热力耦合模拟服役条件对DZ406合金组织和持久性能的影响

贾新云 宗毳 郭婧 陈升平 郑真 赵文侠 黄朝晖

贾新云, 宗毳, 郭婧, 陈升平, 郑真, 赵文侠, 黄朝晖. 热力耦合模拟服役条件对DZ406合金组织和持久性能的影响[J]. 航空材料学报, 2022, 42(2): 83-90. doi: 10.11868/j.issn.1005-5053.2021.000172
引用本文: 贾新云, 宗毳, 郭婧, 陈升平, 郑真, 赵文侠, 黄朝晖. 热力耦合模拟服役条件对DZ406合金组织和持久性能的影响[J]. 航空材料学报, 2022, 42(2): 83-90. doi: 10.11868/j.issn.1005-5053.2021.000172
JIA Xinyun, ZONG Cui, GUO Jing, CHEN Shengping, ZHENG Zhen, ZHAO Wenxia, HUANG Zhaohui. Effect of thermodynamic coupled simulation condition on microstructure and stress rupture properties of DZ406 alloy[J]. Journal of Aeronautical Materials, 2022, 42(2): 83-90. doi: 10.11868/j.issn.1005-5053.2021.000172
Citation: JIA Xinyun, ZONG Cui, GUO Jing, CHEN Shengping, ZHENG Zhen, ZHAO Wenxia, HUANG Zhaohui. Effect of thermodynamic coupled simulation condition on microstructure and stress rupture properties of DZ406 alloy[J]. Journal of Aeronautical Materials, 2022, 42(2): 83-90. doi: 10.11868/j.issn.1005-5053.2021.000172

热力耦合模拟服役条件对DZ406合金组织和持久性能的影响

doi: 10.11868/j.issn.1005-5053.2021.000172
详细信息
    通讯作者:

    贾新云(1971—),女,硕士,高级工程师,主要从事铸造高温合金的研究,E-mail: jiaxinyun@sina.com

  • 中图分类号: TG132.3

Effect of thermodynamic coupled simulation condition on microstructure and stress rupture properties of DZ406 alloy

  • 摘要: 在高温长期服役条件下高温合金涡轮叶片的组织存在老化和性能退化问题。通过对DZ406合金试样进行预先加载处理,模拟涡轮叶片的高温服役环境,热力耦合模拟条件分别为980 ℃/70 MPa,980 ℃/110 MPa,980 ℃/140 MPa与980 ℃/180 MPa,再对试样进行980 ℃/275 MPa持久实验。观察分析不同服役载荷条件下试样的显微组织和980 ℃/275 MPa持久寿命。结果表明:DZ406合金标准热处理组织由碳化物、残余(γ+γ´)共晶和规则立方状的γ´相组成;在模拟服役条件热力耦合作用下,随着服役载荷应力的增加,合金的共晶和碳化物形貌及尺寸无明显变化,平行于[001]方向试样的γ´相呈现不同程度的筏排化,垂直于[001]方向截面的γ´相尺寸明显增大;随着服役载荷应力的增加,不同热力耦合作用试样的剩余持久寿命迅速降低。

     

  • 图  1  DZ406合金标准热处理组织 (a) 碳化物和共晶相;(b) 枝晶干γ´相.

    Figure  1.  Microstructure of DZ406 alloy after heat treatment  (a) carbides and eutectic;(b) γ´ phase at the dendrite

    图  2  980 ℃/70 MPa条件下时效500 h的显微组织 (a)垂直[001]取向的碳化物和共晶相;(b)平行[001]取向的碳化物和共晶相;(c)垂直[001]取向的枝晶干γ´相;(d)平行[001]取向的枝晶干γ´相

    Figure  2.  Microstructures of the alloy after aging at 980 ℃/70 MPa for 500 h  (a) carbides and eutectic perpendicular to [001] direction;(b) carbides and eutectic parallel to [001] direction; (c) γ´ phase at the dendrite perpendicular to [001] direction;(d) γ´ phase at the dendrite parallel to [001] direction

    图  3  980 ℃/110 MPa条件下时效500 h的显微组织 (a)垂直[001]取向的碳化物和共晶相;(b)平行[001]取向的碳化物和共晶相;(c)垂直[001]取向的枝晶干γ´相;(d)平行[001]取向的枝晶干γ´相

    Figure  3.  Microstructures of the alloy after aging at 980 ℃/110 MPa for 500 h  (a) carbides and eutectic perpendicular to [001] direction;(b) carbides and eutectic parallel to [001] direction; (c) γ´ phase at the dendrite perpendicular to [001] direction;(d) γ´ phase at the dendrite parallel to [001] direction

    图  4  980 ℃/140 MPa条件下时效500 h的显微组织 (a)垂直[001]取向的碳化物和共晶相;(b)平行[001]取向的碳化物和共晶相;(c)垂直[001]取向的枝晶干γ´相;(d)平行[001]取向的枝晶干γ´相

    Figure  4.  Microstructures of the alloy after aging at 980 ℃/140 MPa for 500 h  (a) carbides and eutectic perpendicular to [001] direction;(b) carbides and eutectic parallel to [001] direction; (c) γ´ phase at the dendrite perpendicular to [001] direction;(d) γ´ phase at the dendrite parallel to [001] direction

    图  5  980 ℃/180 MPa条件下时效500 h的显微组织 (a)垂直[001]取向的碳化物和共晶相;(b)平行[001]取向的碳化物和共晶相;(c)垂直[001]取向的枝晶干γ´相;(d)平行[001]取向的枝晶干γ´相

    Figure  5.  Microstructure of the alloy after aging at 980 ℃/180 MPa for 500 h  (a) carbides and eutectic perpendicular to [001] direction;(b) carbides and eutectic parallel to [001] direction; (c) γ´ phase at the dendrite perpendicular to [001] direction;(d) γ´ phase at the dendrite parallel to [001] direction

    图  6  模拟服役环境条件下试样的980 ℃/275 MPa剩余持久寿命

    Figure  6.  980 ℃/275 MPa residual stress rupture lives of sample at the simulated service environment

    图  7  模拟服役条件下试样持久性能断口宏观形貌 (a)980 ℃/70 MPa断口正面; (b)980 ℃/70 MPa断口侧面; (c)980 ℃/140 MPa断口正面; (d)980 ℃/140 MPa断口侧面

    Figure  7.  Fractograph macro-morphologies of stress rupture of the samples at the simulated service environment  (a) 980 ℃/70 MPa, fracture frontage; (b) 980 ℃/70 MPa, fracture profile; (c) 980 ℃/140 MPa, fracture frontage; (d) 980 ℃/140 MPa, fracture profile

    图  8  模拟服役载荷试样断口形貌 (a)980 ℃/70 MPa,低倍; (b)980 ℃/70 MPa,高倍;(c)980 ℃/140 MPa,低倍; (d)980 ℃/140 MPa,高倍

    Figure  8.  Fracture morphologies of samples at the simulated service environment  (a) 980 ℃/70 MPa, low magnification; (b) 980 ℃/70 MPa, high magnification; (c) 980 ℃/140 MPa, low magnification; (d) 980 ℃/140 MPa, high magnification

    图  9  试样近断口显微组织 (a)70 MPa服役载荷试样;(b) 140 MPa服役载荷试样

    Figure  9.  Microstructure near the fracture surface of ruptured samples   (a) 70 MPa service load sample; (b) 140 MPa service load sample

    表  1  DZ406合金的化学成分(质量分数/%)

    Table  1.   Nominal chemical compositions of DZ406 alloy (mass fraction/%).

    CrCoWAlTaMoReHfBCNi
    6.5-7.011.4-12.14.7-5.15.8-6.36.1-6.51.3-1.72.6-3.01.3-1.70.01-0.020.08-0.14Bal
    下载: 导出CSV

    表  2  筏状γ´相垂直[001]方向的厚度尺寸测量结果

    Table  2.   Rafted γ´ thickness perpendicular to [001] orientation

    Simulated service
    sample
    γ´ thickness
    1/nm
    γ´thickness
    2/nm
    γ´thickness
    3/nm
    γ´thickness
    4/nm
    γ´thickness
    5/nm
    Mean
    value/nm
    180 MPa 648.1688.0527.6634.2485.8596.7
    140 MPa 594.2649.7702.0647.5634.2645.5
    110 MPa 716.1569.1582.9675.0664.4641.5
    70 MPa612.4553.1418.4522.8584.0538.1
    下载: 导出CSV

    表  3  模拟服役环境条件下试样的980 ℃/275 MPa剩余持久寿命

    Table  3.   980 ℃/275 MPa residual stress rupture lives of sample at the simulated service environment

    Load conditionSample group 1Sample group 2Sample group 3Average value
    180 MPa8.8 h1.2 h5 h
    140 MPa15.3 h17.3 h20.4 h17.7 h
    110 MPa14.8 h23.2 h20.6 h19.5 h
    70 MPa35.3 h24.2 h31.8 h30.4 h
    下载: 导出CSV
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出版历程
  • 收稿日期:  2021-10-21
  • 录用日期:  2022-02-07
  • 修回日期:  2022-03-11
  • 刊出日期:  2022-04-22

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