| Enhancing the temperature of gas turbine's inlet is one of the key technology to improve the efficiency of the gas turbine, and the requirement the blade bearing the high temperature is much higher than before. As a result, investigating on flow and heat transfer performance of blade's film cooling possesses is important to protect the blade effectively and design the gas turbine.Basing on SIMPLE algorithm and discretizing the control equation in finite volume method, standard k-εturbulence model is applied, to numerical simulate the temperature field which have no jets hole static turbine stage, rotation turbine stage at different main flow temperature T∞=350 and 1500K and have jets hole turbine stage and blade cascade at different flow temperature T∞=350 and 1500K and different blowing rate M=0.5, 1 and 1.5. Analyzed temperature of the blade and summing up the jet over the cascades-channel distribution of surface temperature.The results shows that gas turbine static blade surface temperature consistent with mainstream, due to centrifugal force, Coriolis force and the role of floating lift pressure surface of the gas turbine rotating blade form lower temperature zone in middle part of blade; Film cooling efficiencyηthan with the jets rate M, the film cooling efficiency is best when jets rate M=1.5; In different jets rate M, the pressure surface cooling effect were best, because of the cooling gas film closer to the blade surface and cooling the widest scope, the suction surface Cooling effect were worst. The rotation blade cascade, jet cooling of blades affect mainly concentrated in trailing edge and bottom of the leaves, cooling effect not obvious.
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