发动机HPT叶片失效分析及损伤发展趋势研究

Failure analysis and damage development trend research of aero-engine high-pressure turbine blades

基于某航空公司CFM56-7B发动机高压涡轮转叶前缘历史孔探数据,首先分析热障涂层失效原因,运用统计分析方法,确定高压涡轮转叶前缘涂层脱落失效分布模型;然后对高压涡轮转叶前缘损伤发展趋势进行回归分析并计算机队高压涡轮转叶前缘平均寿命。

Datum about one airlines＇ CFM56-TB engine fleet containing borescope inspection information about high pres- sure turbine are used to analyze failure reasons of thermal barrier coatings. Statistical analyzing method is em- ployed to determine the failure distribution model. Regression analysis is then conducted to obtain the damage de- velopment trend of leading edge of blade. Finally, average life expectancy of leading edge of blade is computed.