CMC复合材料涡轮转子叶片结构设计

Study on Structural Design of CMC Compound Material Turbine Rotor Blade

在现有成熟的航空发动机基础上,采用CMC复合材料适应性设计低压涡轮转子叶片的结构,在涡轮盘上均布安装4件,对CMC复合材料能否在航空发动机高温部件上应用,进行结构上可行性的研究。

Based on the existing aviation motor,this paper adopts CMC material to design the structure of low-pressure turbine blade. 4 blades are installed on the turbine disc, Feasibility of applying CMC compound material on the aviation motor is studied.