An integrated multidisciplinary design optimization proce1 for cooled gas turbine blades

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

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 blade surface geometry is defined by Bezier-Bemstein polynomials. A comprehensive 3-D Navier-Stokes equation solver is used for flow field evaluation and finite element method is used to obtain the blade interior temperatures. The average blade temperature and maximum blade temperature are minimized, with aerodynamic and geometric constraints on the blade. The constrained multiobjective optimization problem is solved using the Kreisselmeier-Steinhauser (K-S) function approach. The results for the numerical example show significant improvements after optimization.

Original languageEnglish (US)
Title of host publication41st Structures, Structural Dynamics, and Materials Conference and Exhibit
StatePublished - 2000
Event41st Structures, Structural Dynamics, and Materials Conference and Exhibit 2000 - Atlanta, GA, United States
Duration: Apr 3 2000Apr 6 2000

Other

Other41st Structures, Structural Dynamics, and Materials Conference and Exhibit 2000
CountryUnited States
CityAtlanta, GA
Period4/3/004/6/00

ASJC Scopus subject areas

  • Civil and Structural Engineering
  • Mechanics of Materials
  • Building and Construction
  • Architecture

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  • Cite this

    Talya, S. S., Chattopadhyay, A., & Rajadas, J. (2000). An integrated multidisciplinary design optimization proce1 for cooled gas turbine blades. In 41st Structures, Structural Dynamics, and Materials Conference and Exhibit