某型钛铝合金航空发动机叶片高温高周振动疲劳实验

张部声; 祝济之; 史剑

doi:10.13224/j.cnki.jasp.2020.06.006

某型钛铝合金航空发动机叶片高温高周振动疲劳实验

doi: 10.13224/j.cnki.jasp.2020.06.006

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出版历程
- 收稿日期: 2019-12-09
- 刊出日期: 2020-06-28

Test of vibration fatigue for the TiAl alloy aeroengine blade at high temperature and high cycle

1.
Tianjin Aerospace Reliability Technology Company Limited,Tianjin 300462,China
2.
Sichuan Gas Turbine Establishment,Aero Engine Corporation of China,Chengdu 610500,China

摘要

摘要: 以某型钛铝合金航空发动机叶片为研究对象,针对该型叶片高温高周振动疲劳实验时遇到的高温疲劳应力监测、高频激励等问题进行了实验方法研究。采用闭环控制最大应力的方法解决了高温疲劳应力的监测,通过夹具放大设计实现了高频激励,利用辐射加热和电磁振动台完成了温度载荷和振动载荷的综合施加。运用所述的高温高周振动疲劳实验方法,对该型叶片进行了寿命实验。实验的高温疲劳应力控制精度优于±2%,得到该型叶片可靠度为50%的中值疲劳极限是444 MPa,并有效获得了其寿命曲线。该实验方法适合航空发动机叶片高温高周振动疲劳实验,并可为其他航空发动机零部件高温高周疲劳实验提供参考。
- 发动机叶片 /
- 高温高周 /
- 振动疲劳 /
- 疲劳极限 /
- 寿命曲线 /
- 发动机零部件
Abstract: Taking TiAl alloy aeroengine blade as the research object, a series of problems likely to happen during the test of the vibration fatigue for aeroengine blade at high temperature and high cycle were studied, including fatigue stress monitoring at high temperature, and high frequency excitation. The closed loop of maximum stress was used to solve the high-temperature fatigue stress monitoring. The high frequency excitation was realized through design of fixture amplification. The temperature load and vibration load were applied synthetically by radiation heating and electromagnetic vibration shaker. Using the method of the vibration fatigue at high temperature and high cycle, the life test was carried out on the blade. The control accuracy of high temperature fatigue stress was better than ±2%. The median fatigue limit value of the blade with 50% reliability was 444 MPa. The life curve of the blade was obtained effectively. This test method is suitable for the high temperature and high cycle vibration fatigue test of the aeroengine blade, providing a reference to the high temperature and high cycle vibration fatigue test of the other aeroengine parts.
- aeroengine blade /
- high temperature and high cycle /
- vibration fatigue /
- ,fatigue limit /
- life curve /
- aeroengine parts

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参考文献(18)

[1]	宋兆泓.航空发动机典型故障分析［M］.北京:北京航空航天大学出版社,1993.
[2]	李静,孙强,李春旺,等.某型航空发动机压气机叶片振动疲劳寿命研究［J］.应用力学学报,2011,28(2):189-193,217. LI Jing,SU Qiang,LI Chunwang,et al.Study on the vibration fatigue life for aero-engine compressor blade［J］.Chinese Journal of Applied Mechanics,2011,28(2):189-193,217.(in Chinese)
[3]	李全通,通旭东,高星伟,等.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. LI Quantong,TONG Xudong,GAO Xingwei,et al.Estimation method of blade high cycle fatigue life based on ultra-high cycle fatigue test of specimen［J］.Journal of Aerospcace Power,2014,29(10):2471-2475.(in Chinese)
[4]	何胜帅,陈立伟,强笑辉,等.航空发动机叶片高应力振动疲劳试验技术研究［J］.装备环境工程,2013,10(4):41-46. HE Shengshuai,CHEN Liwei,QIANG Xiaohui,et al.High stress vibration fatigue test technology of aeroengine blade［J］.Equipment Environmental Engineering,2013,10(4):41-46.(in Chinese)
[5]	杨强,邵闯,方可强.航空发动机复合材料叶片振动疲劳特性研究［J］.实验力学,2014,29(3):361-367. YANG Qiang,SHAO Chuang,FANG Keqiang.Vibration fatigue characteristic study of aeroengine composite blade［J］.Journal of Experimental Mechanics,2014,29(3):361-367.(in Chinese)
[6]	唐铃,尚柏林,高星伟,等.某型发动机风扇叶片振动应力监控方法［J］.噪声与振动控制,2016,36(4):206-209,216. TANG Ling,SHANG Bolin,GAO Xingwei,et al.Method for vibration stress monitoring of engine fan blades［J］.Noise and Vibration Control,2016,36(4):206-209,216.(in Chinese)
[7]	胡安辉,马康民.某型航空发动机压气机四级转子叶片振动特性分析［J］.失效分析与预防,2006(4):10-12. HU Anhui,MA Kangmin.Investigation on vibration characteristics of 4th compressor blades in aero-engine［J］.Failure Analysis and Prevention,2006(4):10-12.(in Chinese)
[8]	李锋,何宇廷,李鸿鹏,等.某型航空发动机压气机四级转子叶片失效分析［J］.材料工程,2006(增刊1):382-384. LI Feng,HE Yuting,LI Hongpeng.Failure analysis for compressor blade of the fourth stage in an aero-engine［J］.Journal of Materials Engineering,2006(Suppl.1):382-384.(in Chinese)
[9]	李晓莹.传感器与测试技术［M］.北京:高等教育出版社,2004.
[10]	张忠平,孙强,李春旺,等.航空发动机压气机叶片振动疲劳寿命与af值的关系［J］.应用力学学报,2006,23(3):459-461,514. ZHANG Zhongpin,SUN Qiang,LI Chunwang,et al.The relationship between aeroengine compressor blade fatigue life and af value［J］.Chinese Journal of Applied Mechanics,2006,23(3):459-461,514.(in Chinese)
[11]	焦胜博,程礼,陈煊,等.Ti-6Al-4V钛合金振动弯曲超高周疲劳及寿命预测模型研究［J］.实验力学,2016,31(6):730-740. JIAO Shengbo,CHENG Li,CHEN Xuan,et al.On the very high cycle fatigue and life prediction model of Ti-6Al-4V titanium alloy subjected to vibration bending［J］.Journal of Experimental Mechanics,2016,31(6):730-740.(in Chinese)
[12]	尹福炎.高温/低温电阻应变片及其应用［M］.北京:国防工业出版社,2014.
[13]	许正功,陈宗帖,黄龙发.表面形变强化技术的研究现状［J］.装备制造技术,2007(4):69-71,75. XU Zhenggong,CHEN Zongtie,HUANG Longfa.Research on the outline of strengthening technology of surface deformation［J］.Equipment Manufacture Technology,2007(4):69-71,75.(in Chinese)
[14]	刘阳春.方兴未艾的喷丸强化处理新技术［J］.世界产品与技术,1997(2):10-11. LIU Chunyang.The new technology of shot penning［J］.The World Production and Technology,1997(2):10-11.(in Chinese)
[15]	中华人民共和国航空工业部.发动机叶片及材料振动疲劳试验方法:HB 5277-1984［S］.北京:国防科学技术工业委员会,1986:288-296.
[16]	高雄兵,何凌川,于进学,等.一种降低叶片高周疲劳实验件频率的配重块连接结构:CN103728111A［P］.2014-04-16.
[17]	姚春斌,李杰,朱正邦.一种发动机叶片高应力振动疲劳实验技术研究:CN206177542U［P］.2017-05-17.
[18]	姚春斌,李杰,张部声.放大夹具在整体叶轮叶片振动疲劳实验中的应用［J］.环境技术,2018,36(3):11-16. YAO Chunbin,LI Jie,ZHANG Busheng.Application of magnified fixture in vibration fatigue test of integral impeller blade［J］.Environmental Testing,2018,36(3):11-16.(in Chinese)