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航空铝合金系列材料裂纹扩展性能的温度效应

李矿 熊峻江 马少俊 陈勃

李矿, 熊峻江, 马少俊, 等 . 航空铝合金系列材料裂纹扩展性能的温度效应[J]. 北京航空航天大学学报, 2017, 43(4): 761-768. doi: 10.13700/j.bh.1001-5965.2016.0244
引用本文: 李矿, 熊峻江, 马少俊, 等 . 航空铝合金系列材料裂纹扩展性能的温度效应[J]. 北京航空航天大学学报, 2017, 43(4): 761-768. doi: 10.13700/j.bh.1001-5965.2016.0244
LI Kuang, XIONG Junjiang, MA Shaojun, et al. Temperature effect on crack propagation properties of aluminum alloys in aircraft[J]. Journal of Beijing University of Aeronautics and Astronautics, 2017, 43(4): 761-768. doi: 10.13700/j.bh.1001-5965.2016.0244(in Chinese)
Citation: LI Kuang, XIONG Junjiang, MA Shaojun, et al. Temperature effect on crack propagation properties of aluminum alloys in aircraft[J]. Journal of Beijing University of Aeronautics and Astronautics, 2017, 43(4): 761-768. doi: 10.13700/j.bh.1001-5965.2016.0244(in Chinese)

航空铝合金系列材料裂纹扩展性能的温度效应

doi: 10.13700/j.bh.1001-5965.2016.0244
基金项目: 

国家自然科学基金 51375033

详细信息
    作者简介:

    李矿, 男, 硕士研究生。主要研究方向:航空金属结构材料的疲劳性能

    熊峻江, 男, 博士, 教授, 博士生导师。主要研究方向:飞机结构适航性、航空复合材料新结构、飞行器系统与结构效能评估

    通讯作者:

    熊峻江, E-mail:jjxiong@buaa.edu.cn

  • 中图分类号: V252.2;TG113.1;TG115.5

Temperature effect on crack propagation properties of aluminum alloys in aircraft

Funds: 

National Natural Science Foundation of China 51375033

More Information
  • 摘要:

    高低温裂纹扩展性能是航空金属结构损伤容限设计的前提,为此,试验测定了3种系列的6种航空铝合金材料(2024-T351、2397-T8、6061-T651、7050-T7451、7050-T7452和7475-T761)在5种温度环境(-70、-54、25、125和150℃)下的裂纹扩展性能,观测了试验现象,并进行了性能对比分析和疲劳断口扫描电子显微镜(SEM)分析,研究了温度对航空铝合金材料裂纹扩展性能的影响机制,获得了具有工程参考价值的结果与结论:与25℃相比,低温下裂纹扩展阻力系数的对数值降低7%~15%,而高温下却增大5%~23%;低温下裂纹扩展指数增大7%~21%,而高温下却减少5%~34%;氢脆效应和高温氧化作用是导致裂纹扩展速率随温度升高而加快的主要原因。

     

  • 图 1  标准M (T) 试样

    Figure 1.  Standard M (T) specimen

    图 2  裂纹扩展测试

    Figure 2.  Crack propagation test

    图 3  裂纹扩展测试结果

    Figure 3.  Crack propagation test results

    图 4  7475-T761铝合金断口分析

    Figure 4.  Fractographic analysis of 7475-T761 aluminum alloy

    图 5  裂纹扩展da/dNK曲线

    Figure 5.  Crack propagation da/dNK curves

    图 6  温度对mC的影响

    Figure 6.  Temperature effect on m and C

    图 7  不同航空铝合金的对比

    Figure 7.  Comparison among different aluminum alloys in aircraft

    表  1  铝合金材料的力学性能

    Table  1.   Mechanical properties of aluminum alloy materials

    材料 E/GPa σb/MPa σs/MPa δ/%
    2024-T351 72.4 473 364 18.0
    2397-T8 70.0 472 421 9.5
    6061-T651 71.0 311 246 14.7
    7050-T7451 70.3 510 455 9.0
    7050-T7452 70.5 475 399 11.1
    7475-T761 70.5 526 482 13.3
    下载: 导出CSV

    表  2  裂纹扩展速率da/dNK参数值

    Table  2.   Parameter values of crack propagation rate da/dNK

    材料 T/℃ C m
    2024-T351 125 9.93×10-10 3.45
    25 3.56×10-11 4.08
    -54 1.17×10-12 4.87
    2397-T8 150 4.60×10-9 3.07
    25 7.61×10-10 3.51
    -70 3.52×10-11 4.22
    6061-T651 150 1.24×10-10 4.23
    25 3.10×10-11 4.48
    -70 5.63×10-12 4.80
    7050-T7451 150 9.02×10-10 3.60
    25 2.35×10-10 3.94
    7050-T7452 150 1.31×10-8 3.01
    25 6.66×10-11 4.54
    7475-T761 125 6.67×10-9 3.45
    25 1.90×10-9 3.75
    -54 3.71×10-10 4.15
    下载: 导出CSV
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出版历程
  • 收稿日期:  2016-03-29
  • 录用日期:  2016-06-24
  • 网络出版日期:  2017-04-20

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