| The output power and efficiency of the gas turbine increases with the improvement ofthe turbine inlet temperature. With the constant pursuit of power and efficiency of the gasturbine, the turbine inlet temperature continuously improved, now modern engine turbineinlet temperature has reached1800K~2000K, it is far higher than the turbine bladeheat-resistance limit and caused the heat load of turbine blades increased greatly, so it isessential to take effective cooling measures. Therefore, carried on detailed research on thefilm cooling is particularly important. In this paper, according to a certain type of gas turbinefirst stage vane of the real working environment, the3D blades were simplified, then usingcomputational fluid dynamics software (CFD) and SST turbulence model to simulate. In thispaper, the main research contents are as follows:1. The film cooling efficiency researched on the leading edge. As to the film holes thatlocated in the leading edge near the pressure side, carried on the film cooling efficiency, filmcoverage ratio and specific discharge under different blowing ratios, different diameters anddifferent hole shapes, then draw the leading edge film holes variation under differentconditions2. The film cooling efficiency researched on pressure side. Study respectively threeparameters of the pressure side, the film cooling effectiveness, effective coverage ratio andthe specific discharge under different blowing ratios and different diameters, to provide thebasis for the optimization of the pressure side film hole.3. The film cooling efficiency researched on suction side. The article has beensystematically studied the film cooling effectiveness under different blowing ratios, differentdiameters and different shaped holes. Compared effective coverage ratios and specificdischarge under different conditions. Summarized the range of the best blowing ratios, thebest diameters and the best shaped holes that arranged on the suction side. Provide areference for the optimization of film cooling holes on the suction side.4. Based on the existing blade model, decorate12rows of film holes in the blade surface,analyzed and compared the leading edge blade surface film cooling efficiency under differentcompound angles and different blowing ratios, and compared the cooling efficiency of the blade axis. On this basis, optimized the design of the leading edge of the film cooling holesand improved the cooling efficiency of the leading edge greatly. |
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