摘要
为提高航空发动机FGH96材料涡轮盘在较高应力梯度缺口处如螺栓孔处的疲劳寿命预测精度,通过使用新的平均应力公式,同时考虑应力梯度和尺寸效应的影响,通过FGH96材料级间盘模拟试验件疲劳试验,对模型所需的寿命预测方程中的参数进行拟合,进一步开展FGH96材料涡轮盘螺栓孔模拟件疲劳试验,与预测结果进行了比较,结果表明,改进后的疲劳构件寿命预测方法具有较高的精度,证明了该方法的有效性。
In order to improve the fatigue life prediction accuracy of FGH96 material for turbine engine at higher stress gradient notch, such as bolt holes, the new mean stress formula is used in this paper, the effect of stress gradient and size effect are considered at the same time, Fatigue test of FGH96 material inter-stage disc simulation test piece is done, and the parameters in the life prediction equation of the model are fitted. Further study on fatigue test of FGH96 material turbine pin bolt hole simulation unit is done, and test results is compared with the forecast results. The result shows that, the improved fatigue life prediction method has higher accuracy, and the validity of the method is proved.
作者
刘红彬
陈伟
刘林
LIU Hongbin;CHEN Wei;LIU Lin(School of Energy and Power, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;AECC Sichuan Gas Turbine Establishment, Chengdu 610500, China)
出处
《西北工业大学学报》
EI
CAS
CSCD
北大核心
2019年第4期744-750,共7页
Journal of Northwestern Polytechnical University
关键词
FGH96
涡轮盘
螺栓孔
平均应力
参数拟合
寿命预测
疲劳试验
模拟
FGH96 material
turbine disk
bolt hole
average stress
parameter fitting
life prediction
fatigue test
simulation