航空发动机低压压气机三级盘裂纹分析  

Failure Analysis of Crack on the Fan Disk in an Aero-engine

作　　者：刘军和[1] 张银东[2] 李明[1] 杨树林[1] 

机构地区：[1]驻沈阳黎明发动机制造公司军事代表室,沈阳110043 [2]沈阳黎明航空发动机(集团)有限责任公司,沈阳110043

出　　处：《失效分析与预防》2013年第2期107-111,共5页Failure Analysis and Prevention

摘　　要：航空发动机在地面试车过程中,出现低压压气机三级盘裂纹故障。通过对故障件进行尺寸复测、性能测试、组织分析和断口观察,分析故障性质和原因。结果发现:断口为多源疲劳断裂,裂纹起始于三级盘排气侧辐板与轴颈转接R表面,向进气边方向扩展,扩展区疲劳条带细密,具有高周疲劳的特征。源区未见明显的冶金缺陷,但裂纹在宏观上与加工接刀痕迹吻合。分析认为故障盘疲劳裂纹的产生与使用过程中特定条件下的振动有关。三级盘辐板与轴颈转接处转接R尺寸偏小,转接不圆滑,存在应力集中,促进裂纹的产生。Crack was present on the fan disk of an aero-engine during the trial run.Failure analysis was conducted by the microstructure analysis,the fracture surface observation,the repeated measurement of disk size,and the examination of mechanical properties.The results show that the crack initiated at the transit position between the former and the rim of the disk and propagated from the exhaust side to inlet side.No metallurgical defects were found at the fracture initiation area of the crack,however,the transit radius between the former and the rim of the disk is smaller than the designing requirement and the former transit to the rim poor smoothly.Machining trace was also found near the crack.The integrated effects of out-of-tolerance can introduce the stress concentration,which may bring the fatigue.The crack was analyzed to have relation with the shock of aero-engine in service.

关 键 词：航空发动机 裂纹 疲劳 应力集中 

分 类 号：V231.95[航空宇航科学与技术—航空宇航推进理论与工程]