典型涡扇发动机陶瓷基复合材料涡轮叶片概念设计

For the purpose of technological progress for ceramic matrix composites (CMCs) turbine blade design in advanced aero-engines，based on main performance parameters of typical turbofan engine，and according to the forward turbine blade design process，a conceptual design method was established from aerodynamic design to structural design finally to deformation and strength analysis，and a CMCs low pressure turbine rotor blade was designed，which was solid without cooling. In the conceptual design method，strength was taken as the major constraint，aero-engine thrust and specific fuel consumption taken as inputs， and model of turbine blade body taken as output. The simulation results indicated that aerodynamic performance， strength and vibration performance of the designed blade under design conditions satisfy the design requirements. Reserve factor of safety reached 1.8 and the external load level of the turbine disk was estimated to be reduced by 50%，proving the feasible application of CMCs on advanced aero-engines. Turbine efficiency increased approximately 0.98%—1.17%，which demonstrated the potential of CMCs to promote the performance of high-temperature components in advanced aero-engines.