Multi-step optimizations of leading edge and downstream film cooling configurations on a high pressure turbine vane

Multi-step optimizations of leading edge and downstream film cooling configurations on a high pressure turbine vane are conducted using full three-dimensional optimization method. Firstly, a full three-dimensional optimization platform for film-cooled turbines, which consists of the parametric modeling, automatic mesh generation, the CFD numerical calculation and the optimization strategy is established. On the basis of it, the optimization platform is used to optimize the configurations of multi-rows film cooling holes for C3X gas turbine vane cooled with leading edge showerhead film cooling, and the layout of rows of film cooling holes on pressure side and suction side is optimized for the further step optimization. The sensitivity analysis for film cooling performance is used to decide the final design variables, and the adiabatic film cooling effectiveness is adopted to evaluate the overall performance of film-cooled turbine vane. The results show that the average film cooling effectiveness of the optimized leading edge region, pressure surface and suction surface are increased by 8.4%, 1.1% and 5.5% compared with the original case, while the average temperature of the leading edge region is decreased by 19 K.