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TECHNICAL PAPERS

Toward Improved Film Cooling Prediction

[+] Author and Article Information
G. Medic, P. A. Durbin

Mechanical Engineering Department, Stanford University, Stanford, CA 94305-3030

J. Turbomach 124(2), 193-199 (Apr 09, 2002) (7 pages) doi:10.1115/1.1458021 History: Received March 20, 2001; Revised October 15, 2001; Online April 09, 2002
Copyright © 2002 by ASME
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References

Medic,  G., and Durbin,  P. A., 2002, “Toward Improved Prediction of Heat Transfer on Turbine Blades,” ASME J. Turbomach., 124, pp. 187–192.
Launder, B. E., and Kato, M., 1993, Modelling Flow-Induced Oscillations in Turbulent Flow Around a Square Cylinder,” ASME FED 157 , pp. 189–199.
Durbin,  P. A., 1996, “On the k−ε Stagnation Point Anomaly,” Int. J. Heat Fluid Flow, 17, pp. 89–90.
Leylek,  J. H., and Zerkle,  R. D., 1994, “Discrete-Jet Film Cooling: A Comparison of Computational Results with Experiments,” ASME J. Turbomach., 116, pp. 358–368.
Camci, C., 1985, Theoretical and Experimental Investigation of Film Cooling Heat Transfer on a Gas Turbine Blade, Ph.D. thesis, Von Karman Institute for Fluid Dynamics and University of Leuven, Belgium.
Camci,  C., and Arts,  T., 1985a, “Short Duration Measurements and Numerical Simulation of Heat Transfer Along the Suction Side of a Film-Cooled Gas Turbine Blade,” ASME J. Eng. Power, 107, pp. 991–997.
Camci,  C., and Arts,  T., 1985b, “Experimental Heat Transfer Investigation Around the Film-Cooled Leading Edge of a High-Pressure Gas Turbine Rotor Blade,” ASME J. Eng. Power, 107, pp. 1016–1021.
Camci,  C., and Arts,  T., 1990, “An Experimental Convective Heat Transfer Investigation Around a Film-Cooled Gas Turbine Blade,” ASME J. Turbomach., 112, pp. 497–503.
Walters,  D. K., and Leylek,  J. H., 2000, “A Detailed Analysis of Film Cooling Physics: Part I—Streamwise Injection With Cylindrical Holes,” ASME J. Turbomach., 122, pp. 102–112.
Garg,  V. K., and Gaugler,  R. E., 1997, “Effect of Coolant Temperature and Mass Flow on Film Cooling of Turbine Blades,” Int. J. Heat Mass Transf., 40, 435–445.
Friedrics,  S., Hodson,  H. P., and Dawes,  W. N., 1999, “The Design of an Improved Endwall Film-Cooling Configuration,” ASME J. Turbomach., 121, pp. 772–780.
STAR-CD Version 3.10—Methodology, 1999, Computational Dynamics Limited.
Hale,  C. A., Plesniak,  M. W., and Ramadhyani,  S., 2000, “Film Cooling Effectiveness for Short Film Cooling Holes Fed by a Narrow Plenum,” ASME J. Turbomach., 122, pp. 553–557.

Figures

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Geometry of cooling holes
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Detail of the computational mesh, suction side cooling holes
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Detail of the computational mesh, pressure side cooling holes
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Detail of velocity vectors in the plenum-tube junction region, computations with v2−f model
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Detail of turbulent intensity contours in the plenum-tube junction region, computations with v2−f model
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Temperature and location of characteristic cross sections, m=1.0
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Heat transfer coefficient, ht (W/m2K), suction side cooling, m=0.45
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Heat transfer coefficient, ht (W/m2K), suction side cooling, m=0.6
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Heat transfer coefficient, ht (W/m2K), suction side cooling, m=1.0
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Temperature and location of characteristic cross sections, m=4.25
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Temperature contours computed with different turbulence models, cross section A, suction side cooling, high blowing ratio m=1.0
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Temperature contours computed with different models, cross section B, suction side cooling, high blowing ratio m=1.0
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Turbulence intensity computed with various models, cross section A, suction side cooling, high blowing ratio m=1.0
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Turbulence intensity computed with various models, cross section B, suction side cooling, high blowing ratio m=1.0
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Velocity magnitude with different models, cross section C, suction side cooling, high blowing ratio m=1.0 (cascade inflow Uinflow=100 m/s)
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Heat transfer coefficient, ht (W/m2K), pressure side cooling, m=1.75
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Heat transfer coefficient, ht (W/m2K), pressure side cooling, m=3.3
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Heat transfer coefficient, ht (W/m2K), pressure side cooling, m=4.25
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Temperature contours computed with various turbulence models, cross section A, pressure side cooling, high blowing ratio m=4.25 (blade surface at the top)
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Temperature contours computed with different models, cross section B, pressure side cooling, high blowing ratio m=4.25 (blade surface at the top)
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Velocity magnitude with different models, cross section C, pressure side cooling, high blowing ratio m=4.25 (cascade inflow Uinflow=100 m/s)

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