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RESEARCH PAPERS

Experimental Determination of Stator Endwall Heat Transfer

[+] Author and Article Information
R. J. Boyle, L. M. Russell

NASA Lewis Research Center, Cleveland, OH 44135

J. Turbomach 112(3), 547-558 (Jul 01, 1990) (12 pages) doi:10.1115/1.2927693 History: Received February 01, 1989; Online June 09, 2008

Abstract

Local Stanton numbers were experimentally determined for the endwall surface of a turbine vane passage. A six-vane linear cascade having vanes with an axial chord of 13.81 cm was used. Results were obtained for Reynolds numbers based on inlet velocity and axial chord between 73,000 and 495,000. The test section was connected to a low-pressure exhaust system. Ambient air was drawn into the test section; inlet velocity was controlled up to a maximum of 59.4 m/s. The effect of the inlet boundary layer thickness on the endwall heat transfer was determined for a range of test section flow rates. The liquid crystal measurement technique was used to measure heat transfer. Endwall heat transfer was determined by applying electrical power to a foil heater attached to the cascade endwall. The temperature at which the liquid crystal exhibited a specific color was known from a calibration test. Lines showing this specific color were isotherms, and because of uniform heat generation they were also lines of nearly constant heat transfer. Endwall static pressures were measured, along with surveys of total pressure and flow angles at the inlet and exit of the cascade.

Copyright © 1990 by The American Society of Mechanical Engineers
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