Abstract
A multidisciplinary design optimization procedure for the design of turbine blades has been developed. The blade cross section (airfoil) is designed for improved aerodynamic performance via shape optimization. The focus has been on shaping the blade geometry such that the parameter that characterizes the accelerating flow about the blade is modified to delay the onset of transition to turbulence. The airfoil shape is modeled using analytical splines. The spline parameters and the blade geometric parameters are used as design variables in the optimization procedure. A mulliobjective optimization formulation technique, based on the Kreisselmeier-Steinhauser function, is used to improve the acceleration parameter at several control points along the airfoil surface. Aerodynamic analysis is performed using a two-dimensional panel code. The acceleration parameter has been used as the objective function during optimization. Results obtained show improvements in the acceleration parameter distribution of the optimum configuration.
| Original language | English (US) |
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| Title of host publication | 6th Symposium on Multidisciplinary Analysis and Optimization |
| Publisher | American Institute of Aeronautics and Astronautics Inc, AIAA |
| Pages | 1372-1381 |
| Number of pages | 10 |
| State | Published - 1996 |
| Event | 6th AIAA/NASA/ISSMO Symposium on Multidisciplinary Analysis and Optimization, 1996 - Bellevue, United States Duration: Sep 4 1996 → Sep 6 1996 |
Other
| Other | 6th AIAA/NASA/ISSMO Symposium on Multidisciplinary Analysis and Optimization, 1996 |
|---|---|
| Country/Territory | United States |
| City | Bellevue |
| Period | 9/4/96 → 9/6/96 |
ASJC Scopus subject areas
- Aerospace Engineering
- Mechanical Engineering