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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。
On the basis of the existing mature aeroengine, the structure of low pressure turbine rotor blade is adaptively designed by using CMC composite materials. Four pieces are uniformly arranged on the turbine disk. Whether CMC composite material can be applied on the high temperature components of aeroengine can be used to carry out the structure Feasibility study.