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论文:2019,Vol:37,Issue(4):744-750 |
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引用本文： |
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刘红彬, 陈伟, 刘林. 某轮盘螺栓孔处疲劳寿命预测方法与验证[J]. 西北工业大学学报 |
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LIU Hongbin, CHEN Wei, LIU Lin. Prediction Method and Verification of Fatigue Life for a Turbine Disk with Bolt Hole[J]. Northwestern polytechnical university |
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| 某轮盘螺栓孔处疲劳寿命预测方法与验证 |
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| 刘红彬1,2, 陈伟1, 刘林2 |
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1. 南京航空航天大学 能源与动力学院, 江苏 南京 210016;
2. 中国航发四川燃气涡轮研究院, 四川 成都 610500 |
| 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。 |
| 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
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| Prediction Method and Verification of Fatigue Life for a Turbine Disk with Bolt Hole |
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| LIU Hongbin1,2, CHEN Wei1, LIU Lin2 |
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1. School of Energy and Power, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;
2. AECC Sichuan Gas Turbine Establishment, Chengdu 610500, China |
| Abstract: |
| 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. |
| Key words:
FGH96 material
turbine disk
bolt hole
average stress
parameter fitting
life prediction
fatigue test
simulation
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| 收稿日期: 2018-08-14
修回日期:
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| DOI: 10.1051/jnwpu/20193740744 |
| 通讯作者:
Email： |
| 作者简介: 刘红彬(1977-),南京航空航天大学博士研究生,主要从事航空发动机强度设计与试验研究。
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| 作者相关文章 |
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| 刘红彬 在本刊中的所有文章 |
| 陈伟 在本刊中的所有文章 |
| 刘林 在本刊中的所有文章 |
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