Measurement and Analyses of Heat Flux Data in a Turbine Stage: Part II—Discussion of Results and Comparison With Predictions

[+] Author and Article Information
M. G. Dunn, W. J. Rae

Aerodynamic Research Department, Calspan Advanced Technology Center, Buffalo, N.Y. 14225

J. L. Holt

Air Force Wright Aeronautical Laboratories, Aero Propulsion Laboratory, Wright-Patterson AFB, Ohio 45433

J. Eng. Gas Turbines Power 106(1), 234-240 (Jan 01, 1984) (7 pages) doi:10.1115/1.3239540 History: Received December 27, 1982; Online October 15, 2009


Parts I and II of this paper report the measurement and analysis of detailed heat flux distributions obtained on the nozzle guide vane (NGV), rotor, and shroud of the full-stage rotating turbine of the Garrett TFE 731-2 engine. Part I is devoted to a description of the experimental apparatus and the data analysis procedure. Part II is concerned with the experimental results and their comparison with predictions obtained using a flat-plate technique and with predictions obtained using STAN5. Measurements were performed for values of the ratio of wall temperature to total temperature equal to 0.21, 0.33, and 0.53. For the NGV airfoil and rotor blade, the influence of wall temperature ratio on the Stanton number is shown to be generally 10 percent or less. For the NGV airfoil, and the rotor blade pressure surface, the flat-plate turbulent-flow prediction provides a reasonably good comparison with the data. With the rotor operating, the state of the boundary layer generally appears to be turbulent for both the NGV airfoil and the rotor blade. Predictions obtained using STAN5 confirm that boundary layer transition occurs at a value of Reθ substantially less than 200.

Copyright © 1984 by ASME
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