| 一种涡轮机匣挂钩槽疲劳寿命研究的试验方案 |
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| 引用本文： | 刘春风,张允华,张小勇,闫晓军,聂景旭.一种涡轮机匣挂钩槽疲劳寿命研究的试验方案[J].航空动力学报,2014,29(11):2735-2742. |
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| 作者姓名： | 刘春风 张允华 张小勇 闫晓军 聂景旭 |
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| 作者单位： | 北京航空航天大学 能源与动力工程学院, 北京 100191;中国航天科技集团公司 中国航天空气动力技术研究院, 北京 100074;中国航空工业集团公司 南方航空工业(集团)有限公司, 湖南 株洲 412002;北京航空航天大学 能源与动力工程学院, 北京 100191;北京航空航天大学 能源与动力工程学院, 北京 100191;北京航空航天大学 能源与动力工程学院 航空发动机气动热力国家级重点实验室, 北京 100191;北京航空航天大学 能源与动力工程学院, 北京 100191 |
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| 基金项目： | 国家自然科学基金(11272025) |
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| 摘 要： | 提出了一种针对涡轮机匣挂钩槽疲劳寿命的试验方案.该方案首先对涡轮机匣进行数值分析,得到危险部位的应力分布,再通过常温下机械加载来模拟危险部位总应力场,并在该载荷下获取涡轮机匣挂钩槽疲劳寿命.利用该方案,对新制作的涡轮机匣结构改进措施、原有涡轮机匣维修措施以及腐蚀影响进行了试验研究.结果表明:1新制作的涡轮机匣挂钩槽增加倒圆半径为0.8mm的圆角后,安全寿命在50%,95%置信度下可分别增加69%和198%;2原有涡轮机匣挂钩槽铣倒圆半径为1.5mm的内圆角后可以获得与新制作的涡轮机匣挂钩槽相近的疲劳寿命;3腐蚀会严重影响涡轮机匣挂钩槽的疲劳寿命.
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| 关 键 词： | 挂钩槽 疲劳裂纹 涡轮机匣 概率-应力-循环次数(P-S-N)曲线 疲劳试验 |
| 收稿时间： | 2013/5/27 0:00:00 |
An experimental scheme of investigating fatigue life of turbine casing slot |
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| LIU Chun-feng,ZHANG Yun-hu,ZHANG Xiao-yong,YAN Xiao-jun and NIE Jing-xu.An experimental scheme of investigating fatigue life of turbine casing slot[J].Journal of Aerospace Power,2014,29(11):2735-2742. |
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| Authors: | LIU Chun-feng ZHANG Yun-hu ZHANG Xiao-yong YAN Xiao-jun and NIE Jing-xu |
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| Institution: | School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;China Academy of Aerospace Aerodynamics, China Aerospace Science and Technology Corporation, Beijing 100074;South Aviation Industry Company Limited, Aviation Industry Corporation of China, Zhuzhou Hunan 412002, China;School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China |
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| Abstract: | An experimental scheme of studying the fatigue life of the turbine casing slot was presented. With the scheme, the stress field of the critical section was obtained by numerical analysis, and mechanical loading was applied to simulate the total stress field of the critical section at room temperature. Under the load, the fatigue life of the turbine casing slot can be obtained. Using the proposed scheme, structural improvement measure of new turbine casing, modification measure of old turbine casing and the effect of corrosion were evaluated experimently. The results show that: (1) rounding the new turbine casing slot corner with a 0.8mm-radius can increase the safe life by 69% and 198% with confidence of 50% and 95%, respectively; (2) a fatigue life similar to the new turbine casing slot can be obtained through cutting a 1.5mm-radius corner on the old turbine casing slot; (3) corrosion can affect the fatigue life of the turbine casing slot significantly. |
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| Keywords: | casing slot fatigue crack turbine casing probability-stress-cycle number (P-S-N) curve fatigue experiment |
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