摘要
针对缺乏航空发动机再制造涡轮盘低周疲劳(low cycle fatigue,LCF)参数数据,无法直接利用传统寿命预测方法进行再制造涡轮盘LCF寿命预测的现状,考虑疲劳极限与疲劳寿命的关系,提出利用再制造涡轮盘寿命修正系数,对通过有限元应力-应变分析及局部应力-应变法得到的寿命预测结果进行修正的方法,实现再制造涡轮盘寿命预测.最后将预测结果与相关试验结果进行对比,证明预测结果具有一定准确性.
Due to the lack of low cycle fatigue (LCF) parameter data of remanufactured turbine disk on aeroengine, it is impossible to predict the low cycle fatigue life of remanufactured turbine disk directly by using traditional life prediction method. Considering the relationship between fatigue limit and fatigue life, the life corrective factor of remanufactured turbine disk is put forward to correct the life prediction results obtained by finite element stress-strain analysis and local stress-strain method, then the life of remanufactured turbine disk is predicted. Finally, the prediction results are compared with the relevant experimental results, which proves that the prediction results are accurate.
作者
王常浩
刘淑杰
王轶凡
张洪潮
WANG Changhao;LIU Shujie;WANG Yifan;ZHANG Hongchao(School of Mechanical Engineering,Dalian University of Technology,Dalian 116024,China)
出处
《大连理工大学学报》
EI
CAS
CSCD
北大核心
2019年第4期366-371,共6页
Journal of Dalian University of Technology
基金
国家自然科学基金资助项目(51775086)
关键词
再制造涡轮盘
疲劳寿命修正系数
局部应力-应变法
低周疲劳寿命预测
remanufactured turbine disk
fatigue life corrective factor
local stress-strain method
low cycle fatigue life prediction
