Development of multi disciplinary optimization procedure for gas turbine blade design

S. S. Talya, R. Jha, Aditi Chattopadhyay, John Rajadas

Research output: Chapter in Book/Report/Conference proceedingConference contribution

3 Citations (Scopus)

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 languageEnglish (US)
Title of host publication37th Aerospace Sciences Meeting and Exhibit
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
StatePublished - 1999
Event37th Aerospace Sciences Meeting and Exhibit, 1999 - Reno, United States
Duration: Jan 11 1999Jan 14 1999

Other

Other37th Aerospace Sciences Meeting and Exhibit, 1999
CountryUnited States
CityReno
Period1/11/991/14/99

Fingerprint

turbine blades
gas turbines
blades
turbine
Turbomachine blades
Gas turbines
optimization
gas
Geometry
Poisson equation
Constrained optimization
Viscous flow
Multiobjective optimization
Airfoils
geometry
Kinetic energy
Temperature
Navier Stokes equations
viscous flow
temperature

ASJC Scopus subject areas

  • Space and Planetary Science
  • Aerospace Engineering

Cite this

Talya, S. S., Jha, R., Chattopadhyay, A., & Rajadas, J. (1999). Development of multi disciplinary optimization procedure for gas turbine blade design. In 37th Aerospace Sciences Meeting and Exhibit [A 99-0364] American Institute of Aeronautics and Astronautics Inc, AIAA.

Development of multi disciplinary optimization procedure for gas turbine blade design. / Talya, S. S.; Jha, R.; Chattopadhyay, Aditi; Rajadas, John.

37th Aerospace Sciences Meeting and Exhibit. American Institute of Aeronautics and Astronautics Inc, AIAA, 1999. A 99-0364.

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Talya, SS, Jha, R, Chattopadhyay, A & Rajadas, J 1999, Development of multi disciplinary optimization procedure for gas turbine blade design. in 37th Aerospace Sciences Meeting and Exhibit., A 99-0364, American Institute of Aeronautics and Astronautics Inc, AIAA, 37th Aerospace Sciences Meeting and Exhibit, 1999, Reno, United States, 1/11/99.
Talya SS, Jha R, Chattopadhyay A, Rajadas J. Development of multi disciplinary optimization procedure for gas turbine blade design. In 37th Aerospace Sciences Meeting and Exhibit. American Institute of Aeronautics and Astronautics Inc, AIAA. 1999. A 99-0364
Talya, S. S. ; Jha, R. ; Chattopadhyay, Aditi ; Rajadas, John. / Development of multi disciplinary optimization procedure for gas turbine blade design. 37th Aerospace Sciences Meeting and Exhibit. American Institute of Aeronautics and Astronautics Inc, AIAA, 1999.
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