Effect of creep and artificial aging on fatigue crack growth performance of 2524 aluminum alloy

被引：0
|
作者：
Liu Y.-L. [1 ,2 ]
Wang Q. [1 ]
Liu C. [1 ]
Li S.-B. [1 ]
He J. [1 ]
Zhao X.-Q. [1 ]
机构：
[1] College of Mechanical and Electrical Engineering, Central South University, Changsha
[2] Light Alloy Research Institute, Central South University, Changsha
来源：
Jilin Daxue Xuebao (Gongxueban)/Journal of Jilin University (Engineering and Technology Edition) | 2019年 / 49卷 / 05期
关键词：
2524 aluminum alloy; Aerospace materials; Creep aging; Fatigue crack propagation; Fracture mechanics; Precipitate;
D O I：
10.13229/j.cnki.jdxbgxb20180343
中图分类号：
学科分类号：
摘要：
The effects of creep aging and artificial aging on the fatigue crack propagation properties of 2524 aluminum alloy were investigated. The influence of aging conditions on the fatigue properties of the alloy was analyzed based on the microstructure evolution of the alloy under TEM. The results show that the microstructures of artificial aging and creep aging alloys are mainly Cu-Mg clusters and GPB zones after aging for 4 h, showing good fatigue resistance. Compared with 4 h, after aging for 9 h the microstructures of the alloy are mainly acicular S' phase. The appearance of these coarse S' phases changes the slip mode of dislocation, which reduces the reversibility of slip and accelerates the accumulation of fatigue damage. Near the threshold section of ΔK≤7 MPa•m^(1/2), the alloy fatigue resistance decreases significantly. The precipitate free zone appears at the grain boundary of the alloy after aging for 24 h, and the precipitates in the grain are also larger in size, further accelerating the fatigue crack growth rate of the alloy. Creep stress accelerates the precipitation process of alloy and compared with artificial aging, the creep aging alloy has larger precipitate size, higher yield strength and hardness, but lower fatigue resistance at the same aging time. © 2019, Jilin University Press. All right reserved.
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页码：1636 / 1643
页数：7
相关论文
共 24 条
  • [1] Nakai M., Eto T., New aspects of development of high strength aluminum alloys for aerospace applications, Materials Science and Engineering A, 285, 1-5, pp. 62-68, (2000)
  • [2] Starke E., Staley J.T., Application of modern aluminum alloys to aircraft, Progress in Aerospace Sciences, 32, 2, pp. 131-172, (1996)
  • [3] Warner T., Recently-developed aluminium solutions for aerospace applications, Materials Science Forum, 519-521, pp. 1271-1278, (2006)
  • [4] Zeng Y., Huang X., Forming technologies of large integral panel, Acta Aeronautica Et Astronautica Sinica, 29, 3, pp. 721-727, (2008)
  • [5] Zhan L., Lin J., Dean T.A., A review of the development of creep age forming: experimentation, modelling and applications, International Journal of Machine Tools & Manufacture, 51, 1, pp. 1-17, (2011)
  • [6] Jeunechamps P.P., Ho K.C., Lin J., Et al., A closed form technique to predict springback in creep age-forming, International Journal of Mechanical Sciences, 48, 6, pp. 621-629, (2006)
  • [7] Zhan L., Lin J., Dean T.A., Et al., Experimental studies and constitutive modelling of the hardening of aluminium alloy 7055 under creep age forming conditions, International Journal of Mechanical Sciences, 53, 8, pp. 595-605, (2011)
  • [8] Zhang J., Zhang S.N., Liang E.W., Blazar Anti-Sequence of spectral variation within individual blazars: cases for Mrk 501 and 3C 279, The Astrophysical Journal, 767, pp. 1-7, (2013)
  • [9] Jeshvaghani R.A., Zohdi H., Shahverdi H.R., Et al., Influence of multi-step heat treatments in creep age forming of 7075 aluminum alloy: optimization for springback, strength and exfoliation corrosion, Materials Characterization, 73, 11, pp. 8-15, (2012)
  • [10] Xu Y., Zhan L., Li W., Effect of pre-strain on creep aging behavior of 2524 aluminum alloy, Journal of Alloys & Compounds, 691, pp. 564-571, (2017)
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