基于复合疲劳试验的涡轮叶片振动应力反推法

孙瑞杰; 闫晓军; 聂景旭

基于复合疲劳试验的涡轮叶片振动应力反推法

北京航空航天大学能源与动力工程学院, 北京 100191

基金项目: 国家自然科学基金(10872015)

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出版历程
- 收稿日期: 2011-03-30
- 修回日期: 2011-07-30
- 刊出日期: 2012-02-28

Inverse method for estimating the vibration stress of turbine blades based on combined high-and-low cycle fatigue tests

School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

摘要

摘要: 提出了一种利用复合疲劳试验和外场故障数据反推涡轮叶片实际振动应力的方法.该方法针对与故障叶片同批次的叶片,开展数个振动应力水平下的单件试验和某一特定振动应力水平下的成组试验,利用极大似然法推导出叶片的概率-应力-寿命曲线(P-S-N);最后基于99.87%存活率下的概率-应力-寿命曲(P_99.87%-S-N),结合叶片的外场故障统计结果,反推出叶片实际工作中振动应力的范围和可能的最大振动应力.
- 涡轮叶片 /
- 改型 /
- 高、低周复合疲劳(HCF/LCF) /
- 振动应力 /
- 疲劳特性曲线 /
- 故障统计
Abstract: An inverse method based on combined high-and-low cycle fatigue (HCF/LCF) tests and the outfield practical failure data was developed to estimate the vibration stress of the turbine blade in working condition.All the test specimens of the turbine blades owned the same production procedures as the outfield failure blades.Two groups of HCF/LCF tests were performed,one was median life test at six vibration stress levels,and the other was life dispersion test at a given vibration stress level.Then,P-S-N curves were extrapolated with the maximum likelihood method.Finally,vibration stress of the turbine blade in working condition was determined by the P_99.87%-S-N curve combined with the statistical life of the outfield practical failure data.
- turbine blade /
- retrofitting /
- combined high-and-low cycle fatigue(HCF/LCF) /
- vibration stress /
- fatigue curve /
- failure statistics

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参考文献(19)

[1]	孙瑞杰,闫晓军.涡轮叶片榫齿部位疲劳/蠕变试验的新特点[J].航空动力学报,2007,22(3):419-424. SUN Ruijie,YAN Xiaojun.New characteristics of fatigue-creep tests on serration of turbine blades[J].Journal of Aerospace Power,2007,22(3):419-424.(in Chinese)
[2]	YAN Xiaojun,NIE Jingxu.Creep-fatigue tests on full scale directionally solidified turbine blades[J].J. Eng. Gas Turbines Power,2008,130(4):044501(5 pages).
[3]	Oakley S Y,Nowell D.Prediction of the combined high- and low-cycle fatigue performance of gas turbine blades after foreign object damage[J].Int. J. Fatigue,2007,29(1):69-80.
[4]	王红,左华付.某航空发动机第三级涡轮叶片失效分析[J].失效分析与预防,2007,2(1):24-28. WANG Hong,ZUO Huafu.Failure analysis of 3rd turbine blade of aero-engines[J].Failure Analysis and Prevention,2007,2(1):24-28.(in Chinese)
[5]	Witek L.Experimental crack propagation and failure analysis of the first stage compressor blade subjected to vibration[J].Engineering Failure Analysis,2009,16(7):2163-2170.
[6]	Hou N X,Wen Z X,et al.Application of a combined high and low cycle fatigue life model on life prediction of SC blade[J].Int.J.Fatigue,2009,31(4):616-619.
[7]	Peters J O,Ritchie R O.Influence of foreign-object damage on crack initiation and early crack growth during high-cycle fatigue of Ti-6Al-4V[J].Engineering Fracture Mechanics,2000,67(3):193-207.
[8]	Byrne J,Hall R F,Powell B E.Influence of LCF overloads on combined HCF/LCF crack growth[J].Int. J. Fatigue,2003,25(9-11):827-834.
[9]	张锦,刘晓平.叶轮机振动模态分析理论及数值方法[M].北京:国防工业出版社,2001.
[10]	Cesare M A,Sues R H,Wuj Y T.Probabilistic high cycle fatigue of jet engine blades.AIAA-2001-1379,2001.
[11]	LI Haiyan,ZHANG Xueren,YAN Xiaojun,et al.A new method to calculate the vibrational stress of rotating blades[J].Aircraft Engineering and Aerospace Technology,2001,73(1):26-30.
[12]	Lawson C P,Ivey P C.Tubomachinery blade vibration amplitude measurement through tip timing with capacitance tip clearance probes[J].Sensors and Actuators A,2005,118(1):14-24.
[13]	Aeauseroy P,Lengelle R.Nonintrusive turbomachine blade vibration measurement system[J].Mech.Syst.Signal Process,2007,21(4):1717-1738.
[14]	艾延廷,张凤玲.航空发动机转子叶片振动测量技术研究[J].仪器仪表学报,2008,27(6):1242-1244. AI Yanting,ZHANG Fengling.Study on rotor blade vibration measurement in aero-engine[J].Chinese Journal of Scientific Instrument,2008,27(6):1242-1244.(in Chinese)
[15]	刘新灵,张峥,陶春虎.疲劳断口定量分析[M].北京:国防工业出版社,2010.
[16]	刘芝娜.全尺寸涡轮叶片高、低周复合疲劳试验研究.北京:北京航空航天大学,2009. LIU Zhina.Combined fatigue test methods on full-scale aero-engine turbine blades.Beijing:Beijing University of Aeronautics and Astronautics,2009.(in Chinese)
[17]	康宁,闫晓军,李小甫.高、低周复合疲劳试验中振动应力的监测与计算[J].燃气涡轮试验与研究,2010,23(4):22-25. KANG Ning,YAN Xiaojun,LI Xiaofu.Numericai calculation and measurement of the vibration stress in combined high and low cycle fatigue tests[J].Gas Turbine Experiment and Research,2010,23(4):22-25.(in Chinese)
[18]	闫晓军,孙瑞杰,邓瑛, 等.涡轮叶片复合疲劳特性曲线及其规律的试验[J].航空动力学报,2011,26(8) :1824- 1829. YAN Xiaojun,SUN Ruijie,DENG Ying,et al.Experimental study on fatigue curve law of turbine blade under combined high and low cycle loading[J].Journal of Aerospace Power,2011,26(8):1824-1829.(in Chinese)
[19]	Ling J,Pan J.A maximum likelihood method for estimating P-S-N curves[J].Int. J. Fatigue,1997,19(5):415-419.