高强7050-T7451铝合金厚板的疲劳断口特征
Fatigue Fracture Characteristic of 7050-T7451 High-Strength Aluminum Alloy Thick Plate
摘 要
对7050-T7451铝合金厚板进行了疲劳试验, 并采用光学显微镜、扫描电镜等观察了不同应力幅值下疲劳试样断口, 重点分析厚板试样疲劳裂纹萌生区与扩展区的微观特征。结果表明: 其疲劳裂纹主要在材料中富铁脆性化合物夹杂处萌生, 其位置一般为材料表面或者近表面区, 在240 MPa应力幅值下, 裂纹源距表面距离约为158.64 μm, 而在340 MPa应力幅值下的距离约为120.10 μm; 裂纹扩展区域出现了二次裂纹、峭壁等微观特征, 且疲劳辉纹的间距随应力幅值的增大而增大。
疲劳断口
裂纹扩展
疲劳辉纹
厚板
7050-T7451 Al alloy
fatigue fracture
crack propagation
fatigue striation
thick plate
Abstract
The fatigue test for 7050-T7451 high-strength aluminum alloy thick plate was carried out, and the fatigue fractures at different stress amplitudes were observed by optical microscopy and scanning electron microscopy. The microscopic characteristics of crack initiation region and crack propagation region of the alloy were analyzed with an emphasis. The results showed that the fatigue cracks initiated from or near the surface of the specimen where the brittle Fe-rich compound inclusion particles were. The distance from crack initiation to the surface was 158.64 μm under stress amplitude of 240 MPa, while it was 120.10 μm under the stress amplitude of 340 MPa. The micro characteristics of second crack and cliffs exhibited on crack propagation region. And the larger the stress was, the wider the fatigue striations were.
中图分类号 TG146.1
所属栏目 试验研究
基金项目
收稿日期 2012/4/14
修改稿日期 2013/3/21
网络出版日期
作者单位点击查看
备注王艺淋(1988-), 女, 湖南常德人, 硕士研究生。
引用该论文: WANG Yi-lin,PAN Qing-lin,WEI Li-li,LI Bo,LI Chen. Fatigue Fracture Characteristic of 7050-T7451 High-Strength Aluminum Alloy Thick Plate[J]. Materials for mechancial engineering, 2013, 37(6): 26～30
王艺淋,潘清林,韦莉莉,李波,李晨. 高强7050-T7451铝合金厚板的疲劳断口特征[J]. 机械工程材料, 2013, 37(6): 26～30
被引情况:
【1】彭金波,康国政,刘宇杰,卢福聪,陈辉, "5083H111轧制铝合金的低周疲劳行为",机械工程材料 39, 39-41(2015)
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参考文献
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【3】SURESH R A. 材料的疲劳[M].王中光, 译. 北京: 国防工业出版社, 1993.
【4】FRIDLYANDER J N. Development and application of high strength Al-Zn-Mg-Cu alloys for aerospace application[J].Materials Science and Engineering, 2000(2): 102-107.
【5】AL-RUBAIE K S, BARROSO E K L, GODERFROID LB. Fatigue crack growth analysis of pre-strained 7475-T7351 aluminum alloy[J].International Journal of Fatigue, 2006, 28: 934-942.
【6】FROUSTEY C, LATAILLADE J L. Influence of the microstructure aluminum alloys on their residual impact properties after a fatigue loading program[J].Materials Science and Engineering A, 2009, 500(1): 155-163.
【7】MAYER H. Influence of prosity on the fatigue limit of die cast magnesium and aluminum alloys[J].International Journal of Fatigue, 2003, 25(5): 245-256.
【8】LUDWING W, BUFFIIERE J Y, SAVELLI S, et al. Study of the interaction of a short fatigue crack with grain boundaries in a cast Al alloy using X-ray microtomography[J].Acta Materialia, 2003, 51: 585-598.
【9】LANKFORD J. The influence of microstructure on the growth of small fatigue cracks[J].Fatigue Eng Mater Struct, 1985, 8(2): 161-75.
【10】钟群鹏, 赵子华, 张峥.断口学的发展及微观断裂机理研究[J].机械强度, 2005, 27(3): 358-370.
【11】孙晓旭, 郑子樵, 陈圆圆, 等.含Zr Al-Zn-Mg合金的微观组织与疲劳行为[J].中国有色金属学报, 2009, 19(1): 50-55.
【12】樊喜刚.Al-Zn-Mg-Cu-Zr合金组织性能和断裂行为的研究[D].哈尔滨: 哈尔滨工业大学, 2007: 1-274.
【13】DUMONT D, DESCHAMPS A, BRECHET Y. A model for predicting fracture mode and toughness in 7000 series aluminum alloy[J].Acta Materials, 2004, 52(9): 2529-2540.
【14】CLEMENT P, ANGELI JP, PINEAU A. Short crack behavior innodular cast iron[J].Fatigue Eng Mater Struct, 1984, 7(4): 251-65.
【15】MACDONALD D E. Slipless fatigue in titanium[J].Journal of The Institute of Metals, 1972, 100: 73-77.
【16】BARTER S A, MOLENT L, WANHILL R J H. Typical fatigue-initiating discontinuities in metallic aircraft structures[J].International Journal of Fatigue, 2012, 41(3): 11-22.
【17】DONNELLY E, NELSON D. A study of small crack growth in aluminum alloy 7075-T6[J].International Journal of Fatigue, 2002, 24(11): 1175-1189.
【18】SRIVATSAN T S, ANAND S, SRIRAM S, et al. The high-cycle fatigue and fracture behavior of aluminum alloy 7055[J].Materials Science and Engineering A, 2000, 281(1/2): 292-304
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