Measurements of Heat Transfer Distribution Over the Surfaces of Highly Loaded Turbine Nozzle Guide Vanes

[+] Author and Article Information
D. A. Nealy, M. S. Mihelc, L. D. Hylton

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

H. J. Gladden

NASA, Lewis Research Center, Cleveland, Ohio 44135

J. Eng. Gas Turbines Power 106(1), 149-158 (Jan 01, 1984) (10 pages) doi:10.1115/1.3239528 History: Received December 20, 1982; Online October 15, 2009


The results of an experimental study of aerodynamic (surface velocity) and heat transfer distributions over the surfaces of two different, highly loaded, low-solidity contemporary turbine vane designs are presented. The aerodynamic configurations of the two vanes were carefully selected to emphasize fundamental differences in the character of the suction surface pressure distributions and the consequent effect on surface heat transfer distributions. The experimental measurements were made in moderate-temperature, three-vane cascades under steady-state conditions. The principal independent parameters (Mach number, Reynolds number, turbulence intensity, and wall-to-gas temperature ratio) were varied over ranges consistent with actual engine operation, and the test matrix was structured to provide an assessment of the independent influence of each parameter. These measurements are intended to serve as verification data for a parallel analytical code development effort. The results of this parallel effort are briefly reviewed, and the principal conclusions to date are summarized.

Copyright © 1984 by ASME
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