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Improving Film Cooling Performance Using Airfoil Contouring

[+] Author Affiliations
Atul Kohli

Pratt & Whitney, East Hartford, CT

David G. Bogard

University of Texas at Austin, Austin, TX

Paper No. GT2006-90852, pp. 669-676; 8 pages
doi:10.1115/GT2006-90852
From:
  • ASME Turbo Expo 2006: Power for Land, Sea, and Air
  • Volume 3: Heat Transfer, Parts A and B
  • Barcelona, Spain, May 8–11, 2006
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 0-7918-4238-X | eISBN: 0-7918-3774-2
  • Copyright © 2006 by ASME

abstract

In this study, a CFD-based optimization process is used to change the contour of the airfoil near a suction side cooling hole in order to improve its film effectiveness characteristics. An overview of the optimization process, which includes automated geometry, grid generation and CFD analyses is provided. From the results for the optimized geometry it is clear that the detachment of the cooling jet is much reduced and the cooling jet spread in the spanwise direction is increased substantially. The new external contour was then tested in a low-speed wind tunnel to provide a direct measure of the predictive capability. Comparisons to verification test data indicate that good agreement was achieved for both pressure and film cooling effectiveness behavior. This study proves that despite its limitations, current RANS methodology can be used a viable design tool and lead to innovative concepts for improving film cooling effectiveness.

Copyright © 2006 by ASME
Topics: Cooling , Airfoils

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