| 基于试片超高周疲劳试验的叶片高周疲劳寿命估算方法 |
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| 引用本文： | 李全通,通旭东,高星伟,陈卫,程礼.基于试片超高周疲劳试验的叶片高周疲劳寿命估算方法[J].航空动力学报,2014,29(10):2471-2475. |
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| 作者姓名： | 李全通 通旭东 高星伟 陈卫 程礼 |
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| 作者单位： | 空军工程大学 航空航天工程学院, 西安 710038;空军工程大学 航空航天工程学院, 西安 710038;空军工程大学 航空航天工程学院, 西安 710038;空军工程大学 航空航天工程学院, 西安 710038;空军工程大学 航空航天工程学院, 西安 710038 |
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| 摘 要： | 依据梁的振动理论,推导了叶尖振幅a与叶片自振频率f乘积af值,来表征叶片振动应力;基于某型航空发动机压气机叶片材料试片超高周疲劳试验结果,结合af值理论,推断该叶片高周疲劳寿命.对该叶片进行1阶弯曲高周疲劳试验,结果显示:af值为1 700,1 800,1 900mm/s时,超高周试验疲劳试片和实际叶片的疲劳寿命均在1×107,0.7×107,0.5×107周次附近,即超高周疲劳试验试片和实际叶片的疲劳寿命基本一致.
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| 关 键 词： | af值 疲劳寿命 估算 高周疲劳 超高周疲劳 |
| 收稿时间： | 2013/6/18 0:00:00 |
Estimation method of blade high cycle fatigue life based on ultra-high cycle fatigue test of specimen |
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| LI Quan-tong,TONG Xu-dong,GAO Xing-wei,CHEN Wei and CHENG Li.Estimation method of blade high cycle fatigue life based on ultra-high cycle fatigue test of specimen[J].Journal of Aerospace Power,2014,29(10):2471-2475. |
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| Authors: | LI Quan-tong TONG Xu-dong GAO Xing-wei CHEN Wei and CHENG Li |
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| Institution: | Aeronautics and Astronautics Engineering College, Air Force Engineering University, Xi'an 710038, China;Aeronautics and Astronautics Engineering College, Air Force Engineering University, Xi'an 710038, China;Aeronautics and Astronautics Engineering College, Air Force Engineering University, Xi'an 710038, China;Aeronautics and Astronautics Engineering College, Air Force Engineering University, Xi'an 710038, China;Aeronautics and Astronautics Engineering College, Air Force Engineering University, Xi'an 710038, China |
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| Abstract: | According to girder vibration theory of beam, "af"value, which is the product of blade tip vibration amplitude "a" and frequency "f", was deduced to express vibration stress of blade. Based on the ultra-high cycle fatigue test result of a type of aero-engine compressor blade material specimen and "af" value theory, the blade high cycle fatigue life was deduced. The results of blade first order bending high cycle fatigue validated the deduction. It shows that when "af" value is 1700, 1800, 1900mm/s, the fatigue lives of ultra-high cycle fatigue test specimen and actual blade are in the vicinity of 1×107, 0.7×107 and 0.5×107 cycle, indicating the fatigue life of ultra-high cycle fatigue test specimen is consistent with the actual blade. |
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