CMC涡轮平面叶栅优化设计OA

Ceramic based composite materials(CMC)are gradually being applied in aviation engine turbine components due to their excellent properties such as high temperature resistance and low density.However,due to their special preparation process,they are difficult to meet the special shape of traditional turbine rotor blades with low thickness and large curvature,resulting in poor aerodynamic performance of CMC turbine rotor blades.In order to further improve the aerodynamic performance of CMC turbine rotor blades,this paper conducted a modified design of the CMC turbine blade profile for the mid section blade of a low-pressure turbine rotor blade,a parameter sensitivity analysis based on the blade profile,and a forward-and-inverse-problem combined multi-objective optimization analysis based on the design constraints for CMC turbine blade profiles.The optimized results indicate that this method can effectively improve the flow field structure inside CMC turbine cascades and enhance and lower the total pressure loss coefficient of the blade profile by 17.61％compared to the initial blade profile.