航空发动机涡轮叶片高周疲劳裂纹故障分析与思考  

Analysis and consideration for turbine blade high-cycle fatigue crack failure of aero-engine

作　　者：陈博 朱剑寒 鲁辉军 CHEN Bo;ZHU Jian-han;LU Hui-jun(Equipment Department of PLA Air Force,Beijing 100843,China;AECC Sichuan Gas Turbine Establishment,Chengdu 610500,China)

机构地区：[1]中国人民解放军空军装备部,北京100843 [2]中国航发四川燃气涡轮研究院,成都610500

出　　处：《燃气涡轮试验与研究》2020年第3期33-36,共4页Gas Turbine Experiment and Research

摘　　要：针对航空发动机涡轮整体叶盘叶片发生的高周疲劳裂纹故障,及排故初期受动应力测试条件限制,主要采取增强结构抗力的排故措施使裂纹位置集中于叶片尾缘根部。后经高温、高转速、小尺寸整体叶盘叶片动应力测试技术攻关,明确故障主要为涡轮导叶尾流激起的叶片振动应力超限所致。采取增加导叶数避开共振的改进措施,并经整机高周疲劳试验考核验证了其有效性。认识到叶片振动特性设计时需关注的几个问题,及先进动应力测试技术在发动机研制过程中的不可或缺,形成了一套经过实践验证的叶片高周疲劳排故工作流程,对国内航空发动机研制起到一定的参考借鉴作用。For high-cycle fatigue crack occurred in turbine disc blade of a certain aero-engine,due to the limitation of dynamic stress testing conditions at the initial stage,the cracks were concentrated at the root of the trailing edge of the blade by strengthening the structural resistance.Later,after a technical breakthrough in the dynamic stress test of high temperature,high speed and small size blisk blade,it was clear that the main reason for the failure was the over-limit vibration stress caused by the wake flow of turbine guide blade.Finally,the problem was solved by increasing the number of blades to avoid resonance,and the effectiveness of the method was verified by high-cycle fatigue test in the engine environment.Through the troubleshooting,it is understood that some issues should be paid attention to in the design of blade vibration characteristics.The dynamic stress test technology is indispensable in the aero-engine development,and a set of verified troubleshooting work flow is established,which can be referential for the domestic areo-engine development.

关 键 词：航空发动机 涡轮叶片 高周疲劳 裂纹 振动应力测试 排故 

分 类 号：V236[航空宇航科学与技术—航空宇航推进理论与工程]