用残余应力确定涡轮盘应变循环研究  

A Study on the Maximal Turbine Disk Strain Cycle with Residue Stress

作　　者：杨兴宇[1] 赵福星[1] 耿中行[1] 

机构地区：[1]北京航空工程研究中心,北京100076

出　　处：《航空动力学报》2004年第5期614-618,共5页Journal of Aerospace Power

摘　　要：提出了一种避开瞬态温度场测试而通过残余应力计算得到最大应力应变循环的方法。应用以应力释放位移为几何边界条件的残余应力确定法对某型发动机高压涡轮盘进行了残余应力分析,得到了涡轮盘中心孔与径向销钉孔交界处的残余应力,并计算了该危险点最大应力应变循环,预测了低循环疲劳寿命。研究结果表明,该方法可以较准确地确定影响零部件寿命主要因素的最大应力应变循环。In order to avoid the difficulty and expensive measurement of transient temperature field,a method for maximal stress and strain cycle calculation using residue stress is proposed.This method was used to analyze a high pressure turbine disk with the displacement of stress release as geometrical boundary condition.The residue stress and the maximal stress and strain cycle of the critical points adjacent to central hole and radial pin hole are obtained and the life of low cycle fatigue is predicted.The result shows that using the residue stress we can calculate accurately the maximal stress-strain cycle,which is the main factor influencing component life.

关 键 词：推进系统 残余应力 最大应力应变循环 低循环疲劳寿命 航空航天 

分 类 号：V231.9[航空宇航科学与技术—航空宇航推进理论与工程]