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Small Diameter Film Cooling Holes: Wall Convective Heat Transfer FREE

[+] Author Affiliations
G. E. Andrews, M. Alikhanizadeh, A. A. Asere, C. I. Hussain, M. S. Khoshkbar Azari, M. C. Mkpadi

University of Leeds, Leeds, UK

Paper No. 88-GT-225, pp. V001T01A081; 8 pages
doi:10.1115/88-GT-225
From:
  • ASME 1988 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 1: Turbomachinery
  • Amsterdam, The Netherlands, June 6–9, 1988
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7918-4
  • Copyright © 1988 by ASME

abstract

The wall heat transfer resulting from small diameter holes drilled at 90° through gas turbine combustion chamber and turbine blade walls is considered. Available information is briefly reviewed and shown to generally omit the hole approach surface heat transfer and to relate only to the internal hole heat transfer. Experimental techniques are described for the determination of the overall heat transfer in a metal plate with a large number of coolant holes drilled at 90°. The results are compared with conventional short-tube internal heat transfer measurements and shown to involve much higher heat transfer rates and this mainly resulted from the additional hole approach flow heat transfer.

Copyright © 1988 by ASME
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