Film cooling is vital to gas turbine blades to protect them from high temperatures and hence high thermal stresses. In the current\r\nwork, optimization of film cooling parameters on a flat plate is investigated numerically. The effect of film cooling parameters such\r\nas inlet velocity direction, lateral and forward diffusion angles, blowing ratio, and streamwise angle on the cooling effectiveness is\r\nstudied, and optimum cooling parameters are selected. The numerical simulation of the coolant flow through flat plate hole system\r\nis carried out using the ââ?¬Å?CFDRC packageââ?¬Â coupled with the optimization algorithm ââ?¬Å?simplexââ?¬Â to maximize overall film cooling\r\neffectiveness. Unstructured finite volume technique is used to solve the steady, three-dimensional and compressible Navier-Stokes\r\nequations. The results are compared with the published numerical and experimental data of a cylindrically round-simple hole, and\r\nthe results show good agreement. In addition, the results indicate that the average overall film cooling effectiveness is enhanced\r\nby decreasing the streamwise angle for high blowing ratio and by increasing the lateral and forward diffusion angles. Optimum\r\ngeometry of the cooling hole on a flat plate is determined. In addition, numerical simulations of film cooling on actual turbine\r\nblade are performed using the flat plate optimal hole geometry.
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