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Heat Transfer and Aerodynamics of a High Rim Speed Turbine Nozzle Guide Vane Tested in the RAE Isentropic Light Piston Cascade (ILPC) PUBLIC ACCESS

[+] Author Affiliations
S. P. Harasgama, E. T. Wedlake

Royal Aerospace Establishment, Pyestock, Farnborough, UK

Paper No. 90-GT-041, pp. V004T09A008; 8 pages
doi:10.1115/90-GT-041
From:
  • ASME 1990 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 4: Heat Transfer; Electric Power; Industrial and Cogeneration
  • Brussels, Belgium, June 11–14, 1990
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7907-8
  • Copyright © 1990 by ASME

abstract

Detailed heat transfer and aerodynamic measurements have been made on an annular cascade of highly loaded nozzle guide vanes. The tests were carried out in an Isentropic Light Piston test facility at engine representative Reynolds number, Mach number and gas-to-wall temperature ratio.

The aerodynamics indicate that the vane has a weak shock at 65–70% axial chord (mid span) with a peak Mach number of 1.14. The influence of Reynolds number and Mach number on the Nusselt number distributions on the vane and endwall surfaces are shown to be significant. Computational techniques are used for the interpretation of test data.

Copyright © 1990 by ASME
This article is only available in the PDF format.

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