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TECHNICAL BRIEFS

Development of Taylor-Görtler Vortices Over the Pressure Surface of a Turbine Blade

[+] Author and Article Information
H. P. Wang

Pratt & Whitney

S. J. Olson

TSI, Inc.

R. J. Goldstein

Department of Mechanical Engineering, University of Minnesota, Minneapolis, Minnesota

J. Heat Transfer 127(5), 540-543 (May 25, 2005) (4 pages) doi:10.1115/1.1865219 History: Received March 01, 2004; Revised October 31, 2004; Online May 25, 2005
Copyright © 2005 by ASME
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References

Wang,  H. P., Goldstein,  R. J., and Olson,  S. J., 1999, “Effect of High Free-Stream Turbulence with Large Length Scale on Blade Heat/Mass Transfer,” ASME J. Turbomach., 121, pp. 1–8.
Goldstein,  R. J., and Cho,  H. H., 1995, “A Review of Mass Transfer Measurements using Naphthalene Sublimation,” Exp. Therm. Fluid Sci., 10, pp. 416–434.
Coleman, H. W., and Steel, W. G., Jr., 1999, Experimentation and Uncertainty Analysis for Engineers, 2nd ed., Wiley, New York.
Sparrow,  E. M., Quack,  H., and Boerner,  C. J., 1970, “Local Nonsilmilarity Boundary-Layer Solutions,” AIAA J., 8, pp. 1936–1942.
Liepmann, H. W., 1945, “Investigation of Boundary Layer Transition on Concave Walls,” NACA Wartime Report.

Figures

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Photographs of Taylor-Görtler vortices on a pressure surface at Reex=5.2×105 (scale in centimeters). (a) Smooth leading edge and (b) Rough leading edge.
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Velocity profiles measured along pressure surface for Reex=5.2×105
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Distribution of measured and calculated boundary layer thickness, wavelength, and Görtler number for Reex=5.2×105
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Average Sherwood variation along blade surface at Reex=5.2×105
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Three-dimensional surface plots for Reex=5.2×105. (a) Reex=5.05×105, smooth LE, (b) Reex=5.28×105, smooth LE, (c) Reex=5.20×105, distributed rough LE, and (d) Reex=5.19×105, distorted rough LE.

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