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Computations of a Film Cooled Turbine Rotor Blade With Non-Uniform Inlet Temperature Distribution Using a Three-Dimensional Viscous Procedure FREE

[+] Author Affiliations
B. Weigand, S. P. Harasgama

ABB Power Generation Limited, Baden, Switzerland

Paper No. 94-GT-015, pp. V004T09A004; 9 pages
doi:10.1115/94-GT-015
From:
  • ASME 1994 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 4: Heat Transfer; Electric Power; Industrial and Cogeneration
  • The Hague, Netherlands, June 13–16, 1994
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7886-6
  • Copyright © 1994 by ASME

abstract

A numerical investigation of film cooling on a turbine rotor blade has been carried out. The computations were performed with a 3D-Navier-Stokes code utilizing an unstructured solution adaptive grid methodology (Dawes (1992)). The code uses a low Reynolds number k-epsilon model for prescribing the Reynolds stresses. The results show that there is a significant interaction between the coolant flow and the secondary flow near the hub and the tip of the turbine blade. It was observed that, by blowing on the pressure side of the blade, some of the cooling air was transported through the tip gap of the blade to the suction side of the blade where the coolant flow interacts with the secondary flow field.

When radial inlet temperature distortion (RTD) is included, it was possible to show that there were some further modifications of the film cooling effectiveness on the rotating blade near the pressure side tip. This is believed to be mostly because of the changed secondary flow system due to the radial inlet temperature profile.

Copyright © 1994 by ASME
This article is only available in the PDF format.

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