Film cooling performance for injection through discrete holes in the endwall of a turbine blade is investigated. The effectiveness is measured at 60 locations in the region covered by injection. Three nominal blowing rates, two density ratios, and two approaching flow Reynolds numbers are examined. Analysis of the data reveals that even 60 locations are insufficient for the determination of the field of film cooling effectiveness with its strong local variations. Visualization of the traces of the coolant jets on the endwall surface, using ammonium-diazo-paper, provides useful qualitative information for the interpretation of the measurements, revealing the paths and interaction of the jets, which change with blowing rate and density ratio.
Film Cooling of the Gas Turbine Endwall by Discrete-Hole Injection
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Jabbari, M. Y., Marston, K. C., Eckert, E. R. G., and Goldstein, R. J. (April 1, 1996). "Film Cooling of the Gas Turbine Endwall by Discrete-Hole Injection." ASME. J. Turbomach. April 1996; 118(2): 278–284. https://doi.org/10.1115/1.2836637
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