航空发动机叶片残余应力监测及安全评定研究  

Surface Residual Stress Test for Aero-engine Blade and its Safety Assessment

作　　者：刘建勋[1] 魏东[1] 刘成武[1] 杨军良[1] 

机构地区：[1]空军第一航空学院,信阳464000

出　　处：《科学技术与工程》2009年第11期2877-2879,2898,共4页Science Technology and Engineering

基　　金：总装"十一五"预研项目资助

摘　　要：针对航空发动机叶片的疲劳断裂问题,采用X射线衍射分析方法,对某型发动机压气机叶片进行了残余应力测试。分析了叶片表面不同部位残余应力随工作寿命和损伤情况的变化规律,探讨了将残余应力应用于叶片使用安全评定的可行性。结果表明,通过监测叶片表面残余应力,可以评估叶片的疲劳损伤状况,解决叶片的安全使用评定问题。To tackle the fatigue fracture problem of aero-engine blades, the residual stresses of compressor blades are tested for a certain type of engine. The variation characteristics of residual stresses for different blade part are analyzed with working life and scathing status. The validity of residual stresses in engine blades safety assessment is discussed. It shows that the fatigue fracture status can be assessed by inspecting the residual stresses of blade surface, and the safety assessment of engine blade can be solved.

关 键 词：航空发动机 叶片 疲劳断裂 残余应力 X射线衍射分析 

分 类 号：O348.6[理学—固体力学]