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RESEARCH PAPERS

Film Cooling Research on the Endwall of a Turbine Nozzle Guide Vane in a Short Duration Annular Cascade: Part 1—Experimental Technique and Results

[+] Author and Article Information
S. P. Harasgama, C. D. Burton

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

J. Turbomach 114(4), 734-740 (Oct 01, 1992) (7 pages) doi:10.1115/1.2928026 History: Received March 04, 1991; Online June 09, 2008

Abstract

Heat transfer and aerodynamic measurements have been made on the endwalls of an annular cascade of turbine nozzle guide vanes in the presence of film cooling. The results indicate that high levels of cooling effectiveness can be achieved on the endwalls of turbine nozzle guide vanes (NGV). The NGV were operated at the correct engine nondimensional conditions of Reynolds number, Mach number, gas-to-wall temperature ratio, and gas-to-coolant density ratio. The results show that the secondary flow and horseshoe vortex act on the coolant, which is convected toward the suction side of the NG V endwall passage. Consequently the coolant does not quite reach the pressure side/casing trailing edge, leading to diminished cooling in this region. Increasing the blowing rate from 0.52 to 1.1 results in significant reductions in heat transfer to the endwall. Similar trends are evident when the coolant temperature is reduced. Measured heat transfer rates indicate that over most of the endwall region the film cooling reduces the Nusselt number by 50 to 75 percent.

Copyright © 1992 by The American Society of Mechanical Engineers
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