不同冲击角度外物损伤对TC4钛合金高循环疲劳强度的影响

包珍强; 胡绪腾; 宋迎东

doi:10.13224/j.cnki.jasp.2015.09.023

不同冲击角度外物损伤对TC4钛合金高循环疲劳强度的影响

doi: 10.13224/j.cnki.jasp.2015.09.023

1. 南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室, 南京 210016;
2. 南京航空航天大学机械结构力学及控制国家重点实验室, 南京 210016

基金项目:

国家自然科学基金青年基金(51105198)

详细信息

作者简介:
包珍强(1989-),男,安徽芜湖人,硕士生,主要从事材料与结构的疲劳研究.

中图分类号: V231.9
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出版历程
- 收稿日期: 2014-03-21
- 刊出日期: 2015-09-28

Effect of foreign object damage at different impact angles onhigh cycle fatigue strength of TC4 titanium alloys

1. Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;
2. State Key Laboratory of Mechanics and Control of Mechanical Structures, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

摘要

摘要: 基于空气炮冲击试验装置在不同冲击角度下进行了TC4钛合金平板试件的外物损伤模拟试验,采用逐级加载试验方法测试获得了光滑和冲击损伤试件的高循环疲劳(high cycle fatigue,HCF)强度,研究了冲击角度、冲击位置以及冲击损伤宏观几何尺寸与HCF强度的关系.结果表明:不同冲击角度下的损伤对HCF强度的影响程度不同.冲击损伤在试件边缘时,30°冲击使试件HCF强度的下降幅度最大;冲击损伤在试件表面时,60°冲击使试件HCF强度的下降幅度最大.试件边缘产生的缺口使HCF强度的下降幅度一般大于试件表面产生弹坑的影响.但在60°冲击时,冲击缺口损伤的影响要小于冲击弹坑损伤的影响.冲击损伤宏观几何尺寸一定程度上可以表征损伤试件HCF强度下降的严重程度.
- TC4钛合金 /
- 高循环疲劳 /
- 高速弹道冲击 /
- 外物损伤 /
- 冲击角度
Abstract: Based on the air-gun impact test device, the foreign object damage (FOD) simulation test of TC4 titanium alloy plate specimens was conducted at different impact angles. The high cycle fatigue (HCF) strength of smooth and impact damage samples was obtained with the step-test method. The relationship among the impact angles, impact positions, macroscopic geometry of impact damage and HCF strength of the damaged samples was studied. Results show that, the effect of impact damages on the HCF strength at different impact angles is not the same. When the impact damage appears at the edge of sample, the maximum decrease of HCF strength occurs in the impaction of 30°; while the impact damages appear at the middle of sample, the maximum decrease of HCF strength occurs in the impaction of 60°. In most cases, impact notches at the samples' edge compared to impact pits at the sample's intermediate surface have a more seriously effect on the HCF strength. However, at the impaction of 60°, the impact pit damage has a more serious effect. The geometry of the impact damage to a certain extent can characterize the changes of the HCF strength severity of damaged sample.
- TC4 titanium alloy /
- high cycle fatigue /
- high-speed ballistic impact /
- foreign object damage /
- impact angle

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参考文献(17)

[1]	国防科学技术工业委员会.GJB241-87航空涡轮喷气和涡轮风扇发动机通用规范[S].北京:国防科学技术工业委员会军标出版发行部,1987.
[2]	Cowles B A.High cycle fatigue in aircraft gas turbines:an industry perspective[J].International Journal of Fracture,1996,80(2/3):147-163.
[3]	North Atlantic Treaty Organization.Best practices for the mitigation and control of foreign[R].Research and Technology Organization,RTO TR-AVT-094,2005.
[4]	Martinez C M.Effects of ballistic impact damage on fatigue crack initiation in Ti-6Al-4V simulated engine blades[D].Dayton,Ohio:University of Dayton,2000.
[5]	Storace A F.Foreign object impact design criteria[R].Air Force Aerospace Propulsion Laboratory,AFAPL-TR-78-81.
[6]	Nicholas T,Barber J P,Bertke R S.Impact damage on titanium leading edges from small hard objects[J].Experimental Mechanics,1980,20(3):357-364.
[7]	Huber N.Plan to control high cycle fatigue in engines[R].San Antonio,Texas:USAF Structural Integrity Program Conference,1995.
[8]	Peters J O,Ritchie R O.Foreign object damage and high cycle fatigue:role of microstructure in Ti-6Al-4V[J].International Journal of Fatigue,2001,23(suppl.1):413-421.
[9]	Peters J O,Ritchie R O.Foreign object damage and high cycle fatigue of Ti-6Al-4V[J].Material Science and Engineering:A,2001,319/320/321:597-601.
[10]	Ruschau J,Nicholas T,Thompson S.Influence of foreign object damage (FOD) on the fatigue life of simulated Ti-6Al-4V airfoils[J].International Journal of Impact Engineering,2001,25(3):233-250.
[11]	Weeks C,Bastnagel P,Cook T,et al.FOD analytical modeling:FOD event modeling[R].Air Force Research Laboratory,AFRL-ML-WP-TR-2001-4159,2001.
[12]	国家标准化管理委员会.GB/T 13810-2007外科植入物用钛及钛合金加工材[S].北京:中国标准出版社,2007.
[13]	Nowell D,Duo,P,Stewart I F.Prediction of fatigue performance in gas turbine blades after foreign object damage[J].International Journal Fatigue,2003,25(9/10/11):963-969.
[14]	Dunham J M A,Mech G I E,Grad R.Damage to axial compressors[J].Journal of the Royal Aeronautical Society,1959,63:576-580.
[15]	国家标准化管理委员会.GB 3075-82 金属轴向疲劳试验方法[S].北京:中国标准出版社,1982.
[16]	高镇同.疲劳性能测试[M].北京:国防工业出版社,1980.
[17]	Maxwell D C,Nicholas T.A rapid method for generation of a haigh diagram for high cycle fatigue[R].ASME Paper STP 1332-EB,1999.