典型涡扇发动机陶瓷基复合材料涡轮叶片概念设计

为了推动先进航空发动机陶瓷基复合材料（CMCs）涡轮叶片设计技术进步，以典型涡扇发动机基准性能参数为原始数据，按照涡轮叶片正向设计流程，从气动设计，到结构设计，再到变形及强度分析，梳理出以材料强度为约束，发动机推力和耗油率为输入值，涡轮叶片叶身模型为结果的概念设计方法。设计了一种陶瓷基复合材料低压涡轮转子叶片，该叶片实心无冷却，设计工况下的气动性能、强度和振动特性仿真结果满足设计要求。安全储备系数可达1.8，涡轮盘外载预估减少50%，验证了陶瓷基复合材料用于先进航空发动机热端部件的可行性。涡轮效率提高0.98%～1.17%表明陶瓷基复合材料具有提升先进航空发动机热端部件性能的潜力。

Conceptual design of ceramic matrix composites turbine blade for typical turbofan engine

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.