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RESEARCH PAPERS

An Experimental Investigation of Endwall Heat Transfer and Aerodynamics in a Linear Vane Cascade

[+] Author and Article Information
R. E. York

Aerothermodynamics Research, Detroit Diesel Allison Division, General Motors Corporation, Indianapolis, Ind. 46206

L. D. Hylton

Experimental Heat Transfer, Detroit Diesel Allison Division, General Motors Corporation, Indianapolis, Ind. 46206

M. S. Mihelc

Detroit Diesel Allison Division, General Motors Corporation, Indianapolis, Ind. 46206

J. Eng. Gas Turbines Power 106(1), 159-167 (Jan 01, 1984) (9 pages) doi:10.1115/1.3239529 History: Received December 20, 1982; Online October 15, 2009

Abstract

The purpose of this experimental investigation was to produce a data base of end-wall heat transfer data under conditions that simulate those in the passage of the first-stage stator in advanced turbine engines. The data base is intended to be sufficiently complete to provide verification data for refined computational models, and to provide a basis for advanced core engine endwall cooling designs. A linear, two-dimensional cascade was used to generate the data base. The test plan provided data to examine the effects of exit Mach number, exit Reynolds number, inlet boundary layer thickness, gas-to-wall temperature ratio, inlet pressure gradients, and inlet temperature gradients. The data generated consist of inlet, intrapassage, and exit aerodynamic data plus intrapassage endwall heat flux, adiabatic wall temperature measurements, and inlet turbulence data.

Copyright © 1984 by ASME
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