某型航空发动机高温测头应力研究

Stress analysis of the high temperature probe of an aero engine

对被试航空发动机内涵涡轮处测头进行应力分析是测头强度计算及寿命准确预测的关键。针对某型航空发动机涡轮前的高温压力测头,分析了其工作时受到的载荷情况,通过试验数据及基于有限元软件进行分析计算,得出了该高温测头工作时受到基础载荷、气动载荷和热载荷作用下的合应力及各载荷对合应力的贡献,分析计算表明,热载荷是高温测头工作时应力的主要贡献者,计算结果为该高温测头设计和加工提供依据,保证了试飞试验安全。

Stress analysis of the high temperature probe installed at the turbine of the aero engine is the key to the strength check and service life prediction of the probe. In this study,we analyzed the operation loads of the high temperature probe of an aero engine. Based on the testing data and finite element analysis,we acquired the total stress of the probe under basic load,aerodynamic load and thermal load,as well as the proportion each load took in the total stress. The results showed that,thermal load was the major contributor to the stress of the high temperature probe. The results provided reference for the design and manufacture of high temperature probes,and ensured the safety of flight tests.