某航空发动机径向扩压器叶片断裂分析

Analysis of Radial Diffuser Blade Fracture in an Aircraft Engine

为了确定某航空发动机径向扩压器叶片断裂故障的断裂性质和产生的原因,通过对径向扩压器叶片失效分析进行了初步故障分析,并从径向扩压器的材料、设计、加工及环境影响等方面进行了详细的故障分析。结果表明:径向扩压器叶片断裂性质为高周疲劳断裂,产生高周疲劳的原因为径向扩压器在发动机工作转速范围内存在共振。径向扩压器共振时振动应力的大应力区在叶片前缘叶根处,导致叶片从该处产生裂纹,最终发生高周疲劳断裂。建议优化径向扩压器叶片叶型,避开工作转速范围内的共振,以避免类似故障重复发生。

In order to determine the fracture nature and cause of the radial diffuser blade fracture fault in an aircraft engine,a preliminary failure analysis was conducted through the failure analysis of the radial diffuser blade,and detailed fault analysis was conducted from the aspects of material,design,processing,and environmental impact of the radial diffuser.The result indicates that the fracture property of the blade is high-cycle fatigue.In the working state of the aircraft engine,the radial diffuser exhibits resonance within the operating speed range,and the highsress zone is located at the root of the leading edge of the blade,resulting in cracks in the blade and ultimately leading to high-cycle fatigue.It is recommended to optimize the blade shape and avoid resonance to avoid similar faults from recurring.