Fully Scaled Transonic Turbine Rotor Heat Transfer Measurements

[+] Author and Article Information
G. R. Guenette, A. H. Epstein, M. B. Giles, R. Haimes

Gas Turbine Laboratory, Massachusetts Institute of Technology, Cambridge, MA 02139

R. J. G. Norton

Rolls-Royce Inc., Atlanta, GA 30349

J. Turbomach 111(1), 1-7 (Jan 01, 1989) (7 pages) doi:10.1115/1.3262231 History: Received November 18, 1987; Online November 09, 2009


The heat transfer to an uncooled transonic singlestage turbine has been measured in a short-duration facility, which fully simulates all the nondimensional quantities of interest for fluid flow and heat transfer (Reynolds number, Prandtl number, Rossby number, temperature ratios, and corrected speed and weight flow). Data from heat flux gages about the midspan of the rotor profile, measured from d-c to more than 10 times blade passing frequency (60 kHz), are presented in both time-resolved and mean heat transfer form. These rotating blade data are compared to previously published heat transfer measurements taken at Oxford University on the same profile in a two-dimensional cascade with bar passing to simulate blade row interaction effects. The results are qualitatively quite similar at midspan. The data are also compared to a two-dimensional Navier–Stokes calculation of the blade mean section and the implications for turbine design are discussed.

Copyright © 1989 by ASME
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