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燕尾榫连接结构微动疲劳全寿命预测方法

徐可宁 李雯 黄勇 余庆陶 马国佳 胡文颖

徐可宁, 李雯, 黄勇, 等 . 燕尾榫连接结构微动疲劳全寿命预测方法[J]. 北京航空航天大学学报, 2020, 46(10): 1890-1898. doi: 10.13700/j.bh.1001-5965.2019.0471
引用本文: 徐可宁, 李雯, 黄勇, 等 . 燕尾榫连接结构微动疲劳全寿命预测方法[J]. 北京航空航天大学学报, 2020, 46(10): 1890-1898. doi: 10.13700/j.bh.1001-5965.2019.0471
XU Kening, LI Wen, HUANG Yong, et al. A fretting fatigue total life prediction method for dovetail attachment[J]. Journal of Beijing University of Aeronautics and Astronautics, 2020, 46(10): 1890-1898. doi: 10.13700/j.bh.1001-5965.2019.0471(in Chinese)
Citation: XU Kening, LI Wen, HUANG Yong, et al. A fretting fatigue total life prediction method for dovetail attachment[J]. Journal of Beijing University of Aeronautics and Astronautics, 2020, 46(10): 1890-1898. doi: 10.13700/j.bh.1001-5965.2019.0471(in Chinese)

燕尾榫连接结构微动疲劳全寿命预测方法

doi: 10.13700/j.bh.1001-5965.2019.0471
基金项目: 

国家自然科学基金 51705490

国家自然科学基金 5187600

装备预研重点实验室基金 614290802081706

详细信息
    作者简介:

    徐可宁  女, 博士, 高级工程师。主要研究方向:航空发动机结构强度振动可靠性

    李雯 女, 博士, 研究员。主要研究方向:机械传动与摩擦学、微动损伤多尺度建模与仿真技术

    通讯作者:

    李雯, E-mail: mosquato@buaa.edu.cn

  • 中图分类号: V231.91

A fretting fatigue total life prediction method for dovetail attachment

Funds: 

National Natural Science Foundation of China 51705490

National Natural Science Foundation of China 5187600

Pre-research Key Laboratory Fund for Equipment 614290802081706

More Information
  • 摘要:

    微动损伤使航空发动机榫连接结构疲劳寿命显著降低。以钛合金Ti-6Al-4V燕尾榫连接结构为例,提出一种适用于复杂结构微动疲劳全寿命预测方法。基于修正的Manson-McKnight方法和多轴疲劳理论,疲劳损伤参数由等效应力参数(ESP)表征,微动疲劳裂纹萌生位置和成核寿命通过有限元分析(FEA)和ESP预测。基于断裂力学理论和最大周向应力准则,提出微动疲劳裂纹扩展数值模拟方法,建立微动疲劳扩展寿命与裂纹长度函数关系,依据裂纹终值长度预测微动疲劳扩展寿命。结果显示:钛合金Ti-6Al-4V燕尾榫连接结构微动疲劳裂纹扩展角预测值与实验值均为18°,裂纹生长方向预测值与实验值相符;微动疲劳全寿命(成核寿命+扩展寿命)预测值在实验值的2倍分散带内;最大拉伸载荷对榫连接结构的微动疲劳全寿命影响显著,在相同应力比下,最大拉伸载荷从18 kN变化到24 kN,钛合金Ti-6Al-4V燕尾榫连接结构微动疲劳全寿命降低1个数量级。

     

  • 图 1  钛合金Ti-6Al-4V等效应力σeq与裂纹成核寿命Ni关系[14]

    Figure 1.  Equivalent stress σeq versus crack nucleation life Ni for titanium alloy Ti-6Al-4V[14]

    图 2  微动疲劳仿真流程

    Figure 2.  Flowchart of fretting fatigue simulation

    图 3  燕尾榫连接结构微动疲劳实验设施[5]

    Figure 3.  Fretting fatigue test rig for dovetail attachment[5]

    图 4  1/2燕尾榫连接结构的有限元分析模型

    Figure 4.  Finite element analysis model for half of dovetail attachment

    图 5  钛合金Ti-6Al-4V应力-应变曲线

    Figure 5.  Stress-strain curve for titanium alloy Ti-6Al-4V

    图 6  燕尾榫连接结构的von Mises应力分布

    Figure 6.  von Mises stress distribution for dovetail attachment

    图 7  燕尾榫连接结构的切向接触应力分布

    Figure 7.  Tangential contact stress at contact interface for dovetail attachment

    图 8  不同单元尺寸下的切向接触应力

    Figure 8.  Tangential contact stress at different element sizes

    图 9  燕尾榫细化的有限元模型

    Figure 9.  Refined mesh for dovetail attachment

    图 10  二维和三维模型的切向接触应力计算结果

    Figure 10.  Calculation results of tangential contact stress for 2D and 3D models

    图 11  等效应力σeq在接触区的云图

    Figure 11.  Contour of equivalent stress σeq at contact region

    图 12  裂纹成核寿命Ni在接触区的云图

    Figure 12.  Contour of crack nucleation life Ni at contact region

    图 13  榫头裂纹扩展路径实验与数值解

    Figure 13.  Experimental and numerical results of crack propagation path for dovetail

    图 14  裂纹扩展角与裂纹长度的对应关系

    Figure 14.  Crack kink angle versus crack length

    图 15  裂纹扩展速率与裂纹长度的对应关系

    Figure 15.  Crack growth rate versus crack length

    图 16  裂纹扩展寿命与裂纹长度的对应关系

    Figure 16.  Crack propagation life versus crack length

    图 17  全寿命预测值与实验值对比

    Figure 17.  Predicted total life compared to experimental life

    表  1  钛合金Ti-6Al-4V的裂纹扩展常数[13]

    Table  1.   Crack growth constants of titanium alloy Ti-6Al-4V[13]

    参数 数值
    Kth 4.207 54
    Kc 65.931 72
    A 0.025 4
    B -18.144
    P 3.710 7
    Q 0.234 9
    d -0.006 6
    m(R>0) 0.72
    m(R<0) 0.275
    下载: 导出CSV

    表  2  不同载荷下的裂纹成核寿命分析结果

    Table  2.   Analysis results of crack nucleation life at different loads

    最大拉伸载荷/kN 裂纹成核寿命
    16 2 028 490
    18 920 752
    19 512 825
    20 374 895
    22 172 616
    24 91 184
    下载: 导出CSV

    表  3  不同载荷下的裂纹扩展寿命分析结果

    Table  3.   Analysis result of crack propagation life at different loads

    最大拉伸载荷/kN 裂纹扩展寿命
    16 107
    18 1 589 605
    19 781 162
    20 625 667
    22 363 834
    24 231 415
    下载: 导出CSV
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出版历程
  • 收稿日期:  2019-09-02
  • 录用日期:  2020-04-03
  • 网络出版日期:  2020-10-20

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