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Internal Cooling Passage Heat Transfer Near the Entrance to a Film Cooling Hole: Experimental and Computational Results FREE

[+] Author Affiliations
A. R. Byerley

United States Air Force Academy, CO

T. V. Jones, P. T. Ireland

Oxford University, Oxford, England

Paper No. 92-GT-241, pp. V004T09A021; 12 pages
doi:10.1115/92-GT-241
From:
  • ASME 1992 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 4: Heat Transfer; Electric Power; Industrial and Cogeneration
  • Cologne, Germany, June 1–4, 1992
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7896-5
  • Copyright © 1992 by ASME

abstract

Detailed heat transfer measurements were made near the entrance to a single film cooling hole using a transient liquid crystal technique in a large scale (100X) model. The hole inclination angle and flow extraction rate were varied across a range representative of actual engine conditions. Local values of heat transfer were found to exceed 6 times the levels associated with fully developed, turbulent channel flow. The region of maximum heat transfer enhancement occurred downstream of the hole entrance. Computational and experimental flow diagnostics were performed to investigate the mechanisms responsible for the observed heat transfer distributions. The removal of the upstream boundary layer and the downwash created by a vortex pair were found to be important phenomena.

Copyright © 1992 by ASME
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