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RESEARCH PAPERS

Heat Transfer in Rotating Serpentine Passages With Trips Normal to the Flow

[+] Author and Article Information
J. H. Wagner, B. V. Johnson

United Technologies Research Center, East Hartford, CT 06108

R. A. Graziani

Group Engineering, Pratt & Whitney, East Hartford, CT 06108

F. C. Yeh

NASA Lewis Research Center, Cleveland, OH 44135

J. Turbomach 114(4), 847-857 (Oct 01, 1992) (11 pages) doi:10.1115/1.2928038 History: Received March 04, 1991; Online June 09, 2008

Abstract

Experiments were conducted to determine the effects of buoyancy and Coriolis forces on heat transfer in turbine blade internal coolant passages. The experiments were conducted with a large-scale, multipass, heat transfer model with both radially inward and outward flow. Trip strips on the leading and trailing surfaces of the radial coolant passages were used to produce the rough walls. An analysis of the governing flow equations showed that four parameters influence the heat transfer in rotating passages: coolant-to-wall temperature ratio, Rossby number, Reynolds number, and radius-to-passage hydraulic diameter ratio. The first three of these four parameters were varied over ranges that are typical of advanced gas turbine engine operating conditions. Results were correlated and compared to previous results from stationary and rotating similar models with trip strips. The heat transfer coefficients on surfaces, where the heat transfer increased with rotation and buoyancy, varied by as much as a factor of four. Maximum values of the heat transfer coefficients with high rotation were only slightly above the highest levels obtained with the smooth wall model. The heat transfer coefficients on surfaces where the heat transfer decreased with rotation, varied by as much as a factor of three due to rotation and buoyancy. It was concluded that both Coriolis and buoyancy effects must be considered in turbine blade cooling designs with trip strips and that the effects of rotation were markedly different depending upon the flow direction.

Copyright © 1992 by The American Society of Mechanical Engineers
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