Abstract
A multidisciplinary design optimization framework for cooled gas turbine blade design has been developed and demonstrated using three test cases. Aerodynamic, heat transfer, structural and modal design objectives are integrated along with various constraints for multidisciplinary shape optimization of the three dimensional blade. The average and maximum blade temperatures, blade weight, pressure losses and kinetic energy efficiency are some of the design objectives that have been addressed. Both internal and external cooling mechanisms are included in the blade analysis part of the framework. Analyses for flow field range from simple panel methods to comprehensive 3-D Navier-Stokes equations and finite element method is used to evaluate the blade interior temperatures. The blade stresses and modal frequencies are evaluated using the ANSYS software. The multiobjective optimization problem is solved using the Kreisselmeier-Steinhauser (K-S) function approach. The results show the versatility and usefulness of the design optimization framework.
| Original language | English (US) |
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| Title of host publication | 9th AIAA/ISSMO Symposium on Multidisciplinary Analysis and Optimization |
| Publisher | American Institute of Aeronautics and Astronautics Inc. |
| State | Published - 2002 |
| Event | 9th AIAA/ISSMO Symposium on Multidisciplinary Analysis and Optimization 2002 - Atlanta, GA, United States Duration: Sep 4 2002 → Sep 6 2002 |
Other
| Other | 9th AIAA/ISSMO Symposium on Multidisciplinary Analysis and Optimization 2002 |
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| Country/Territory | United States |
| City | Atlanta, GA |
| Period | 9/4/02 → 9/6/02 |
ASJC Scopus subject areas
- Aerospace Engineering
- Mechanical Engineering