The effect of film cooling parameters on the cooling effectiveness of an actual turbine blade is studied numerically. Film cooling\nparameters such as the hole shape, holes distribution, blowing ratio, stream wise angle, and span wise angle are investigated to\nselect the appropriate cooling parameters. Unstructured finite volume technique is used to solve the steady, three-dimensional, and\ncompressible Navier-Stokes equations. Using one cooling holes array indicates that the average overall film cooling effectiveness is\nenhanced by decreasing the stream wise angle for high blowing ratio on the suction side of the turbine blade. The film cooling\neffectiveness is enhanced on the pressure side for a blowing ratio of unity. In addition, the cooling effectiveness increases by\nincreasing the lateral and forward diffusion angles. The computations reveal that the efficiency of cooling is decreased at the leading\nedge due to the large surface curvature of the blade. The presence of compound shape (span wise angle) enhanced the film cooling\neffectiveness on the two sides. Multistagger cooling hole arrays are investigated and the results indicate that five-stagger cooling\narrays on the pressure side and three-stagger cooling arrays on the suction side with LFDCA-9.3-14.6 hole shape are enough to have\ngood cooling of the two sides using 2.17% bleed air of the engine.
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