relative location being closer to the center plate than Plate III.

Example 7 - Axisymmetric Flow in a Pipe Figure 7-5

Z Region A

Fluid

Region B q = qvol (z) = 1200 (1 - Z/5) Btu/hr-ft3

h = 3.0 Btu/hr-ft2-oF

5.0 ft

Tamb = 100 oF

X

1.5 ft 3.5 ft 3.9167 ft 4.75 ft Oil Flow

Nu = 0.023 Re0.8 Pr0.3333

Tin = 100 oF

Koil = 0.077 Btu/hr-ft-oF

KA = 0.2 Btu/hr-ft-oF

m = 2.88E6 lbm/hr

Cp oil = 0.44 Btu/lbm-oF

KB = 0.5 Btu/hr-ft-oF

μoil = 100.08 lbm/ft-hr

ρoil = 56.8 lbm/ft3

.

Problem Description In this example we will analyze an axisymmetric structure for its temperature distribution. We will use the MSC Nastran CTRIAX6 axisymmetric element (in its 3 node configuration) as the heat conduction element.

Main Index

263

264

Patran Interface to MSC Nastran Thermal Example 7 - Axisymmetric Flow in a Pipe

The basic geometry is detailed in the figure above. A section of pipe consisting of composite materials is divided into two different material regions. Region A is from radius 1.5 feet to 3.5 feet. Region B is from radius 3.5 feet to 4.75 feet. The overall pipe section is 5.0 feet long with an inside diameter of 3 feet and an outside diameter of 9.5 feet. Oil flows through the interior with an inlet temperature of 100 oF and a mass flow rate of 2.88E6 lbm/hr. The forced convection heat transfer coefficient between the oil and wall is calculated by MSC Nastran using the following relationship: Nu = 0.023 Re0.8 Pr0.3333 Thermal conductivity properties for Region A and Region B are 0.2 and 0.5 Btu/hr-ft-oF. Volumetric internal heat generation occurs in the subregion of Region B (Specifically from radius 3.5 feet to 3.9167 feet), and varies based on Z location. The heat generation is 1200 * (1-Z/5) Btu/hr-ft3, where Z is given in units of feet. Free convection to an ambient temperature of 100 oF is applied to the exterior surface of the structure through a heat transfer coefficient of 3.0 Btu/hr-ft2-oF.

Modeling We will apply a special modeling technique, FIELDS, to input the volumetric heating rate as a function of Z. Coupled Flow Tube is used to tie the structure to the fluid elements.

Main Index

Chapter 7: Example Problems Example 7 - Axisymmetric Flow in a Pipe

Main Index

265

266

Patran Interface to MSC Nastran Thermal Example 7 - Axisymmetric Flow in a Pipe

Create the Geometry

Table 7-122

u Geometry

Action:

Create

Object:

Curve

Method:

XYZ

Vector Coordinates List

Origin Coordinates List

[000] Select the Bottom View for working with axisymmetric geometries

-Apply-

Table 7-123

u Geometry

Action:

Create

Object:

Surface

Method:

XYZ

Surface ID List

1

Vector Coordinates List

Origin Coordinates List

[ 1.5 0 0 ]

-Apply-

Surface ID List

2

Vector Coordinates List

< .4167 0 5 >

Origin Coordinates List

[ 3.5 0 0 ]

-ApplySurface ID List

3

Vector Coordinates List

< .8333 0 5 >

Origin Coordinates List

[ 3.9167 0 0 ]

-Apply-

Main Index

Chapter 7: Example Problems Example 7 - Axisymmetric Flow in a Pipe

Mesh the Fluid Curve and the Pipe Surfaces

Table 7-124

uFinite Elements

Action:

Create

Object:

Mesh Seed

Method:

One Way Bias

Number =

10

L2/L1 =

2.0

Curve List

Curve 1 Surface 1.4 3.2 -Apply-

Table 7-125

uFinite Elements

Action:

Create

Object:

Mesh

Type:

Surface

Global Edge Length=

0.25

Element Topology=

Tria3

Surface List

Surface 1:3 -Apply-

Table 7-126

uFinite Elements

Action:

Create

Object:

Mesh

Type:

Curve

Global Edge Length =

0.25

Element Topology =

Bar2

Curve List

Curve 1 -Apply-

Main Index

267

268

Patran Interface to MSC Nastran Thermal Example 7 - Axisymmetric Flow in a Pipe

Remove Coincident Nodes

Table 7-127

u Finite Elements

Action:

Equivalence

Object:

All

Method:

Tolerance Cube

Equivalencing Tolerance -Apply-

Main Index

0.005

Chapter 7: Example Problems Example 7 - Axisymmetric Flow in a Pipe

Specify Material Properties

Table 7-128

u Materials

Action:

Create

Object:

Isotropic

Method:

Manual Input

Material Name

mat_a

Input Properties... Constitutive Model:

Solid Properties

Thermal Conductivity =

0.2

-Apply-

Material Name

mat_b

Constitutive Model:

Solid Properties

Thermal Conductivity =

0.5

-Apply-

Material Name

oil

Constitutive Model:

Fluid Properties

Thermal Conductivity =

0.077

Specific Heat =

0.44

Density =

56.8

Dynamic Viscosity =

100.08

-Apply-

Main Index

269

270

Patran Interface to MSC Nastran Thermal Example 7 - Axisymmetric Flow in a Pipe

Define Element Properties

Table 7-129

u Properties

Action:

Create

Dimension:

2D

Type:

Axisym Solid

Property Set Name

pipe_a

Input Properties... Material Name:

m:mat_a

Select from Material Property Sets

OK Application Region Select Members

Surface 1 Add -Apply-

Property Set Name

pipe_b

Input Properties... Material Name:

m:mat_b OK

Application Region Select Members

Surface 2 3 Add -Apply-

Main Index

Select from Material Property Sets

Chapter 7: Example Problems Example 7 - Axisymmetric Flow in a Pipe

Table 7-130

u Properties

Action:

Create

Dimension:

1D

Type:

Flow Tube

Property Set Name

oil

Input Properties... Material Name:

m:oil

Diameter at Node 1

3.0 OK

Application Region

Select Members

Curve 1 Add -Apply-

Define a Spatial Field

Table 7-131

uFields

Action:

Create

Object:

Spatial

Method:

PCL Function

Field Name

qvol_z

Scalar Function (’X, ’Y, ’Z)

1200*(1.0-’Z/5.0)

-Apply-

Main Index

Select from Material Property Sets

271

272

Patran Interface to MSC Nastran Thermal Example 7 - Axisymmetric Flow in a Pipe

Apply a Volumetric Heat Load

Table 7-132

u Load/Boundary Conditions

Action:

Create

Object:

Applied Heat

Type:

Element Uniform

Option:

Volumetric Generation

New Set Name:

qvol

Target Element Type:

2D

Input Data... Volumetric Heat Generation

f:qvol_z

OK Select Application Region Geometry Filter

uGeometry

Select Surfaces:

Surface 2 Add OK -Apply-

Main Index

Select from Spatial Fields

Chapter 7: Example Problems Example 7 - Axisymmetric Flow in a Pipe

Apply Free Convection

Table 7-133

u Load/Boundary Conditions

Action:

Create

Object:

Convection

Type:

Element Uniform

Option:

To Ambient

New Set Name

conv

Target Element Type

2D

Input Data... Surface Option

edge

Edge Convection Coef

3.0

Ambient Temperature

100

OK Select Application Region

uGeometry

Geometry Filter

Select the Edge icon

Select Surfaces or Edges Add OK -Apply-

Main Index

Surface 3.2

273

274

Patran Interface to MSC Nastran Thermal Example 7 - Axisymmetric Flow in a Pipe

Define Inlet Temperatures of the Fluid

Table 7-134

u Load/Boundary Conditions

Action:

Create

Object:

Temp (Thermal)

Type:

Nodal

New Set Name

inlet_temp

Input Data... Boundary Temperature

100

OK Select Application Region Geometry Filter

uGeometry

Select Geometry Entities

Point 1

Add OK -Apply-

Main Index

Chapter 7: Example Problems Example 7 - Axisymmetric Flow in a Pipe

Main Index

275

276

Patran Interface to MSC Nastran Thermal Example 7 - Axisymmetric Flow in a Pipe

Define Coupled Flow Tube Apply a fluid-structure coupling between the oil and the inner wall of the pipe. Table 7-135

u Load/Boundary Conditions

Action:

Create

Object:

Convection

Type:

Element Uniform

Option:

Coupled Flow Tube

New Set Name

coup_ftube

Target Element Type

10

Region 2

2D Input Data...

Form Type:

Advanced

Mass Flow Rate

2.88e6

Heat Transfer Coefficient

0.023

Formula Type Option

u h=k/d*coef*Re**Expr*Pr**Expp

Reynolds Exponent

0.8

Prandtl Exponent, Heat In

0.3333

OK Select Application Region Geometry Filter

uGeometry

Select Curves

Curve 1 Add Active List

Select Surfaces or Edges

For the Companion Region (the second one)

Surface 1.4 Be sure to click on the Edge icon while selecting the geometrical entity

Add OK -Apply-

Main Index

Chapter 7: Example Problems Example 7 - Axisymmetric Flow in a Pipe

Perform the Analysis

Table 7-136

u Analysis

Action:

Analyze

Object:

Entire Model

Method:

Full Run

Job Name

ex7 -Apply-

Read in the Analysis Results

Table 7-137

u Analysis

Action:

Read Output2

Object:

Result Entities

Method:

Translate

Job Name

ex7 Select Results File... ex7.op2 OK -Apply-

Display the Results

Main Index

Highlight

277

278

Patran Interface to MSC Nastran Thermal Example 7 - Axisymmetric Flow in a Pipe

u Results Object:

Quick Plot

Table 7-138 Select Results Cases Default, PW Linear: 100. % of Load

Highlight

Select Fringe Result

Highlight

Temperatures

-Apply-

Discussion of Results The maximum temperature occurs near the internal heat generation region with a temperature of 842.3oF. The fluid temperature remains constant at 100 oF because of the massive flow rate at 2.88E6 lbm/hr. We can check the energy balance on this model as follows: Total heat = 2.91246E4 Btu/hr (from the OLOAD RESULTANT of the F06 file) Sum of the heat on the column under Free Convection = 2.5828E4 Btu/hr Sum of the heat on the column under Forced Convection = 3.297E3 Btu/hr Sum of the heat on the above two columns = 2.9125E4 Btu/hr, which is equal to the input heat of 2.91246E4 Btu/hr. An assumption of a 1-D fluid element is that temperature gradients within the fluid are only significant along the axial direction. With such a large diameter flow tube, this assumption is probably being misused in this particular problem. The application of the flow tube boundary convection relationship also implies fully developed flow, yet, over only a 5 foot section and with a 3 foot diameter, this is also a very crude approximation. In essence, what we are saying, is that this example serves to illustrate coupled convection in an axisymmetric environment, application of spatial heat loads, and use of convection correlation equations, rather than fluid physics.

Main Index

Chapter 7: Example Problems Example 8 - Directional Heat Loads

Example 8 - Directional Heat Loads Figure 7-6

6.0 in

Radiation Boundary Condition 1.5 in

q = qvec = 30 W/in2

View Factor = 1.0 Tamb = 20.0 oC

Aluminum Cylinder k = 3.96 W/in-oC

Y

α = ε = 0.8 Thickness = 0.0625 in

Z

X

Problem Description In this example we will apply a directional heat load on cylinder. We will orient the surface normal from the surface such that the normal vector (Right hand rule) will point away from the surface. This allows the incoming directional heat flux to see the normals, and project the correct energy by forming a dot product with this vector. A typical application of this directional heat load process is in an orbital heating environment. The dimension of the cylinder is 1.5 inch in diameter with a length of 6 inches. The material is aluminum with a thermal conductivity of 3.96 W/in-oC. The absorptivity and emissivity of the cylinder surface are 0.8. The directional heat load is 30 W/in2. The exterior surface of the cylinder looses heat by radiation to space. The radiation view factor is 1.0 and the ambient temperature is 20 oC.

Main Index

279

280

Patran Interface to MSC Nastran Thermal Example 8 - Directional Heat Loads

Modeling We will first calculate the temperature distribution based on the above boundary conditions. Subsequently in Example 9, we will create a spatial FEM field that defines the temperature load for a thermal stress analysis.

Main Index

Chapter 7: Example Problems Example 8 - Directional Heat Loads

Main Index

281

282

Patran Interface to MSC Nastran Thermal Example 8 - Directional Heat Loads

Create the Geometry Table 7-139 u Geometry Action:

Create

Object:

Point

Method:

XYZ

Point ID List

1

Refer Coordinate Frame

Coord 0

Point Coordinates List

[ 0.75 0 0 ]

-Apply-

Table 7-140

u Geometry

Action:

Create

Object:

Curve

Method:

Revolve

Curve ID List

1

Total Angle

360.0 If the Auto Execute is ON, you do not need to click on -Apply-

Auto Execute Point List

Point 1 -Apply-

Table 7-141

u Geometry

Action:

Create

Object:

Surface

Method:

Extrude

Translation Vector

< 0 0 -6 >

Curve List

Curve 1 Click on Iso1 View icon to obtain 3D view of the cylinder

-Apply-

Main Index

You can use the Auto Execute instead of clicking on -Apply-

Chapter 7: Example Problems Example 8 - Directional Heat Loads

The surface normal direction is important in this problem, because the incoming heat flux vector will form a dot product with the normal vector for the surface generating the correct projected surface area for application of the heat load. Therefore, when we created the cylinder using geometry, we should verify that the normal vector points outward. This is accomplished by using: Table 7-142

u Geometry

Action:

Show

Object:

Surface

Info:

Normal If the Auto Execute is ON, you do not need to click on -Apply-

Auto Execute

Surface List

Surface 1

With the mouse draw a box around Surface 1

Change the view to Front View

-ApplySelect Surface 1 to make sure that the normal vector indicated by the red arrow points outward from the cylinder. If the normal vector is pointing inward, then you can reverse the surface normal by using the following command: Table 7-143

u Geometry

Action:

Edit

Object:

Surface

Method:

Reverse If the Auto Execute is ON, you do not need to click on -Apply-

Auto Execute

Surface List

Surface 1 -Apply-

Main Index

283

284

Patran Interface to MSC Nastran Thermal Example 8 - Directional Heat Loads

Create Finite Elements

Table 7-144

uFinite Elements

Action:

Create

Object:

Mesh

Method:

Surface

Global Edge Length

0.1

Element Topology

Quad4

Surface List

Surface 1

Highlight

-ApplyChange the view to Iso1 View

Remove Coincident Nodes

Table 7-145

u Finite Elements

Action:

Equivalence

Object:

All

Method:

Tolerance Cube

Equivalencing Tolerance -Apply-

Main Index

0.005

Chapter 7: Example Problems Example 8 - Directional Heat Loads

Specify Material Properties

Table 7-146

u Materials

Action:

Create

Object:

Isotropic

Method:

Manual Input

Material Name

alum

Input Properties... Constitutive Model

Solid properties

Thermal Conductivity

3.96

-Apply-

Main Index

285

286

Patran Interface to MSC Nastran Thermal Example 8 - Directional Heat Loads

Define Element Properties

Table 7-147

u Properties

Action:

Create

Dimension:

2D

Type:

Shell

Property Set Name

alum

Input Properties... Material Name

m:alum

Thickness

0.0625 OK

Select Members

Surface 1 Add -Apply-

Main Index

Select from Material Property Sets

Chapter 7: Example Problems Example 8 - Directional Heat Loads

Apply a Directional Heat Load

Table 7-148

u Load/Boundary Conditions

Action:

Create

Object:

Applied Heat

Type:

Element Uniform

Option:

Directional Fluxes

New Set Name

vector_flux

Target Element Type:

2D

Input Data... Surface Option:

Top

Top Surf Absorptivity

0.8

Top Surf Heat Flux

30

Incident Thermal Vector

< -1 0 0 >

OK Select Application Region Geometry Filter

uGeometry

Select Surfaces or Edges

Surface 1

Add OK -Apply-

Main Index

Select the Directional Fluxes Option before defining the Element Uniform Type

287

288

Patran Interface to MSC Nastran Thermal Example 8 - Directional Heat Loads

Apply a Radiation Boundary Condition

Table 7-149

u Load/Boundary Conditions

Action:

Create

Object:

Radiation

Type:

Element Uniform

Option:

Ambient Space

New Set Name:

rad_space

Target Element Type:

2D

Input Data... Surface Option:

Top

Top Surf Emissivity

0.8

Top Surf Absorptivity

0.8

Ambient Temperature

20

View Factor

1.0 OK

Select Application Region Geometry Filter

uGeometry

Select Surfaces or Edges

Surface 1

Add OK -Apply-

Main Index

Chapter 7: Example Problems Example 8 - Directional Heat Loads

Specify Radiation Parameters and Perform the Analysis

Table 7-150

u Analysis

Action:

Analyze

Object:

Entire Model

Method:

Full Run

Job Name

ex8 Solution Type...

STEADY STATE ANALYSIS Solution Parameters... Radiation Parameters... Absolute Temperature Scale:

273.15

Click on Absolute Temperature Scale for list in various units

Stefan-Boltzmann Constant:

3.6580E-11

Click on Stefan-Boltzmann Constant for list in various units

OK OK OK -Apply-

Main Index

289

290

Patran Interface to MSC Nastran Thermal Example 8 - Directional Heat Loads

Read in the Analysis Results

Table 7-151

u Analysis

Action:

Read Output2

Object:

Result Entities

Method:

Translate

Job Name

ex8 ex8.op2

Select Results File...

Highlight

OK -Apply-

Display the Results

u Results Object:

Quick Plot

Table 7-152 Select Results Cases Default, PW Linear: 100. % of Load Select Fringe Result

Temperatures

Highlight Highlight

-Apply-

Note:

Continue with Step 1 of Example 9 to perform a structural analysis.

Discussion of Results Example 8 demonstrates an aluminum cylinder in radiative equilibrium. The heat source is directional (light source oriented), and the radiation boundary condition is equal for all directions. Main Index

Chapter 7: Example Problems Example 9 - Thermal Stress Analysis from Directional Heat Loads

The cylinder’s maximum temperature (~473 oC) is attained on the side subject to the solar heat load. The minimum temperature (~424 oC) occurs in the shadow region. The high conductivity of the cylinder helps to equilibrate the temperatures. If the conductivity were very low, the maximum temperature would approach 740 oC with the minimum approximately 20 oC.

Example 9 - Thermal Stress Analysis from Directional Heat Loads Figure 7-7

6.0 in

Aluminum Cylinder

1.5 in

E = 1.0E7 lb/in2

ν = 0.34 α = 1.3E-5 in/in-oC

Y

Z

Main Index

Thickness = 0.0625 in

X

291

292

Patran Interface to MSC Nastran Thermal Example 9 - Thermal Stress Analysis from Directional Heat Loads

Problem Description This example demonstrates how to apply the thermal results of Example 8 to perform a stress analysis. We will create the temperature loading for the stress run by using the Create-Spatial-FEM command under the Fields Application. You can also use the include punch file option to get the thermal load. The diameter of the cylinder is 1.5 inch with a length of 6 inches. The material is aluminum. The heat transfer problem solved in Example 8 resulted in a temperature solution which we would now like to apply to a thermal stress analysis.

Modeling We will first apply the Create-Spatial-FEM command to define the temperature load for a thermal stress analysis. Initially, the structure is stress-free at a temperature of 0 oC. The cylinder is clamped on both ends for the thermal stress calculation. Create a Spatial FEM Field Based on the Temperature Profile

Table 7-153

uFields

Action:

Create

Object:

Spatial

Method:

FEM

Field Name

tempload

FEM Field Definition Mesh/Results Group Filter

uContinuous uScalar uCurrent Viewport

Select Group

default_group

Field Type

-Apply-

Change the Analysis Type to Structural

Table 7-154 Preferences Analysis...

Main Index

Highlight

Chapter 7: Example Problems Example 9 - Thermal Stress Analysis from Directional Heat Loads

Analysis Type:

Structural OK

Specify the Structural Materials

Table 7-155

u Materials

Action:

Create

Object:

Isotropic

Method:

Manual Input

Material Name

alum_st

Input Properties... Constitutive Model

Linear Elastic

Elastic Modulus =

1.0e7

Poisson Ratio =

0.34

Thermal Expan. Coeff =

1.3e-5

Reference Temperature

0.0

-Apply-

Main Index

293

294

Patran Interface to MSC Nastran Thermal Example 9 - Thermal Stress Analysis from Directional Heat Loads

Assign Element Properties

Table 7-156

u Properties

Action:

Create

Dimension:

2D

Type:

Shell

Property Set Name

alum_st

Input Properties... Material Name

m:alum_st

Thickness

0.0625

Select from Material Property Sets

OK Select Members

Surface 1 Add -Apply-

Create a New Load Case We will create a new load case consisting of the structural thermal loading and apply the fixed boundary conditions on the ends of the cylinder. Table 7-157

u Load Cases

Action:

Create

Load Case Name

struct_load

Load Case Type:

Static -Apply-

Main Index

Chapter 7: Example Problems Example 9 - Thermal Stress Analysis from Directional Heat Loads

Apply the Clamped Boundary Conditions

u Load/Boundary Conditions

Table 7-158 Action:

Create

Object:

Displacement

Type:

Nodal

Analysis Type:

Structural

Current Load Case:

struct_load

New Set Name:

clamp_bc

Switch to Structural from Thermal

Input Data... Load/BC Set Scale Factor

1.0

Translations

< 0., 0., 0. >

Rotations

< 0., 0., 0. >

OK Select Application Region

uGeometry

Geometry Filter

Click on the Curve or Edge icon

Select Geometry Entities Add OK -Apply-

Main Index

Curve 1 Surface 1.3

295

296

Patran Interface to MSC Nastran Thermal Example 9 - Thermal Stress Analysis from Directional Heat Loads

Define a Temperature Load

u Load/Boundary Conditions

Table 7-159 Action:

Create

Object:

Temperature

Type:

Nodal

Analysis Type:

Structural

Current Load Case:

struct_load

New Set Name

temp_load

Input Data... Load/BC Set Scale Factor

1.0

Temperature

f:tempload

Select from Spatial Fields

OK Select Application Region

uGeometry

Geometry Filter

Click on the Surface or Face icon

Select Geometry Entities Add OK -Apply-

Main Index

Surface 1

Chapter 7: Example Problems Example 9 - Thermal Stress Analysis from Directional Heat Loads

Perform the Analysis

Table 7-160

u Analysis

Action:

Analyze

Object:

Entire Model

Method:

Full Run

Job Name

ex9 Subcase Select

Subcases For Solution Sequence: 101

struct_load

Highlight

Subcases Selected:

struct_load

Click on default to remove

OK -Apply-

Read in the Analysis Results

u Analysis Action:

Read Output2

Object:

Result Entities

Method:

Translate

Table 7-161 Job Name Select Results File... OK -Apply-

Main Index

ex9 ex9.op2

Highlight

297

298

Patran Interface to MSC Nastran Thermal Example 9 - Thermal Stress Analysis from Directional Heat Loads

Display the Results

u Results Object:

Quick Plot

Table 7-162 Select Results Cases

struct_load, Static Subcase

Highlight

Select Fringe Result

Stress Tensor

Highlight

Position:

At Z1

Quantity:

von Mises

Select Deformation Result

Displacements, Translational

Highlight

-Apply-

Discussion of Results For output we plot the von Mises stress for the fixed end cylinder undergoing the directional thermal load. Peak stresses occur near the fixed end points (recall the points are fixed in X, Y, and Z directions). Thermal expansion causes growth in the axial and radial directions with a circumferential variation due to the directional nature of the thermal load. Near the cylinder mid-plane, in an axial sense, we find the maximum stress at the location which is normal to the directional load vector. The minimum is on the opposite side of the cylinder in the shadow.

Main Index

Chapter 7: Example Problems Example 10 - Thermal Stress Analysis of a Bi-Metallic Plate

Example 10 - Thermal Stress Analysis of a Bi-Metallic Plate Figure 7-8 Y

KGe = 1.524 W/in-oC

1.0 in

Ksolder = 1.27 W/in-oC EGe = 1.885E7 lb/in2 GGe = 0.933E7 lb/in2 αGe = 5.8E-6 in/in-oC

1.0 in

X Z

ESolder = 1.3E7 lb/in2 νSolder = 0.4 αSolder = 2.47E-5 in/in-oC

T = -30.0 oC

Ge: 0.025 in X

Solder: 0.05 in

Tref = -30 oC

T = 70.0 oC

Problem Description In this example we will perform the thermal stress analysis of a bi-metallic strip. We will build the entire model from geometric construction so that we can apply loads directly on the geometry. The dimension of the bi-metallic strip is one inch by one inch. The thickness for the solder type material is 0.05 inch, and the thickness of the Ge material is 0.025 inch. Thus the assembly thickness is 0.075 inch. The top surface temperature boundary condition is -30 oC, and the bottom surface temperature boundary condition is 70 oC. We will determine the temperature distribution by running a steady-state thermal analysis.

Modeling Prior to the development of the Patran MSC Nastran Heat Transfer interface, one would request: TEMP(PUNCH)=all in the MSC Nastran Case Control section of the thermal run. The temperature load is then created and saved inside the punch file. In the subsequent thermal stress analysis one can access this file by defining TEMP(LOAD)=1 in the Case Control section of the ensuing stress analysis run.

Main Index

299

300

Patran Interface to MSC Nastran Thermal Example 10 - Thermal Stress Analysis of a Bi-Metallic Plate

However, using Patran you can use the Create-Spatial-FEM command after you have post processed the thermal result in the viewport. We will use this technique to apply a thermal load for the stress analysis. Also, we will analyze the thermal stress analysis for the free-free expansion by enforcing a minimum number of constraints to fix-rigid body motion.

Main Index

Chapter 7: Example Problems Example 10 - Thermal Stress Analysis of a Bi-Metallic Plate

Create the Model

Table 7-163

u Geometry

Action:

Create

Object:

Surface

Method:

XYZ

Vector Coordinates List

Origin Coordinates List

[000]

-Apply-

Table 7-164

u Geometry

Action:

Create

Object:

Solid

Method:

Extrude

Translation Vector

< 0 0 0.05 > If the Auto Execute is ON, you do not need to click on -Apply-

Auto Execute

Surface List

Surface 1 -ApplyClick on the Solid Face icon

Translation Vector

< 0 0 0.025 >

Surface List

Solid 1.6 -Apply-

Main Index

You can use the Auto Execute instead of clicking on -Apply-

301

302

Patran Interface to MSC Nastran Thermal Example 10 - Thermal Stress Analysis of a Bi-Metallic Plate

Mesh the Solids

Table 7-165

uFinite Elements

Action:

Create

Object:

Mesh Seed

Type:

Uniform

Number =

4

Curve List

Solid 1.1.1 1.2.1 1.2.3 1.1.3

Click on the four (4) corners of Solid 1. Hold the shift key down while you click

-ApplyNumber =

2

Curve List

Solid 2.1.1 2.2.1 2.2.3 2.1.3

Click on the four (4) corners of Solid 2. Hold the shift key down while you click

-Apply-

Table 7-166

uFinite Elements

Action:

Create

Object:

Mesh

Type:

Solid

Global Edge Length= Element Topology=

Hex8

Solid List

Solid 1 2 -Apply-

Main Index

0.1 Highlight

Chapter 7: Example Problems Example 10 - Thermal Stress Analysis of a Bi-Metallic Plate

Remove Coincident Nodes

Table 7-167

u Finite Elements

Action:

Equivalence

Object:

All

Method:

Tolerance Cube

Equivalencing Tolerance

0.005

-Apply-

Specify Thermal Material Properties

Table 7-168

u Materials

Action:

Create

Object:

Isotropic

Method:

Manual Input

Material Name

Ge

Input Properties... Constitutive Model

Solid properties

Thermal Conductivity

1.524

-ApplyMaterial Name

Solder

Constitutive Model

Solid properties

Thermal Conductivity

1.27

-Apply-

Main Index

303

304

Patran Interface to MSC Nastran Thermal Example 10 - Thermal Stress Analysis of a Bi-Metallic Plate

Define Element Properties

Table 7-169

u Properties

Action:

Create

Dimension:

3D

Type:

Solid

Property Set Name

Ge

Input Properties... Material Name

m:Ge

Select from Material Property Sets

OK Change the view to Bottom View

Select Members

Solid 2 Add -Apply-

Property Set Name

Solder

Input Properties... Material Name

m:Solder OK

Select Members

Solid 1 Add -Apply-

Main Index

Select from Material Property Sets

Chapter 7: Example Problems Example 10 - Thermal Stress Analysis of a Bi-Metallic Plate

Main Index

305

306

Patran Interface to MSC Nastran Thermal Example 10 - Thermal Stress Analysis of a Bi-Metallic Plate

Apply Temperature Boundary Conditions

u Load/Boundary Conditions

Table 7-170 Action:

Create

Object:

Temp (Thermal)

Type:

Nodal

Analysis Type:

Thermal

New Set Name

temp_bottom

Input Data... Boundary Temperature

70

OK Select Application Region

uGeometry

Geometry Filter

Click on the Surface or Face icon

Select Geometry Entities

Surface 1

Click on bottom surface

Add OK -Apply-

New Set Name

temp_top

Input Data... Boundary Temperature

-30

OK Select Application Region

uGeometry

Geometry Filter

Click on the Surface icon

Select Geometry Entities Add OK -Apply-

Main Index

Solid 2.6

Chapter 7: Example Problems Example 10 - Thermal Stress Analysis of a Bi-Metallic Plate

Perform the Thermal Analysis

Table 7-171

u Analysis

Action:

Analyze

Object:

Entire Model

Method:

Full Run

Job Name

ex10 -Apply-

Read in the Analysis Results

u Analysis Action:

Read Output2

Object:

Result Entities

Method:

Translate

Table 7-172 Job Name

ex10

Select Results File... ex10.op2 OK -Apply-

Display the Results

Main Index

Highlight

307

308

Patran Interface to MSC Nastran Thermal Example 10 - Thermal Stress Analysis of a Bi-Metallic Plate

u Results Object:

Quick Plot

Table 7-173 Select Results Cases Select Fringe Result

Default, PW Linear: 100. % of Load

Highlight Highlight

Temperatures

Change the view to Iso1 View

-ApplyDefine a Spatial FEM Field Based on the Temperature Profile

u Fields Action:

Create

Object:

Spatial

Method:

FEM

Table 7-174 Field Name

t_load

FEM Field Definition

Mesh/Results Group Filter

uContinuous uScalar uCurrent Viewport

Select Group

default_group

Field Type

-Apply-

Change the Analysis Type to Structural

Main Index

Highlight

Chapter 7: Example Problems Example 10 - Thermal Stress Analysis of a Bi-Metallic Plate

Table 7-175 Preferences Analysis...

Analysis Type:

Structural OK

Specify Structural Material Properties

Table 7-176

u Materials

Action:

Create

Object:

Isotropic

Method:

Manual Input

Material Name

Solder_st

Input Properties... Constitutive Model

Linear Elastic

Elastic Modulus =

1.3e7

Poisson Ratio =

0.4

Thermal Expan. Coeff =

2.47e-5

Reference Temperature

-30.0

-ApplyMaterial Name

Ge_st

Constitutive Model

Linear Elastic

Elastic Modulus =

1.885e7

Shear Modulus =

0.933e7

Thermal Expan. Coeff =

5.8e-6

Reference Temperature

-30.0

-Apply-

Main Index

309

310

Patran Interface to MSC Nastran Thermal Example 10 - Thermal Stress Analysis of a Bi-Metallic Plate

Assign Element Properties

Table 7-177

u Properties

Action:

Create

Dimension:

3D

Type:

Solid

Property Set Name

Ge_st

Options:

Standard Formulation Input Properties...

Material Name

m:Ge_st

Select from Material Property Sets

OK Select Members

Solid 2 Add -Apply-

Property Set Name

Solder_st

Options:

Standard Formulation Input Properties...

Material Name

m:Solder_st OK

Select Members

Solid 1 Add -Apply-

Create a New Load Case

Table 7-178

Main Index

u Load Cases

Select from Material Property Sets

Chapter 7: Example Problems Example 10 - Thermal Stress Analysis of a Bi-Metallic Plate

Action:

Create

Load Case Name

struct_load

Load Case Type:

Static -Apply-

Main Index

311

312

Patran Interface to MSC Nastran Thermal Example 10 - Thermal Stress Analysis of a Bi-Metallic Plate

Define a Temperature Load

Table 7-179

u Load/Boundary Conditions

Action:

Create

Object:

Temperature

Type:

Nodal

Analysis Type:

Structural

Current Load Case:

struct_load

New Set Name

temp_load

Switch to Structural from Thermal

Input Data... Load/BC Set Scale Factor

1.0

Temperature

f:t_load

Select from Spatial Fields

OK Select Application Region Geometry Filter

Geometry Click on the Solid icon

Select Geometry Entities Add OK -Apply-

Main Index

Solid 1 2

Chapter 7: Example Problems Example 10 - Thermal Stress Analysis of a Bi-Metallic Plate

Main Index

313

314

Patran Interface to MSC Nastran Thermal Example 10 - Thermal Stress Analysis of a Bi-Metallic Plate

Apply Constraints Apply constraints on the four corner points of the top surface. Table 7-180

u Load/Boundary Conditions

Action:

Create

Object:

Displacement

Type:

Nodal

Analysis Type

Structural

New Set Name:

fix_x

Input Data... Load/BC Set Scale Factor

1.0

Translations

< 0., , >

OK Select Application Region

uGeometry

Geometry Filter

Click on the Point icon

Select Geometry Entities

Point 9 10

Add OK -Apply-

New Set Name:

fix_y

Input Data... Load/BC Set Scale Factor

1.0

Translations

< , 0., >

OK Select Application Region Geometry Filter

uGeometry

Select Geometry Entities

Point 11

Add OK -Apply-

Main Index

Chapter 7: Example Problems Example 10 - Thermal Stress Analysis of a Bi-Metallic Plate

New Set Name:

fix_z

Input Data... Load/BC Set Scale Factor

1.0

Translations

< , , 0.>

OK Select Application Region Geometry Filter

uGeometry

Select Geometry Entities

Point 9:12

Add OK -Apply-

Perform the Structural Analysis

Table 7-181

u Analysis

Action:

Analyze

Object:

Entire Model

Method:

Full Run

Job Name

ex10_st Subcase Select

Subcases For Solution Sequence: 101

struct_load

Highlight

Subcases Selected:

struct_load

Click on Default to remove

OK -Apply-

Main Index

315

316

Patran Interface to MSC Nastran Thermal Example 10 - Thermal Stress Analysis of a Bi-Metallic Plate

Read in the Analysis Results

Table 7-182

u Analysis

Action:

Read Output2

Object:

Result Entities

Method:

Translate

Job Name

ex10_st Select Results File... ex10_st.op2

Highlight

OK -Apply-

Display the Results

u Results Object:

Quick Plot

Table 7-183 Select Results struct_load, Static Subcase Cases

Highlight

Select Fringe Result

Stress Tensor

Highlight

Quantity:

von Mises

Select Deformation Result

Displacements, Translational

Highlight

-Apply-

Discussion of Results The reference or zero stress state for the assembly is initialized at -30 oC. The thermal coefficient of expansion for the solder is approximately four times that of Ge. When the temperature gradient associated with the temperature boundary conditions is applied, the solder layer wants to grow significantly more than the Ge

Main Index

Chapter 7: Example Problems Example 10 - Thermal Stress Analysis of a Bi-Metallic Plate

layer due not only to the higher coefficient of thermal expansion, but also because of the higher temperature relative to TREF. The Ge layer ends up with a more complex stress pattern due to its four corner points being constrained, the distribution of temperature through the layer, and the growth enforced by the solder layer. The free surface of the solder layer exhibits the low stress levels.

Main Index

317

318

Patran Interface to MSC Nastran Thermal Example 10 - Thermal Stress Analysis of a Bi-Metallic Plate

Main Index

Chapter 7: Example Problems Example 10 - Thermal Stress Analysis of a Bi-Metallic Plate

Main Index

319

320

Patran Interface to MSC Nastran Thermal Example 10 - Thermal Stress Analysis of a Bi-Metallic Plate

Main Index

Chapter 7: Example Problems Example 10 - Thermal Stress Analysis of a Bi-Metallic Plate

Main Index

321

322

Patran Interface to MSC Nastran Thermal Example 10 - Thermal Stress Analysis of a Bi-Metallic Plate

Main Index

MSC Nastran Implicit Nonlinear (SOL 600) User’s Guide

A

Files



Main Index

Files

324

324 Files

Files The Patran MSC Nastran Preference uses or creates several files.The following table outlines each file and its uses. In the file name definition, jobname will be replaced with the jobname assigned by the user. Description

*.db

This is the Patran database. During an analyze pass, model data is read from this database and, during a Read Results pass, model and/or results data is written into it. This file typically resides in the current directory.

jobname.jbr

These are small files used to pass certain information between Patran and the independent translation programs during translation. There should never be a need to directly alter these files. These files typically reside in the current directory.

jobname.bdf

This is the MSC Nastran input file created by the interface. This file typically resides in the current directory.

msc_v#_sol#.alt

These are a series of MSC Nastran alters that are read during forward translation. These alters instruct MSC Nastran to write information to the OUTPUT2 file that the results translation will be looking for. The forward translator searches the Patran file path for these files, but they typically reside in the /alters directory. If these files do not meet specific needs, edit them accordingly. However, the naming convention of msc_v# _sol#.alt must be preserved. Either place the edited file back into the /alters directory or in any directory on the Patran file path, which takes precedence over the /alters directory. If these files are not used, remove them from the Patran file path, rename them, or delete them altogether.

jobname.op2

This is the NASTRAN OUTPUT2 file, which is read by the Read Results pass. This file typically resides in the current directory.

jobname.flat

This file may be generated during a Read Results pass. If the results translation cannot write data directly into the specified Patran database, it will create this jobname.flat file. This file typically resides in the current directory.

jobname.msg.xx

These message files contain any diagnostic output from the translation, either forward or reverse. This file typically resides in the current directory.

MscNastranExecute

This is a Linux script file, which is called on to submit MSC Nastran after translation is complete. This file might need customizing with site specific data, such as, host machine name and MSC Nastran executable commands. This file contains many comments and should be easy to edit. Patran searches its file path to find this file, but it typically resides in the /bin/exe directory. Either use the general copy in /bin/exe, or place a local copy in a directory on the file path, which takes precedence over the /bin/exe directory.

Main Index

MSC Nastran Implicit Nonlinear (SOL 600) User’s Guide

B

Error Messages



Main Index

Error Messages

326

326 Error Messages

Error Messages There are many error or warning messages that may be generated by the Patran MSC Nastran Interface. The following table outlines some of these. Description Unable to open a new message file " ". Translation messages will be written to standard output.

If the translation tries to open a message file and cannot, it will write messages to Standard Output. On most systems, the translator automatically writes dmessages to standard output and never tries to create a separate message file.

Unable to open the specified OUTPUT2 file " ".

The OUTPUT2 file was not found. Check the OUTPUT2 file specification in the translation control file.

The specified OUTPUT2 file " " is not in standard binary format and cannot be translated.

The OUTPUT2 file is not in standard binary format. Check the OUTPUT2 file specification in the translation control file.

Group " " does not exist in the database. Model data will not be translated.

The name of a nonexistent group was specified in the translator control file. No model data will be translated from the OUTPUT2 file.

Needed file specification missing! The full name of the job file must be specified as the first command-line argument to this program.

The translation control file must be specified as the first online argument to the translator.

Unable to open the specified database " ". Writing If the translator cannot communicate directly to the specified the OUTPUT2 information to the PCL command file database. It will write the results and/or model data to a PCL " ". session file. Unable to open either the specified database " ", or a PCL command file, " ".

The naspat3 translator is unable to open any output file. Check file specification and directory protection.

Unable to open the NASTRAN input file " ".

The translator was unable to open a file to where the input file information will be written.

Unable to open the specified database, " " .

The forward Patran MSC Nastran translator was unable to open the specified Patran database.

Alter file of the name " " could not be found. No OUPUT2 alter will be written to the NASTRAN input file.

The OUTPUT2 DMAP alter file, for this type of analysis, could not be found. Correct the search path to include the necessary directory if you want the alter files to be written to the input file.

No property regions are defined in the database. No elements or element properties can be translated.

Elements referenced by an element property region in the Patran database will not get translated by the forward Patran MSC Nastran translator. If no element regions are defined, no elements will be translated.

Main Index

MSC Nastran Implicit Nonlinear (SOL 600) User’s Guide

C

Main Index

Supported Commands



File Management Statements

328



Executive Control Statements

328



Case Control Commands



Bulk Data Entries

329

328

328 File Management Statements

File Management Statements The following MSC Nastran File Management statement is supported. Description ASSIGN

An ASSIGN command is used to assign a particular name (job name + user specified MSC Nastran results suffix) to the NASTRAN OUTPUT2 file to be created during the analysis.

Executive Control Statements The following MSC Nastran Executive Control statements are supported. Description SOL

Specifies the solution sequence or main subDMAP to be executed. (p. 108)

TIME

Sets the maximum CPU and I/O time.(p. 110), (p. 113)

Case Control Commands The following MSC Nastran Case Control commands are supported. Description DLOAD

Selects a dynamic load or an acoustic source to be applied in a transient or frequency response problem. (p. 61)

ECHO

Controls echo (i.e., printout) of the Bulk Data. (p. 110), (p. 113)

ENTHALPY

Requests form of enthalpy vector output in transient heat transfer analysis (SOL 159). (p. 124)

FLUX

Requests the form and type of gradient and flux output in heat transfer analysis. (p. 124)

HDOT

Requests form of rate of change of enthalpy vector output in transient heat transfer analysis (SOL 159). (p. 124)

IC

Selects the initial conditions for direct transient analysis (SOLs 27, 69, 99, 109, 129, and 159). (p. 70)

LOAD

Selects an external static load set. (p. 61)

MAXLINES

Sets the maximum number of output lines. (p. 110), (p. 113)

MPC

Selects a multipoint constraint set. (p. 44)

NLPARM

Selects the parameters used for nonlinear static analysis. (p. 117), (p. 127)

OLOAD

Requests the form and type of applied load vector output. (p. 124)

SPC

Selects a single-point constraint set to be applied. (p. 69)

SPCFORCES

Requests the form and type of single-point force of constraint vector output. (p. 124)

SUBCASE

Delimits and identifies a subcase. (p. 115), (p. 129)

Main Index

329 Bulk Data Entries

Description SUBTITLE

Defines a subtitle that will appear on the second heading line of each page of printer output. (p. 115)

TEMPERATURE

Selects the temperature set to be used in either material property calculations or thermal loading in heat transfer and structural analysis. (p. 70)

THERMAL

Requests the form and type of temperature output. (p. 124)

TITLE

Defines a character string that will appear on the first heading line of each page of MSC Nastran printer output. (p. 101)

TSTEPNL

Selects integration and output time steps for nonlinear transient problems. (p. 122), (p. 127)

Bulk Data Entries The following MSC Nastran Bulk Data entries are supported. Description CBAR

Defines a simple beam element. (p. 55)

CBEAM

Defines a beam element. (p. 57)

CBEND

Defines a curved beam, curved pipe, or elbow element. (p. 56) (p. 57)

CDAMP1

Defines a scalar damper element. (p. 55)

CELAS1

Defines a scalar spring element. (p. 55)

CHBDYG

Defines a boundary condition surface element without reference to a property entry. (p. 67)

CHBDYP

Defines a boundary condition surface element with reference to a PHBDY entry. (p. 58), (p. 67)

CHEXA

Defines the connections of the six-sided solid element with eight to twenty grid points. (p. 61)

CONROD

Defines a rod element without reference to a property entry.(p. 106)

CONV

Specifies a free convection boundary condition for heat transfer analysis through connection to a surface element (CHBDYi entry). (p. 77), (p. 81), (p. 86)

CONVM

Specifies a forced convection boundary condition for heat transfer analysis through connection to a surface element (CHBDYi entry). (p. 78), (p. 83), (p. 86)

CORD2C

Defines a cylindrical coordinate system using the coordinates of three points. (p. 45)

CORD2R

Defines a rectangular coordinate system using the coordinates of three points. (p. 45)

CORD2S

Defines a spherical coordinate system using the coordinates of three points. (p. 45)

CPENTA

Defines the connections of a five-sided solid element with six to fifteen grid points. (p. 61)

CQUAD4

Defines an isoparametric membrane-bending or plane strain quadrilateral plate element. (p. 60)

CQUAD8

Defines a curved quadrilateral shell or plane strain element with eight grid points. (p. 60)

CROD

Defines a tension-compression-torsion element. (p. 55)

CTETRA

Defines the connections of the four-sided solid element with four to ten grid points. (p. 61)

Main Index

330 Bulk Data Entries

Description CTRIA3

Defines an isoparametric membrane-bending or plane strain triangular plate element. (p. 60)

CTRIA6

Defines a curved triangular shell element or plane strain with six grid points. (p. 60)

CTRIAX6

Defines an isoparametric and axisymmetric triangular cross section ring element with midside grid points. (p. 61)

CTUBE

Defines a tension-compression-torsion tube element. (p. 59)

DLOAD

Defines a dynamic loading condition for frequency response or transient response problems as a linear combination of load sets defined via RLOAD1 or RLOAD2 entries for frequency response or TLOAD1 or TLOAD2 entries for transient response. (p. 61)

INCLUDE

Inserts an external file into the input file. The INCLUDE statement may appear anywhere within the input data file. (p. 105)

MAT4

Defines the constant or temperature dependent thermal material properties for conductivity, heat capacity, density, dynamic viscosity, heat generation, reference enthalpy and latent heat associated with a single phase change. (p. 46)

MAT5

Defines the thermal material properties for anisotropic materials. (p. 46)

MATT4

Specifies table references for temperature-dependent MAT4 material properties. (p. 46)

MATT5

Specifies temperature-dependent material properties on MAT5 entry fields via TABLEMi entries. (p. 46)

MPC

Defines a multipoint constraint equation of the form. (p. 44)

NLPARM

Defines a set of parameters for nonlinear static analysis iteration strategy. (p. 117), (p. 127)

PARAM,AUTO AUTOSPC specifies the action to take when singularities exist in the stiffness matrix [Kgg]. SPC AUTOSPC = YES means that singularities will be constrained automatically. AUTOSPC = NO means that singularities will not be constrained. (p. 110) PARAM,PRGP ST

Controls the printout of singularities. See AUTOSPC. Default = YES. (p. 113)

PARAM,SIGM A

The radiant heat flux is proportional to SIGMA*(Tgrid + TABS)4, where SIGMA is the Stefan-Boltzmann constant. Default = 0.0. (p. 111)

PARAM,TABS

TABS is used to convert units of the temperature input (oF or oC) to the absolute temperature (°R or °K). Default = 0.0. (p. 111)

PBAR

Defines the properties of a simple beam element (CBAR entry). (p. 55)

PBEAM

Defines the properties of a beam element (CBEAM entry). This element may be used to model tapered beams. (p. 57)

PBEND

Defines the properties of a curved beam, curved pipe, or elbow element (CBEND entry). (p. 56) (p. 57)

PCONV

Specifies the free convection boundary condition properties of a boundary condition surface element used for heat transfer analysis. (p. 77), (p. 81), (p. 86)

PCONVM

Specifies the forced convection boundary condition properties of a boundary condition surface element used for heat transfer analysis. (p. 78), (p. 83), (p. 86)

Main Index

331 Bulk Data Entries

Description PDAMP

Specifies the damping value of a scalar damper element using defined CDAMP1 or CDAMP3 entries. (p. 55)

PELAS

Specifies the stiffness, damping coefficient, and stress coefficient of a scalar elastic (spring) element (CELAS1 or CELAS3 entry). (p. 55)

PHBDY

Referenced by CHBDYP entries to give auxiliary geometric information for boundary condition surface elements. (p. 58), (p. 67)

PROD

Defines the properties of a rod element (CROD entry). (p. 55)

PSHELL

Defines the membrane, bending, transverse shear, and coupling properties of thin shell elements. (p. 60)

PSOLID

Defines the properties of solid elements (CHEXA, CPENTA, and CTETRA entries). (p. 61)

PTUBE

Defines the properties of a thin-walled cylindrical tube element (CTUBE entry). (p. 58)

QBDY2

Defines grid point heat flux into CHBDYi elements. (p. 71)

QBDY3

Defines a uniform heat flux load for a boundary surface. (p. 71)

QHBDY

Defines a uniform heat flux load into a set of grid points. (p. 75)

QVECT

Defines thermal vector flux from a distant source into a face of one or more CHBDYi boundary condition surface elements. (p. 72)

QVOL

Defines a rate of volumetric heat addition in a conduction element. (p. 49), (p. 75)

RADBC

Specifies a CHBDYi element face for application of radiation boundary conditions. (p. 92), (p. 93)

RADCAV

Identifies the characteristics of each radiant enclosure. (p. 94), (p. 111), (p. 111)

RADM

Defines the radiation properties of a boundary element for heat transfer analysis. (p. 72), (p. 92), (p. 93), (p. 94)

RADMT

Specifies table references for temperature dependent RADM entry radiation boundary properties. (p. 67), (p. 72), (p. 92), (p. 93), (p. 94)

RADSET

Specifies which radiation cavities are to be included for radiation enclosure analysis. (p. 94)

SLOAD

Defines concentrated static loads on scalar or grid points. (p. 75)

SPC

Defines a set of single point constraints and enforced displacements. (p. 69)

SPOINT

Defines scalar points. (p. 77), (p. 78), (p. 92)

TABLED1

Defines a tabular function for use in generating frequency-dependent and time-dependent dynamic loads. (p. 68)

TABLEM1

Defines a tabular function for use in generating temperature-dependent material properties. (p. 46), (p. 67)

TEMP

Defines temperature at grid points for determination of thermal loading, temperaturedependent material properties, or stress recovery. (p. 70)

TEMPBC

Defines the temperature boundary conditions for heat transfer analysis. Applies to steady state and transient conditions. (p. 69)

Main Index

332 Bulk Data Entries

Description TEMPD

Defines a temperature value for all grid points of the structural model which have not been given a temperature on a TEMP entry. (p. 110), (p. 113)

TLOAD1

Defines a time-dependent dynamic load or enforced motion of the form. (p. 61), (p. 68)

TSTEPNL

Defines parametric controls and data for nonlinear transient structural or heat transfer analysis. TSTEPNL is intended for SOLs 129, 159, and 99. (p. 122), (p. 127)

VIEW

Defines radiation cavity and shadowing for radiation view factor calculations. (p. 94)

VIEW3D

Defines parameters to control and/or request the Gaussian Integration method of view factor calculation for a specified cavity. (p. 111)

Main Index

MSC.Fatigue Quick Start Guide

Index Patran Interface to MSC Nastran Thermal

A Index

absolute temperature, 8, 111 ambient temperature, 7, 77, 80, 81, 85, 87 analysis, 100, 104 analysis form, 101 applied linear loads, 138, 142 Attach XDB, 133

B

bulk data entry, 105, 106, 107, 114, 329 bulk data file, 154

C

case control, 114, 128, 328 conductivity, 3 contour plots, 36, 132, 144 convergence criteria, 12, 119, 121, 123 coordinate frames, 41, 45, 106, 139 analysis coordinate frames, 41 reference coordinate frames, 41

G

database (MSC.Patran), 18, 132, 137 delete XY window, 152 direct text input, 114, 128

GEOM1, 139 GEOM2, 139 geometry creation, 21 geometry import, 40 grid points, 42

E

H

D

elements, 139 enthalpies, 138, 143 error messages, 326 executive control, 114, 328

F

file management statements, 114, 328 files, 324 film coefficient(see also heat transfer coefficient), 7 film node, 64, 78, 81, 83, 86, 89, 91 finite element mesh, 22, 40, 41

Main Index

finite element properties, 24, 40, 43, 50, 51 0D, 53 1D, 53, 54 2D, 53, 55 2D axisymmetric solid elements, 61 2D shell elements, 60 3D, 53, 55 3D solid elements, 61 beam and rod elements-general section, 55 capacitors, 55 conductors, 55 curved general section beam, 56 curved pipe section beam, 57 flow tube, 59 pipe section rod, 58 tapered section beam, 58 forced convection, 7 formats, 106 free convection, 6

heat flows, 138, 142 heat flux, 6, 138, 143, 145 heat generation, 6, 50 heat transfer coefficient, 6, 7, 78, 80, 82, 85, 86, 88, 89, 90 heats of constraint, 138, 142

I

INCLUDE files, 106 input file, 154 input file reader, 108, 114

334 Patran Interface to MSC Nastran Thermal

K

Kirchhoff’s Identity, 8

L

load cases, 98, 100 load tolerance, 12, 119, 121, 123

M

material properties, 3, 24, 40, 45 absorptivity, 8, 73, 74, 92, 93 anisotropic, 48, 49 conductivity, 3, 49 consistent units, 4 density, 4, 49 dynamic viscosity, 5, 49 emissivity, 8, 92, 93, 94 enthalpy, 5, 49 heat capacitance, 4, 49 isotropic, 47, 49 latent heat, 5, 49 orthotropic, 47, 49 specific heat, 4, 49 MSC.Nastran version, 106 MSC.Patran Analysis Manager, 103 multi-point constraints, 41, 44

N

node points, 41 nodes, 41, 106, 139 numbering options, 106

O

OEF1, 138 OPG1, 138 OQG1, 138 OUGV1, 138 output requests, 124, 126, 127, 138, 139, 142 OUTPUT2, 36, 105, 132, 136, 138, 139

P

Prandtl number, 7, 8, 49, 81, 86, 91

Main Index

R radiation ambient nodes, 64, 93 ambient space, 64, 92 enclosures, 64, 94 rate of change of enthalpies, 138, 143 read input file, 154 results, 136 results postprocessing, 36, 143 Reynolds number, 7, 8, 49, 81, 84, 85, 86, 91

S

steady-state analysis (SOL 153), 9, 35, 108 initial conditions, 11 Newton-Raphson iteration, 10 radiation parameters, 111 solution parameters, 110, 121 subcase parameters, 117, 118, 121 view factor parameters, 111, 112 Stefan-Boltzmann constant, 8, 111 subcase, 100, 103, 115, 117, 129 SUPG, 7, 49

T

temperature gradients, 138, 142, 145 temperature tolerance, 12, 118, 121, 123 thermal analysis loads and boundary conditions, 5 steady-state analysis, 9 transient analysis, 11 units, 4, 6

INDEX 335

thermal loads and BCs, 5, 40, 61 advection, forced convection, 7, 64 basic convection, 7, 32, 64 consistent units, 5 contact, 64 control nodes, 64, 72, 75, 76 convection coupled, 81 convection coupled advection, 86 convection coupled flow tube, 83 convection flow tube to ambient, 78 convection to ambient, 77 directional heat flux, 6, 63, 72, 75 directional heat flux-function of time, 74 flow tubes, 78, 83, 86 initial temperatures, 70 nodal source, 6, 63, 75 normal heat flux, 6, 29, 63, 71 radiation enclosures, 8, 64, 94 radiation to ambient nodes, 93 radiation to space, 8, 64, 92 spatial dependence, 67 surface area, 67 temperature boundary conditions, 6, 27, 63, 69 temperature dependence, 67 time dependence, 68 two application regions, 65, 81, 83, 86, 93 volumetric heat generation, 6, 47, 50, 63, 75, 76 tolerances, 105 transient analysis (SOL 159), 11, 108 initial conditions, 12 initial time step, 11, 122 solution parameters, 113 subcase parameters, 122 translation parameters, 105, 106

U

undo feature, 23

V

view factors, 9, 92, 111, 113

W

work tolerance, 12, 118, 121, 123

Main Index

X

XY plots, 132, 146, 150

336 Patran Interface to MSC Nastran Thermal

Main Index