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RESEARCH PAPERS

An Experimental Study of Heat Transfer and Film Cooling on Low Aspect Ratio Turbine Nozzles

[+] Author and Article Information
K. Takeishi, M. Matsuura, S. Aoki, T. Sato

Takasago R&D Center, Mitsubishi Heavy Industries, Ltd., Takasago, Japan

J. Turbomach 112(3), 488-496 (Jul 01, 1990) (9 pages) doi:10.1115/1.2927684 History: Received January 27, 1989; Online June 09, 2008

Abstract

The effects of the three-dimensional flow field on the heat transfer and the film cooling on the endwall, suction, and pressure surface of an airfoil were studied using a low speed, fully annular, low aspect h/c = 0.5 vane cascade. The predominant effects on the horseshoe vortex, secondary flow, and nozzle wake of increases in the heat transfer and decreases in the film cooling on the suction vane surface and the endwall were clearly demonstrated. In addition, it was demonstrated that secondary flow has little effect on the pressure surface. Pertinent flow visualization of the flow passage was also carried out for better understanding of these complex phenomena. Heat transfer and film cooling on the fully annular vane passage surface are discussed.

Copyright © 1990 by The American Society of Mechanical Engineers
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