航空发动机低压涡轮轴通油孔裂纹失效分析  

Crack failure analysis of low pressure turbine shaft oil passage hole of aero-engine

作　　者：王学民 卢绪平 沈莲 古远兴 吴晨 郭建英 徐敬沛 WANG Xuemin;LU Xuping;SHEN Lian;GU Yuanxing;WU Chen;GUO Jianying;XU Jingpei(AECC Sichuan Gas Turbine Research Establishment,Chengdu 610500,China;School of Mechanical and Electrical Engineering,University of Electronic Science and Technology of China,Chengdu 611731,China)

机构地区：[1]中国航发四川燃气涡轮研究院,成都610500 [2]电子科技大学机械与电气工程学院,成都611731

出　　处：《机械强度》2025年第2期37-43,共7页Journal of Mechanical Strength

基　　金：航空动力基础研究项目。

摘　　要：为探究某型航空发动机低压涡轮轴高低周复合疲劳试验过程中通油孔裂纹故障的性质和原因,对低压涡轮轴裂纹位置进行了外观检查、断口分析、表面检查、金相组织检查、有限元分析和裂纹扩展仿真。结果表明,低压涡轮轴通油孔裂纹故障为疲劳裂纹,其原因为通油孔采用电火花加工后,未完全去除重熔层,导致其内侧表面存在部分未去除的重熔层且有可见微裂纹,在较大的高低周复合载荷作用下萌生疲劳裂纹并发生了裂纹扩展,从而导致通油孔裂纹故障,通过裂纹扩展仿真分析预估初始裂纹长度介于0.2~0.3 mm。为了保证通油孔加工质量,考虑该位置加工可达性较差,建议可设计特殊工装、采用机械加工技术进行加工,在保证加工精度的基础上从根本上杜绝重熔层的影响。In order to investigate the nature and causes of the cracked passage hole of the low-pressure turbine shaft of aero-engine during the high and low circumference compound fatigue test,the low-pressure turbine shaft crack location was examined in appearance,fracture analysis,surface inspection,metallographic organization,finite element analysis and crack expansion simulation.The results show that the low-pressure turbine shaft passage hole crack failure is a fatigue crack,which is caused by the incomplete removal of the remelting layer after the passage hole is cut by electrical discharge machining,resulting in the existence of part of the unremoved remelting layer and visible microcracks on the internal surface,and the fatigue crack sprouted and crack expansion occurred under the action of large high and low circumferential composite load,thus leading to the passage hole crack failure.The initial crack length is estimated to be between 0.2-0.3 mm by the crack expansion simulation analysis.In order to ensure the processing quality of the through oil hole,considering the poor processing accessibility of this location,it is suggested that special tooling can be designed and the machining technology can be used for processing,on the basis of ensuring the processing,fundamental eliminate the influence of the remelting layer.

关 键 词：低压涡轮轴 失效分析 重熔层 疲劳断裂 有限元分析 裂纹扩展仿真 航空发动机 

分 类 号：V232.2[航空宇航科学与技术—航空宇航推进理论与工程]