Effect of corrosion damage on fatigue crack initiation mechanism and growth behavior of high strength aluminum alloy

被引：2
作者：
Tan, Xiaoming [1 ]
Zhang, Danfeng [1 ]
Bian, Guixue [1 ]
Chen, Yueliang [1 ]
机构：
[1] Department of Aeronautical Mechanical Engineering, Qingdao Branch, Naval Aeronautical Engineering University, Qingdao
来源：
Jixie Gongcheng Xuebao/Journal of Mechanical Engineering | 2014年 / 50卷 / 22期
关键词：
Constituent particle; Environment spectrum; Fatigue crack growth behavior; Fatigue crack initiation mechanism; High strength aluminum alloy; Pitting corrosion;
D O I：
10.3901/JME.2014.22.076
中图分类号：
学科分类号：
摘要：
Corrosion damage are simulated through accelerated corrosion testing based on the complied environment spectrum, as result of high humidity atmosphere, salt fog, sulfur dioxide, acid rain and dry/wet alternation for aircraft structure during service. Prior corrosion and fatigue experiments are conducted for single edge notched specimen machined from 7B04-T74 advanced high strength aluminum alloy of aircraft critical structure. And the influence of different corrosion damage on fatigue crack initiation and propagation behavior is analyzed, as well as crack growth rate and fatigue life, to find the mechanism of corrosion damage on fatigue behavior. The results indicate that crack initiation site is mainly single pit in early corrosion stage, and the crack follows a relatively straight path. While the corrosion damage grows more severely, multiple small cracks initiate from several pits and there is obvious tunneling effect beneath pits, cracks follow zigzag path. The material microstructures compete with corrosion pits as crack origins. Corrosion damage seriously decreases fatigue life of aluminum alloy. Fatigue crack initiation life with corrosion damage equivalent to 12 years is only 2.2% of that without damage, which indicates crack initiation life is especially sensitive to corrosion damage. ©2014 Journal of Mechanical Engineering
引用
收藏
页码：76 / 83
页数：7
相关论文
共 30 条
  • [1] Platus D.L., Negative-stiffness-mechanism vibration isolation system , Proceedings of the SPIE-the International Society for Optical Engineering, pp. 98-105, (1999)
  • [2] Sankaran K.K., Perez R., Jata K.V., Effects of pitting corrosion on the fatigue behavior of aluminum alloy 7075-T6: Modeling and experimental studies , Materials Science and Engineering, A297, pp. 223-229, (2001)
  • [3] Gruenberg K.M., Craig B.A., Hillberry B.M., Et al., Predicting fatigue life of pre-corroded 2024-T3 aluminum , International Journal of Fatigue, 26, pp. 629-640, (2004)
  • [4] James T.B., James M.L., Richard P.G., Effect of initiation feature on Microstructure scale fatigue crack propagation in Al-Zn-Mg-Cu , International Journal of Fatigue, 42, pp. 104-121, (2012)
  • [5] James T.B., Sangshik K., Richard P.G., Effect of corrosion severity on fatigue evolution in Al-Zn-Mg-Cu , Corrosion Science, 52, pp. 498-508, (2010)
  • [6] Liao M., Rwnaud G., Bellinger N.C., Fatigue modeling for aircraft structures containing natural exfoliation corrosion , International Journal of Fatigue, 29, pp. 677-686, (2007)
  • [7] Liao M., Bellinger N.C., Komorowski J.P., Modeling the effects of prior exfoliation corrosion on fatigue life of aircraft wing skins , International Journal of Fatigue, 25, pp. 1059-1067, (2003)
  • [8] Sangshik K., James T.B., Richard P.G., Fatigue crack formation and growth from localized corrosion in Al-Zn-Mg-Cu , Engineering Fracture Mechanics, 76, pp. 651-667, (2009)
  • [9] Bruce R.C., Chris L., Liu Q.C., Et al., Can pitting corrosion change the location of fatigue failures in aircraft , International Journal of Fatigue, 61, pp. 304-314, (2014)
  • [10] Walde K., Hillberry B.M., Initiation and shape development of corrosion-nucleated fatigue cracking , International Journal of Fatigue, 29, pp. 1269-1281, (2007)
123