航空发动机整体叶环叶片裂纹分析

经锻造热处理和热等静压工艺处理后的整体叶环叶片在振动疲劳试验中出现裂纹，通过宏观检查、断口宏微观分析、材质分析、力学性能试验和有限元应力模拟等手段，对叶片的裂纹性质和萌生原因进行分析与研究，并提出改进建议。结果表明:整体叶环叶片裂纹性质为高周疲劳，疲劳裂纹起源于叶片叶背侧表面最大应力区；整体叶环叶片在热等静压工艺处理后存在平直晶界连续α膜，抗疲劳性能明显降低，导致疲劳裂纹过早萌生。

Failure Analysis of Vibration Fatigue Crack on the Integral Ring Blade of Aeroengine

Aiming at the cracks in the vibration fatigue test of the integral ring blade after the forging heat treatment and hot isostatic pressing process, this paper uses macro inspection, fracture macro and micro analysis, material analysis, mechanical performance test and finite element stress simulation to analyze and study the crack properties and initiation causes of the blade, and put forward suggestions for improvement. The results show that the crack property of the integral ring blade is high cycle fatigue fracture. The fatigue crack originated from the maximum stress area on the back surface of the blade. Furthermore, there was a continuous α film with straight grain boundaries, and the fatigue resistance was significantly reduced, resulting in the premature initiation of fatigue crack.