# Multidisciplinary design optimization of film-cooled gas turbine blades

Mathematical Problems in Engineering. 1999;5(2):97-119 DOI 10.1155/S1024123X99001015

Journal Homepage

Journal Title: Mathematical Problems in Engineering

ISSN: 1024-123X (Print); 1563-5147 (Online)

Publisher: Hindawi Limited

LCC Subject Category: Technology: Engineering (General). Civil engineering (General) | Science: Mathematics

Country of publisher: United Kingdom

Language of fulltext: English

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AUTHORS

Shashishekara S. Talya (Department of Mechanical and Aerospace Engineering, Arizona State University, Tempa, AZ 85287-6106, USA)
J. N. Rajadas (Department of Manufacturing and Aeronautical Engineering Technology, Arizona State University, Tempa, AZ 85287-6106, USA)
A. Chattopadhyay (Department of Mechanical and Aerospace Engineering, Arizona State University, Tempa, AZ 85287-6106, USA)

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Time From Submission to Publication: 26 weeks

Abstract | Full Text

Design optimization of a gas turbine blade geometry for effective film cooling toreduce the blade temperature has been done using a multiobjective optimization formulation. Three optimization formulations have been used. In the first, the average blade temperature is chosen as the objective function to be minimized. An upper bound constraint has been imposed on the maximum blade temperature. In the second, the maximum blade temperature is chosen as the objective function to be minimized with an upper bound constraint on the average blade temperature. In the third formulation, the blade average and maximum temperatures are chosen as objective functions. Shape optimization is performed using geometric parameters associated with film cooling and blade external shape. A quasi-three-dimensional Navierâ€“Stokes solver for turbomachinery flows is used to solve for the flow field external to the blade with appropriate modifications to incorporate the effect of film cooling. The heat transfer analysis for temperature distribution within the blade is performed by solving the heat diffusion equation using the finite element method. The multiobjective Kreisselmeierâ€“Steinhauser function approach has been used in conjunction with an approximate analysis technique for optimization. The results obtained using both formulations are compared with reference geometry. All three formulations yield significant reductions in blade temperature with the multiobjective formulation yielding largest reduction in blade temperature.