涡轮盘多轴低循环疲劳寿命预测及试验验证

杨俊; 李承彬; 谢寿生

涡轮盘多轴低循环疲劳寿命预测及试验验证

1.
中国人民解放军空军西安局某军事代表室,西安 710021
2.
空军工程大学工程学院,西安 710051
3.
中国航空工业集团公司西安航空发动机 (集团) 有限公司,西安 710021

基金项目: 总装关于某型发动机综合整治科研项目(10116-2004); 西航集团“十一五”可靠性科研项目(XAEC-JPS-JHB-1005-0031)

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出版历程
- 收稿日期: 2010-11-05
- 修回日期: 2011-04-04
- 刊出日期: 2011-10-28

Multiaxial low cycle fatigue life prediction and test verification for turbine disk

1.
A Military Representative Office, Airforce Xi'an Bureau, The Chinese People's Liberation Army, Xi'an 710021, China
2.
The Engineering Institute, Air Force Engineering University, Xi'an 710051, China
3.
Xi'an Aero-engine (Group) Corporation Limited, Aviation Industry Corporation of China, Xi'an 710021, China

摘要

摘要: 应用单轴及多轴疲劳寿命预测的Von Mises等效应变模型和临界平面模型对某两级涡轮盘传动臂销钉孔的疲劳寿命进行预测.组装和调试了全尺寸两级涡轮盘联合试验件,在旋转试验器上完成了低循环疲劳试验,得到两级涡轮盘传动臂销钉孔试验失效寿命.预测寿命与试验寿命对比分析显示单轴和Von Mises等效应变模型预测误差较大;临界平面模型误差较小,尤其是拉伸型失效SWT(Smith-Watson-Topper)模型误差为9.26%.
- 涡轮盘 /
- 多轴低循环疲劳 /
- 临界平面 /
- 寿命预测 /
- SWT (Smith-Watson-Topper) 模型 /
- Von Mises等效应变模型
Abstract: The fatigue life of a two-stage turbine disk transmission arm pin hole was predicted by the models of uniaxial,Von Mises strain and critical plane.A full-scale two-stage turbine disk was fabricated and debugged,and then tested for LCF(low cycle fatigue).The predicted life was compared with the life evaluated by fatigue test of real turbine disk,and the result shows that the predicted errors of the critical plane model are less than those of the uniaxial model and the Von Mises strain model,especially the error of SWT(Smith-Watson-Topper)model is 9.26%.
- turbine disk /
- multiaxial low cycle fatigue /
- critical plane /
- life prediction /
- SWT(Smith-Watson-Topper) model /
- Von Mises strain model

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参考文献(14)

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