Multidisciplinary design optimization procedure for improved design of a cooled gas turbine blade

Research output: Contribution to journalArticle

41 Scopus citations

Abstract

A multidisciplinary optimization procedure for gas turbine blade design has been developed and demonstrated on a generic 3-D blade. The blade is cooled both internally and externally (film cooling). Aerodynamic and heat transfer design criteria are integrated along with various constraints on the blade geometry. The blade is divided into numerous spanwise sections and each section is represented by a Bezier-Bernstein polynomial. A comprehensive solver for 3-D Navier-Stokes equations is used for the viscous flow calculations. The finite element method is used to obtain the blade interior temperatures. The average blade temperature and maximum blade temperature at each spanwise section are minimized, with aerodynamic and geometric constraints on the blade geometry. The constrained multiobjective optimization problem is solved using the Kreisselmeier-Steinhauser function approach. The results for a generic turbine blade design problem show significant improvements after optimization.

Original languageEnglish (US)
Pages (from-to)175-194
Number of pages20
JournalEngineering Optimization
Volume34
Issue number2
DOIs
StatePublished - Mar 2002

Keywords

  • Film cooling
  • Internal cooling
  • Multidisciplinary optimization
  • Turbine blade
  • Turbomachinery

ASJC Scopus subject areas

  • Computer Science Applications
  • Control and Optimization
  • Management Science and Operations Research
  • Industrial and Manufacturing Engineering
  • Applied Mathematics

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