Experimental Heat Transfer Investigation Around the Film-Cooled Leading Edge of a High-Pressure Gas Turbine Rotor Blade

[+] Author and Article Information
C. Camci, T. Arts

von Karman Institute for Fluid Dynamics, B-1640 Rhode Saint Genése, Belgium

J. Eng. Gas Turbines Power 107(4), 1016-1021 (Oct 01, 1985) (6 pages) doi:10.1115/1.3239805 History: Received December 27, 1984; Online October 15, 2009


This paper describes an experimental heat transfer investigation around the leading edge of a high-pressure film-cooled gas turbine rotor blade. The measurements were performed in the VKI isentropic compression tube facility using platinum thin film gauges painted on a blade made of machinable glass ceramic. Free-stream to wall temperature ratio, Reynolds, and Mach numbers were selected from actual aeroengines conditions. Heat transfer data obtained without and with film cooling in a stationary frame are presented. The effects of coolant to free-stream mass weight ratio and temperature ratio were successively investigated. Heat transfer modifications due to incidence angle variations were interpreted with the aid of inviscid flow calculation methods.

Copyright © 1985 by ASME
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