Abstract
A multidisciplinary optimization procedure for gas turbine blade design, has been developed and demonstrated on a generic blade. The blade is cooled both internally and externally (film cooling). Aerodynamic and heat transfer design objectives are integrated along with various constraints on the blade geometry. The airfoil shape is represented by Bezier-Bemstein polynomials, which result in a relatively smaller number of design variables for the optimization. Thin layer Navier-Stokes equation is used for the viscous flow calculations. Poisson's equation is solved to obtain the grid for the flow solution. The finite element analysis is used to obtain the blade interior temperatures. Total pressure, exit kinetic energy loss, average blade temperature and maximum blade temperature are minimized, with constraints on the blade geometry. The constrained multi objective optimization problem is solved using the Kreisselmeier-Steinfaauser (K-S) function approach. The results for the numerical example show significant improvements after optimization.
| Original language | English (US) |
|---|---|
| Title of host publication | 37th Aerospace Sciences Meeting and Exhibit |
| Publisher | American Institute of Aeronautics and Astronautics Inc, AIAA |
| State | Published - 1999 |
| Event | 37th Aerospace Sciences Meeting and Exhibit, 1999 - Reno, United States Duration: Jan 11 1999 → Jan 14 1999 |
Other
| Other | 37th Aerospace Sciences Meeting and Exhibit, 1999 |
|---|---|
| Country/Territory | United States |
| City | Reno |
| Period | 1/11/99 → 1/14/99 |
ASJC Scopus subject areas
- Space and Planetary Science
- Aerospace Engineering