The local film-cooling produced by a row of jets on a gas turbine blade is measured by a mass transfer technique. The density of the secondary fluid is from 0.75 to two times that of the mainflow and the range of the mass flux ratio is from 0.2 to three. The effect of blade-wall curvature on the film-cooling effectiveness is very significant. On the convex wall, a near tangential jet is pushed towards the wall by the static pressure force around the jet. For a small momentum flux ratio, this results in a higher effectiveness compared with that on a flat wall. At a large momentum flux ratio, however, the jet tends to move away from the curved wall because of the effect of inertia of the jet resulting in a smaller effectiveness on the convex wall. On the concave wall, the effects of curvature are the reverse of those described for the convex wall.
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July 1978
This article was originally published in
Journal of Engineering for Power
Research Papers
Film Cooling of a Gas Turbine Blade
S. Ito,
S. Ito
Department of Mechanical Engineering, University of Minnesota, Minneapolis, Minn.
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R. J. Goldstein,
R. J. Goldstein
Department of Mechanical Engineering, University of Minnesota, Minneapolis, Minn.
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E. R. G. Eckert
E. R. G. Eckert
Department of Mechanical Engineering, University of Minnesota, Minneapolis, Minn.
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S. Ito
Department of Mechanical Engineering, University of Minnesota, Minneapolis, Minn.
R. J. Goldstein
Department of Mechanical Engineering, University of Minnesota, Minneapolis, Minn.
E. R. G. Eckert
Department of Mechanical Engineering, University of Minnesota, Minneapolis, Minn.
J. Eng. Power. Jul 1978, 100(3): 476-481 (6 pages)
Published Online: July 1, 1978
Article history
Received:
August 4, 1977
Online:
July 14, 2010
Citation
Ito, S., Goldstein, R. J., and Eckert, E. R. G. (July 1, 1978). "Film Cooling of a Gas Turbine Blade." ASME. J. Eng. Power. July 1978; 100(3): 476–481. https://doi.org/10.1115/1.3446382
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