Multidisciplinary analysis and design optimization procedure for cooled gas turbine blades

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

15 Scopus citations

Abstract

A multidisciplinary design optimization procedure for gas turbine blade design has been developed and demonstrated on a generic 3-D blade. Aerodynamic, heat transfer, structural and modal design objectives are integrated along with various constraints on the blade geometry for multidisciplinary shape optimization of the 3-D blade. Effective blade cooling mechanisms are used to cool the blade both internally and externally (film cooling). The blade surface geometry is defined by Bezier-Bernstein 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, maximum blade temperature and the blade weight are minimized with aerodynamic, structural, modal and geometric constraints. 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 publication8th Symposium on Multidisciplinary Analysis and Optimization
StatePublished - 2000
Event8th Symposium on Multidisciplinary Analysis and Optimization 2000 - Long Beach, CA, United States
Duration: Sep 6 2000Sep 8 2000

Other

Other8th Symposium on Multidisciplinary Analysis and Optimization 2000
CountryUnited States
CityLong Beach, CA
Period9/6/009/8/00

ASJC Scopus subject areas

  • Aerospace Engineering
  • Mechanical Engineering

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