An Experimental Convective Heat Transfer Investigation Around a Film-Cooled Gas Turbine Blade

[+] Author and Article Information
C. Camci

Aerospace Engineering Department, The Pennsylvania State University, University Park, PA 16802

T. Arts

von Karman Institute for Fluid Dynamics, Rhode Saint Genèse, Belgium

J. Turbomach 112(3), 497-503 (Jul 01, 1990) (7 pages) doi:10.1115/1.2927685 History: Received May 01, 1989; Online June 09, 2008


The present paper deals with an experimental convective heat transfer investigation around a film-cooled, high-pressure gas turbine rotor blade mounted in a stationary, linear cascade arrangement. The measurements were performed in the von Karman Institute Isentropic Light Piston Compression Tube facility. The test blade was made of Macor glass ceramic and was instrumented with thin film gages. The coolant flow was ejected simultaneously through the leading edge (three rows of holes), the suction side (two rows of holes), and the pressure side (one row of holes). The effects of overall mass weight ratio, coolant to free-stream temperature ratio, and free-stream turbulence were successively investigated.

Copyright © 1990 by The American Society of Mechanical Engineers
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