激光冲击强化提高外物打伤钛合金模拟叶片高周疲劳性能

聂祥樊; 魏晨; 侯志伟; 汤毓源; 何卫锋

doi:10.13224/j.cnki.jasp.2021.01.016

激光冲击强化提高外物打伤钛合金模拟叶片高周疲劳性能

doi: 10.13224/j.cnki.jasp.2021.01.016

基金项目: 博士后创新人才支持计划项目(BX201700077)；博士后面上项目(191785)；陕西省自然科学基金(2018JQ5125)

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出版历程
- 收稿日期: 2020-06-09
- 刊出日期: 2021-01-28

Improving fatigue performance of titanium alloy simulated-blade subjected to foreign object damage by laser shock peening

1.
Science and Technology on Plasma Dynamics Laboratory,Air Force Engineering University,Xi’an 710038,China
2.
School of Mechanical and Power Engineering,East China University of Science and Technology,Shanghai 200237,China

摘要

摘要: 为指导钛合金叶片抗外物打伤激光冲击强化工艺设计,根据真实叶片叶型特征设计了刃口型模拟叶片,采用两种激光冲击强化工艺对模拟叶片进行预处理,并采用空气炮系统进行外物打伤模拟试验,最后通过疲劳试验和应力场预测进行疲劳性能影响规律及机理分析。试验结果表明:模拟叶片外物打伤后疲劳强度由51845 MPa降为29072 MPa,而激光能量为5 J和7 J强化工艺下疲劳强度分别提升至34449、37493 MPa。激光冲击引入高数值残余压应力场,大大改善了外物打伤区域的局部应力场分布,在显著提高外物打伤模拟叶片疲劳强度的同时,可承受更大的应力集中,也增大了疲劳缺口系数偏差。两种强化工艺中激光能量越大,产生的残余压应力场数值和深度越大,更加有效地降低裂纹扩展过程中的等效应力强度因子幅值,外物打伤模拟叶片疲劳强度和疲劳缺口系数偏差提高程度越大。
- 钛合金模拟叶片 /
- 激光冲击强化 /
- 外物打伤 /
- 高周疲劳强度 /
- 疲劳缺口系数 /
- 残余应力
Abstract: In order to design appropriate technics for solving foreign object damage (FOD) problem, a simulated-blade was designed according to aero-engine compressor blade size characteristics, then pre-treated by two laser shock strengthening processes, and impacted by air gun system. The effect rule and strengthening mechanism on fatigue performance were analyzed by high-cycle axial fatigue tests and stress field analysis. Test results indicated that fatigue strength of simulated-blade decreased from 51845 MPa to 29072 MPa subjected to foreign object damage. When pre-treated by laser shock peening with 5 J and 7 J, fatigue strength was improved to 34449 MPa and 37493 MPa, respectively. The introduction of high compressive residual stress field by laser shock peening greatly improved the local stress field distribution in the damage area, which not only significantly improved the fatigue strength of the simulated blade, but also increased the deviation of fatigue notch factor. With these two technics, the greater laser energy means the greater residual stress value and depth, helping to reduce more effectively the amplitude of the equivalent stress intensity factor in the crack propagation process, and bring about the greater increase of fatigue strength and fatigue notch factor deviation of the damaged simulated blade.
- titanium alloy simulated-blade /
- laser shock peening /
- foreign object damage /
- ,high-cycle fatigue strength /
- fatigue notch factor /
- residual stress

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参考文献(21)

[1]	WITEK L.Crack propagation analysis of mechanically damaged compressor blades subjected to high cycle fatigue［J］.Engineering Failure Analysis,2011,18(4):1223-1232.
[2]	李应红.激光冲击强化理论与技术［M］.北京:科学出版社,2013:274-275.
[3]	COWLES B,MORRIS B,NAIK R,et al.Applications,benefits,and challenges of advanced surface treatments surface treatments-an industry perspective［R］.Houston,Texas,US:the First International Conference on Laser Peening,2008.
[4]	BARTSCH T M.High cycle fatigue (HCF) science and technology program 2002 annual report［R］.Tampa,US:Universal Technology Corporation,2003.
[5]	LIN B,LUPTON C,SPANRAD S,et al.Fatigue crack growth in laser-shock-peened Ti-6Al-4V aerofoil specimens due to foreign object damage［J］.International Journal of Fatigue,2014,59:23-33.
[6]	ZABEEN S,PREUSS M,WITHERS P J.Evolution of a laser shock peened residual stress field locally with foreign object damage and subsquent fatigue crack growth［J］.Acta Materialia,2015,83:216-226.
[7]	李东霖,何卫锋,游熙,等.激光冲击强化提高外物打伤TC4钛合金疲劳强度的试验研究［J］.中国激光,2016,43(7):122-130. LI Donglin,HE Weifeng,YOU Xi,et al.Experimental research on improving fatigue strength of wounded TC4 titanium alloy by laser shock peening［J］.Chinese Journal of Lasers,2016,43(7):122-130.(in Chinese)
[8]	吴俊峰,邹世坤,张永康,等.激光冲击强化TC17叶片前缘模拟件的抗FOD性能［J］.稀有金属材料与工程,2018,47(11):113-118. WU Junfeng,ZOU Shikun,ZHANG Yongkang,et al.FOD resistance of the simulator samples of TC17 blades leading edges with laser shock processing［J］.Rare Metal Materials and Engineering,2018,47(11):113-118.(in Chinese)
[9]	ARIF A F M.Numerical prediction of plastic deformation and residual stresses induced by laser shock processing［J］.Journal of Materials Processing Technology,2003,136:117-182.
[10]	CHEN X,HUTCHINSON J W.Foreign object damage and fatigue crack threshold:cracking outside shallow indents［J］.International Journal of Fracture,2001,107(1):31-51.
[11]	MAXWELL D C,NICHOLAS T A.Rapid method for generation of a Haigh diagram for high cycle fatigue［J］.Fatigue and Fracture Mechanics,1999,29(1):626-641.
[12]	《中国航空材料手册》编辑委员会.中国航空材料手册:钛合金铜合金［M］.第2版.北京:中国标准出版社,2002:15-59.
[13]	黄伟,陈伟,潘辉,等.外物损伤对钛合金TC4高周疲劳强度的影响研究［J］.机械强度,2014,36(3):357-362. HUANG Wei,CHEN Wei,PAN Hui,et al.Effect of foreign object damage upon the high cycle fatigue strength of TC4［J］.Journal of Mechanical Strength,2014,36(3):357-362.(in Chinese)
[14]	许祥胜,赵振华,陈伟.外物损伤对TC4钛合金的高周疲劳强度的影响［J］.航空发动机,2017,43(3):88-92. XU Xiangsheng,ZHAO Zhenhua,CHEN Wei.The influences of foreign object damage on the high cycle fatigue behavior of titanium alloy TC4［J］.Aeroengine,2017,43(3):88-92.(in Chinese)
[15]	NICHOLAS T,THOMPSON S R,WILLIAM J,et al.Comparison of fatigue limit strength of Ti-6Al-4V intension and torsion after real and simulated foreign object damage［J］.International Journal of Fatigue,2005,27(10):1637-1643.
[16]	NEUBER H.Theory of notch stresses-principle for exact stress calculation［M］.Ann Arbor,US:Edwards Brothers Incorporation,1946:54-71.
[17]	LANNING D B,NICHOLAS T,HARITOS G K,et al.On the use of critical distance theories for the prediction of the high cycle fatigue limit in notched Ti-6Al-4V［J］.International Journal of Fatigue,2005,27(1):45-47.
[18]	熊再银,秦胜欢,李柳,等.Q235钢缺口试样拉压低循环疲劳的实验研究［J］.固体力学学报,2015,36(5):410-420. XIONG Zaiyin,QIN Shenghuan,LI Liu,et al.Experimental investigation on tension-compression low cycle fatigue of Q235 steel notched specimens［J］.Chinese Journal of Solid Mechanics,2015,36(5):410-420.(in Chinese)
[19]	MARANDI S M,RAHMANI K,TAJDARI M.Foreign object damage on the leading edge of gas turbine blades［J］.Aerospace Science and Technology,2014,33(1):65-75.
[20]	裴亚田.激光冲击双相钛合金TC17强化机理及延寿机理研究［D］.北京:北京化工大学,2017.
[21]	陈传尧.疲劳与断裂［M］.武汉:华中科技大学出版社,2002:97-99.