| Metals and Metal Matrix Composites |
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| Study on Fretting Fatigue Fracture of TB6 High Strength Titanium Alloy Lugs Under Multiaxial Complex Stress |
| KONG Huanping1, 2, 3, 4, JIANG Tao1, 2, 3, 4, LIU Changkui1, 2, 3, 4, YING Shaojun5, ZHAO Kai1, 2, 3, 4
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1 AECC Beijing Institute of Aeronautical Materials, Beijing 100095, China
2 Beijing Key Laboratory of Aeronautical Materials Testing and Evaluation, Beijing 100095, China
3 Key Laboratory of Science and Technology on Aeronautical Materials Testing and Evaluation of Aero Engine Corporation of China, Beijing 100095, China
4 Aviation Key Laboratory of Science and Technology on Materials Testing and Evaluation, Beijing 100095, China
5 AVIC Changhe Aircraft Industry (Group) Corporation Ltd., Jingdezhen 333000, China |
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Abstract The fretting fatigue fracture mechanism of TB6 high strength titanium alloy under tension-torsion multiaxial stress was studied. Based on macro and micro observation, residual stress testing and computer simulation, the difference of the fretting fatigue life of the lugs with different treated conditions under tension-torsion fatigue test stress was analyzed. The characteristics of fretting fatigue crack initiation and propagation under tension-torsion fatigue test were studied, and the mechanism of fretting crack initiation was revealed. The results show that fractures propagation area of twice extrusion lugs is larger. After twice extrusion, the total life of fretting fatigue of lugs is greatly extended, and the crack initiation life accounts for more than 95% of the total life. The driving force of the crack initiation is lower and the resistance against crack initiation is better. Each fracture originates from the marks on the inner hole of lugs have heavier fretting wear. After extrusion strengthening, a higher residual compressive stress layer and a tissue strengthening layer are formed on the hole wall, which can effectively inhibit the initiation and propagation of the cracks. The formation of fretting wear layer in the inner hole of lugs is the result of the combined action of mechanical mechanism and thermal induction mechanism, and the final wear form of lugs is fatigue wear.
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Published: 14 July 2020
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| Fund:This work was financially supported by the Aeronautical Science Foundation of China (2016ZF21005). |
| About author:: Huanping Kongreceived her M.S. degree in January 2012 from Beijing University of Aeronautics and Astronautics. Since January 2012, she has been working in AECC Beijing Institute of Aeronautical Materials, mainly engaged in damage and failure analysis of metal materials. |
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1 Liu C K, Wei Z W, Zhao J, et al. Failure Analysis and Prevention, 2017,12(5),310(in Chinese).
刘昌奎, 魏振伟,赵剑, 等. 失效分析与预防, 2017,12(5),310.
2 Ouyang D L. Research on microstructure evolution and dynamic recrystallization behavior of titanium alloy TB6 and TA15 during β forging. Master's Thesis, Nanjing University of Aeronautics and Astronautics, China, 2011(in Chinese).
欧阳德来. TB6和TA15钛合金β锻组织演变及动态再结晶行为研究.硕士学位论文,南京航空航天大学,2011.
3 Zhang X, Wang Z. International Journal of Fatigue, 2003,25,1249.
4 Warner J J, Clark P N, Hoeppner D W. International Journal of Fatigue, 2014,68,209.
5 Luo X K, Ai Y J, Wang X, et al. Journal of Aeronautical Materials, 2017,37(6),88(in Chinese).
罗学坤,艾莹珺,王欣, 等. 航空材料学报, 2017,37(6),88.
6 Liu X L, Zhang W F, Tao C H. Materials for Mechanical Engineering, 2008,32(5),4(in Chinese).
刘新灵,张卫芳,陶春虎. 机械工程材料, 2008,32(5),4.
7 Zhang Y, Zhang W F, Yan H. Journal of Materials Engineering, 2000(4),45(in Chinese).
张燚,张文峰,闫海. 材料工程, 2000(4),45.
8 Waterhouse R B. Corrosion, 1972,12(3),79.
9 Collins J A, Tovey F M. Testing and Evaluation, 1972,420.
10 Nishioka K, Hirakawa K. Bulletin of the JSME, 1969,52,692.
11 Tian F, Yang H. Surface Technology, 2014, 43(1),55(in Chinese).
田峰,杨辉. 表面技术, 2014, 43(1),55. |
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2020, Vol. 34 
