Failure analysis on an aero-engine combustor is carried out for the cranking failure of combustor liner during its service period. Crack macroscopic observation and microscopic observation are performed. Fluid-structure coupling simulation of aero-engine combustor under typical working conditions is carried out to obtain the temperature distribution of combustor using a CFD commercial code, ANSYS FLUENT. Based on the results of fluid–structure coupling simulation, nonlinear statics analysis of the aero-engine combustor liner is carried out using a commercial code, MSC/NASTRAN. The visual inspection results show that obvious fatigue characteristics are found at fractures, and fatigue is responsible for observed cracks. The simulation results show that the maximum plastic strain of the combustor is located at the edge of the mixing holes near the two cracks. The maximum plastic strain is 0.4476%, 0.4154% respectively. During aero-engine’s service period, the start and stop of engine would cause cyclic loading of plastic strain, which give rise to fatigue damage and fatigue damage leads to cracking of combustor.

针对燃烧器衬套在其使用期间的曲柄故障，对航空发动机燃烧器进行了故障分析。进行裂纹宏观观察和微观观察。使用CFD商业代码ANSYS FLUENT对航空发动机燃烧器在典型工作条件下的流固耦合进行仿真，以获得燃烧器的温度分布。基于流固耦合模拟的结果，使用商业代码MSC / NASTRAN对航空发动机燃烧室衬套进行了非线性静力分析。目视检查结果表明，在断裂处发现了明显的疲劳特性，疲劳是观察到的裂纹的原因。仿真结果表明，燃烧室的最大塑性应变位于两个裂纹附近混合孔的边缘。最大塑性应变分别为0.4476％，0.4154％。在航空发动机的使用期间，发动机的启动和停止会引起周期性的塑性应变载荷，从而引起疲劳损伤，疲劳损伤导致燃烧器破裂。