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.
Toward Improved Film Cooling Prediction
Contributed by the International Gas Turbine Institute for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received by the IGTI, March 20, 2001; revised manuscript received Octoer 15, 2001. Associate Editor: R. Bunker.
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Medic, G., and Durbin, P. A. (April 9, 2002). "Toward Improved Film Cooling Prediction ." ASME. J. Turbomach. April 2002; 124(2): 193–199. https://doi.org/10.1115/1.1458021
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