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

[+] Author and Article Information
S. P. Harasgama, E. T. Wedlake

Royal Aerospace Establishment, Propulsion Department, Pyestock, Farnborough Hampshire, GU14 OLS, United Kingdom

J. Turbomach 113(3), 384-391 (Jul 01, 1991) (8 pages) doi:10.1115/1.2927887 History: Received January 11, 1990; Online June 09, 2008


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 percent axial chord (midspan) 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 © 1991 by The American Society of Mechanical Engineers
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