摘要
在分析疲劳裂纹产生机理的基础上,将塑性应变能和临界平面结合起来,同时引入剪应变能比例因子,提出一种新的多轴损伤参量,通过试棒单轴低循环疲劳试验应力应变曲线得到总的塑性应变能,进而得到一种新的多轴疲劳寿命预测模型。通过对比分析,得到了最佳剪应变能比例因子。使用该模型、Chen-Xu-Huang(CXH)模型、Liu-Wang(LW)模型对某型发动机涡轮盘销钉孔低循环疲劳寿命进行预测,并与真盘试验结果进行对比。结果表明,该多轴疲劳寿命预测模型预测误差为20.5%,优于CXH和LW模型。
Based on the fatigue crack generation mechanism, we tegrating plastic strain energy with critical plane and introducing propose a new multiaxial damage parameter by in- the shear strain energy proportion factor. Then we establish the multiaxial fatigue life prediction model by using the total plastic strain energy obtained with the stress - strain curve from the uniaxial specimen low cycle fatigue test. The optimal shear strain energy factor was obtained with comparative analysis. The low cycle fatigue life of a turbine disk was predicted by using the Chen-Xu-Huang （CXH） and Liu-Wang（LW） model. The prediction results were compared with the experimental results on the fa- tigue life of a real turbine disk, and the comparison results show that the prediction error of our model is 20.5 %, lower than that of the CXH and LW model.
出处
《机械科学与技术》
CSCD
北大核心
2013年第7期1074-1078,1083,共6页
Mechanical Science and Technology for Aerospace Engineering
关键词
塑性应变能
损伤参量
临界平面
多轴疲劳
涡轮盘
寿命预测
disks （ structural components）
strain energy
fatigue testing
errors
mathematical models
plasticstrain energy
muhiaxial damage parameter
critical plane
multiaxial fatigue life
turbine disk
pre-diction model
