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An Experimental Investigation of Convective Heat Transfer at the Leading Edge of a Gas Turbine Airfoil FREE

[+] Author Affiliations
S. Gendron, N. J. Marchand, C. Korn

Ecole Polytechnique, Montreal, Canada

J. P. Immarigeon, J. J. Kacprzynski

National Research Council of Canada, Ottawa, Canada

Paper No. 92-GT-248, pp. V004T09A028; 10 pages
doi:10.1115/92-GT-248
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

This paper describes the experimental methods used to determine the surface temperatures and heat-transfer coefficients at the leading edge, and elsewhere over the surface, of a specially designed double-edge wedge shell specimen subjected to cyclic heating in a high velocity hot gas stream generated by a burner rig. The methods included temperature measurements with thermocouples (embedded below the surface) as well as surface temperature measurements by optical pyrometry. The experiments were carried-out at gas temperatures between 806 to 1323 °C and velocities in the range from Mach 0.32 to Mach 0.39. The calibration procedures for each method, the various testing conditions to which the airfoil-like specimen was exposed and the results pertaining to the determination of the surface temperatures and heat-transfer coefficients are described and discussed.

Copyright © 1992 by ASME
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