飞机发动机铰链结构裂纹扩展分析与试验验证

Hinge Structure Crack Propagation Analysis and Test Verification of Aircraft Engine

为了研究飞机铰链结构损伤容限设计特性,采用有限元分析结合工程计算与试验验证的方法,对铰链结构裂纹扩展与剩余强度特性进行验证。分析与试验结论表明,针对Inconel718高温合金铰链结构,NASGRO模型仅在小裂纹阶段与裂纹平稳扩展阶段能够获得满足工程要求的计算精度,计算值误差在30%以内。在裂纹失稳扩展阶段,计算精度下降,但铰链裂纹扩展寿命计算结果依然偏安全保守,该计算方法可以为工程设计提供参考。

In order to study the damage tolerance design characteristics of aircraft hinge structure, took the method of combining finite element with engineering calculation and experimental verification method, verified the crack growth and residual strength characteristics of hinge structure. The analysis and test results show that, for the Inconel718 hinge structure, the NASGRO model can obtain the calculation accuracy of the engineering requirements only in the stage of small crack and the smooth crack growth stage, and the calculated value error is within 30%. In the stage of crack instability expansion, the calculation precision is reduced, but the calculation result of the crack propagation life of the hinge is still safe and conservative. The calculation method can be used as a reference for the engineering design.