Toward Improved Film Cooling Prediction

Author:

Medic G.1,Durbin P. A.1

Affiliation:

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

Abstract

Abstract Computations of flow and heat transfer for a film-cooled high pressure gas turbine rotor blade geometry are presented with an assessment of several turbulence models. Details of flow and temperature field predictions in the vicinity of cooling holes are examined. It is demonstrated that good predictions can be obtained when spurious turbulence energy production by the turbulence model is prevented.

Publisher

ASME International

Subject

Mechanical Engineering

Reference13 articles.

1. Medic, G., and Durbin, P. A., 2002, “Toward Improved Prediction of Heat Transfer on Turbine Blades,” ASME J. Turbomach., 124, pp. 187–192.

2. Launder, B. E., and Kato, M., 1993, Modelling Flow-Induced Oscillations in Turbulent Flow Around a Square Cylinder,” ASME FED 157, pp. 189–199.

3. Durbin, P. A. , 1996, “On the k−ε Stagnation Point Anomaly,” Int. J. Heat Fluid Flow, 17, pp. 89–90.

4. 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.

5. 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.

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