Volume 37 Issue 8
Aug.  2022
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Article Navigation >  Journal of Aerospace Power  > 2022  >  37(8): 1761-1770
CHEN Xin，HE Yuhuai，XU Wei，et al.Very⁃high cycle fatigue strength estimation method for aero⁃engine reliability design［J］.Journal of Aerospace Power，2022，37（8）：1761‑1770. doi: 10.13224/j.cnki.jasp.20220183
Citation: CHEN Xin，HE Yuhuai，XU Wei，et al.Very⁃high cycle fatigue strength estimation method for aero⁃engine reliability design［J］.Journal of Aerospace Power，2022，37（8）：1761‑1770. doi: 10.13224/j.cnki.jasp.20220183
shu

Very⁃high cycle fatigue strength estimation method for aero⁃engine reliability design

doi: 10.13224/j.cnki.jasp.20220183
  • 1.

    Beijing Institute of Aeronautical Materials， Aero Engine Corporation of China，Beijing 100095，China

  • 2.

    Beijing Key Laboratory of Aeronautical Materials Testing and Evaluation， Beijing Institute of Aeronautical Materials， Aero Engine Corporation of China，Beijing 100095，China

  • 3.

    The State Key Laboratory of Nonlinear Mechanics， Institute of Mechanics，Chinese Academy of Sciences，Beijing 100190，China

Funds:

 91860112

  • Received Date: 2022-04-01
    Abstract

  • A four⁃parameter random fatigue limit model for reliability design was proposed，which can realize very⁃high cycle fatigue stress⁃life （S⁃N） curve processing for small sample of data.The accuracy of the model was verified by fitting analysis and comparison of very⁃high cycle fatigue data of conventional samples of titanium alloys for aviation.At the same time，TC17 titanium alloy for a specific type of aero⁃engine compressor blade was taken as the research object，and the very⁃high cycle fatigue data of small samples were processed at room temperature （RT） and 400 ℃，respectively.The very⁃high cycle fatigue strength under typical confidence and survival probability was investigated by this mode.The results showed that the four⁃parameter random fatigue limit model proposed can obtain the value of the estimated fatigue strength required for engine design in very‑high cycle regime.With a small amount of long⁃life area data，the proposed model provides a reliable method for very⁃high cycle fatigue strength evaluation of engine materials by an economical cost.

     

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    • References(31)
  • [1]
    Airaeronautical Systems Center.MIL⁃HTBK⁃1783B engine structural integrity program （ENSIP）[M].Washington:US Air Force,2004.
    [2]
    高镇同,熊峻江.疲劳可靠性[M].北京：北京航空航天大学出版社,2002.
    [3]
    洪友士,赵爱国,钱桂安.合金材料超高周疲劳行为的基本特征和影响因素[J].金属学报,2009,45（7）:769⁃780.

    HONG Youshi,ZHAO Aiguo,QIAN Guian.Essential characteristics and influential factors for very⁃high cycle fatigue behavior of metallic materials[J].ACTA Metallurgica Sinica,2009,45（7）:769⁃780.（in Chinese）
    [4]
    焦泽辉,于慧臣,钟斌,等.TA11 钛合金超高周疲劳行为[J].航空材料学报,2017,37（3）:84⁃90.

    JIAO Zehui,YU Huichen,ZHONG Bin,et al.Very high cycle fatigue behavior of TA11 titanium alloy[J].Journal of Aeronautical Materials,2017,37（3）:84⁃90.（in Chinese）
    [5]
    HU Yuanpei,SUN Chengqi,XIE Jijia,et al.Effects of loading frequency and loading type on high⁃cycle and very⁃high⁃cycle fatigue of a high⁃strength steel[J].Materials.2018,11（8）:1456.1⁃1456.17.
    [6]
    XU Wei,ZHAO Yanguang,CHEN Xin,et al.An ultra⁃high frequency vibration⁃based fatigue test and its comparative study of a titanium alloy in the VHCF regime[J].Metals，2020，10（11）:1415.1⁃1415.16.
    [7]
    许巍,陈新.TC17合金弯曲振动超高周疲劳试验[J].航空发动机,2021,47（2）:63⁃67.

    XU Wei,CHEN Xin.Vibration bending fatigue test of TC17 Ti⁃alloy in the very⁃high⁃cycle regime[J].Aeroengine,2021,47（2）:63⁃67.（in Chinese）
    [8]
    LING J,PAN J.A maximum likelihood method for estimating P⁃S⁃N curves[J].International Journal of Fatigue,1997,19（5）:415⁃419.
    [9]
    POLLAK R D,PALAZOTTO A N.A comparison of maximum likelihood models for fatigue strength characterization in materials exhibiting a fatigue limit[J].Probabilistic Engineering Mechanics,2009,24（2）:236⁃241.
    [10]
    谢金标，姚卫星.建立P⁃S⁃N曲线的双加权最小二乘法[J].实验力学,2010,25（5）:611⁃616.

    XIE Jinbiao,YAO Weixing.Double weighted least square method for P⁃S⁃N curve regression[J].Journal of Experimental Mechanics，2010,25（5）:611⁃616.（in Chinese）
    [11]
    韩希鹏,许超,段作祥,等.高周疲劳曲线的等效应力法[J].航空材料学报,2003,23（3）:53⁃57.

    HAN Xipeng,XU Chao,DUAN Zuoxiang,et al.Modified equivalent stress model for high cyclic fatigue curves[J].Journal of Aeronautical Materials,2003,23（3）:53⁃57.（in Chinese）
    [12]
    GAO J，AN Z，LIU B.A new method for obtaining P⁃S⁃N curves under the condition of small sample[J].Journal of Risk and Reliability,2017,231（2）:130⁃137.
    [13]
    BUCAR T,NAGODE M,FAJDIGA M.A neural network approach to describing the scatter of S⁃N curves[J].International Journal of Fatigue,2006,28（4）:311⁃323.
    [14]
    LEONETTI D，MALJAARS J，SNIJDER H H B.Fitting fatigue test data with a novel S⁃N curve using frequentist and Bayesian inference[J].International Journal of Fatigue,2017,105（12）:128⁃143.
    [15]
    王荣桥,刘飞,胡殿印,等.基于贝叶斯理论的低循环疲劳寿命模型不确定性量化[J].航空学报,2017,38（9）:249⁃258.

    WANG Rongqiao,LIU Fei,HU Dianyin,et al.Uncertainty quantification in low cycle fatigue life model based on Bayesian theory[J].Acta Aeronautica et Astronautica Sinica,2017,38（9）:249⁃258.（in Chinese）
    [16]
    ZHONG Bin，HUANG Xinyue，GUO Weibin，et al.Experimental study on residual fatigue life for a nickel‑based powder metallurgy superalloy[C]∥Structural Integrity and Materials Ageing in Extreme Conditions.Shanghai:International symposium on structural integrity，2010:221‑226.
    [17]
    PASCUAL F G,MEEKER W Q.Estimating fatigue curves with the random fatigue‑limit model[J].Technometrics,1999,41（4）:277⁃289.
    [18]
    PASCUAL F G.Theory for optimal test plans for the random fatigue⁃limit model[J].Technometrics,2003,45（2）:130⁃141.
    [19]
    POLLAK R D,PALAZOTTO A N.A comparison of maximum likelihood models for fatigue strength characterization in materials exhibiting a fatigue limit[J].Probabilistic Engineering Mechanics,2009,24（2）:236⁃241.
    [20]
    ZHU X,SHYAM A,MAYER H,et al.Effects of microstructure and temperature on fatigue behavior of E319⁃T7 cast aluminum alloy in very long life cycles[J].International Journal of Fatigue,Elsevier,2006,28（11）:1566⁃1571.
    [21]
    ENGLER‑PINTO C C,Sr.,LASECKI J V,FRISCH R J,Sr.,et al.Statistical approaches applied to fatigue test data analysis[R].SAE 2005⁃01⁃0802,2005.
    [22]
    HANAKI S,YAMASHITA M,UCHIDA H,et al.On stochastic evaluation of S⁃N data based on fatigue strength distribution[J].International Journal of Fatigue,Elsevier,2010,32（3）:605⁃609.
    [23]
    钟斌，马少俊，张仕朝，等.TC11钛合金棒材和锻件的室温设计许用值计算[J].航空动力学报，2020，35（10）:2195‑2204.

    ZHONG Bin，MA Shaojun，ZHANG Shichao，et al.Calculation of design allowable values for TC11 titanium bar and forging at room temperature[J].Journal of Aerospace Power，2020，35（1）:2195‑2204.（in Chinese）
    [24]
    陶春虎,刘庆泉,曹春晓,等.航空用钛合金的失效及其预防[M].北京:国防工业出版社,2002.
    [25]
    李全通,刘青川,申景生,等.TC17钛合金超高周弯曲振动疲劳试验[J].航空动力学报,2012,27（3）:617⁃622.

    LI Quantong,LIU Qingchuan,SHEN Jingsheng,et al.Experiment on ultra⁃high cycle bending vibration fatigue of titanium alloy TC17[J].Journal of Aerospace Power，2012,27（3）:617⁃622.（in Chinese）
    [26]
    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 Aerospace Power,2014,29（10）:2471⁃2475.（in Chinese）
    [27]
    高潮,程礼,彭桦,等.20 kHz下TC17钛合金超高周疲劳性能研究[J].航空动力学报,2012,27（4）:811⁃816.

    GAO Chao,CHENG Li,PENG Hua,et al.Investigation of ultra⁃high cycle fatigue behavior of TC17 alloy at a frequency of 20 kHz[J].Journal of Aerospace Power,2012,27（4）:811⁃816.（in Chinese）
    [28]
    李久楷,刘永杰,王清远,等.TC17高温高周旋转弯曲疲劳实验研究[J].四川大学学报（工程科学版）,2014,46（2）:198⁃202.

    LI Jiukai,LIU Yongjie,WANG Qingyuan,et al.High⁃cycle rotate bending fatigue behavior of TC17 at elevated temperature[J].Journal of Sichuan University （Engineering Science Edition）,2014,46（2）:198⁃202.（in Chinese）
    [29]
    刘汉青,何超,黄志勇,等.TC17合金超高周疲劳裂纹萌生机理[J].金属学报,2017,53（9）:1047⁃1054.

    LIU Hanqing,HE Chao,HUANG Zhiyong,et al.Very high cycle fatigue failure mechanism of TC17 alloy[J].ACTA Metallurgica Sinica,2017,53（9）:1047⁃1054.（in Chinese）
    [30]
    程礼,焦胜博,李全通,等.超高周疲劳与断裂[M].北京:国防工业出版社,2017.
    [31]
    SCHOLZ F W,STEPHENS M A.K‑sample Anderson⁃Darling tests[J].Journal of the American Statistical Association,1987,82（399）:918⁃924.
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