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Predicted Turbine Heat Transfer for a Range of Test Conditions FREE

[+] Author Affiliations
R. J. Boyle, B. L. Lucci

NASA Lewis Research Center, Cleveland, OH

Paper No. 96-GT-304, pp. V004T09A036; 16 pages
doi:10.1115/96-GT-304
From:
  • ASME 1996 International Gas Turbine and Aeroengine Congress and Exhibition
  • Volume 4: Heat Transfer; Electric Power; Industrial and Cogeneration
  • Birmingham, UK, June 10–13, 1996
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7875-0
  • Copyright © 1996 by ASME

abstract

Comparisons are shown between predictions and experimental data for blade and end wall heat transfer. The comparisons are given for both vane and rotor geometries over an extensive range of Reynolds and Mach numbers. Comparisons are made with experimental data from a variety of sources. A number of turbulence models are available for predicting blade surface heat transfer, as well as aerodynamic performance. The results of an investigation to determine the turbulence model which gives the best agreement with experimental data over a wide range of test conditions are presented.

Copyright © 1996 by ASME
This article is only available in the PDF format.

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