7050凹槽铝板激光冲击强化残余应力分布与疲劳寿命

doi:10.7527/S1000-6893.2019.23096

材料工程与机械制造

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7050凹槽铝板激光冲击强化残余应力分布与疲劳寿命

苟磊¹, 马玉娥¹, 杜永¹, 刘磊², 郭超², 李钢²

1. 西北工业大学航空学院, 西安 710072;
2. 航空工业第一飞机设计研究院, 西安 710089

收稿日期:2019-04-18 修回日期:2019-05-07 出版日期:2019-12-15 发布日期:2019-06-06
通讯作者: 马玉娥 E-mail:ma.yu.e@nwpu.edu.cn
基金资助:
国家自然科学基金（91860128，11572250）

Residual stress profile and fatigue life of 7050 aluminum plate with groove under laser shot peening

GOU Lei¹, MA Yu'e¹, DU Yong¹, LIU Lei², GUO Chao², LI Gang²

1. School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China;
2. AVIC The First Aircraft Institute, Xi'an 710089, China

Received:2019-04-18 Revised:2019-05-07 Online:2019-12-15 Published:2019-06-06
Supported by:
National Natural Science Foundation of China (91860128, 11572250)

摘要/Abstract

摘要： 激光冲击强化（LSP）是改善结构疲劳性能的重要手段，传统数值模拟方法很难模拟复杂结构的多点冲击强化过程。本文利用一种连续动态冲击方法对7050凹槽铝板进行激光冲击强化数值模拟，得到了冲击后稳定的残余应力场，并与试验测量的残余应力相对比，验证了该方法的精度与较高效率。运用4种基于临界平面法的应变模型，最大正应变模型、最大剪应变模型、BM模型和SWT模型分别对未强化件和强化件进行疲劳寿命预测。完成了激光冲击强化件和未强化件的疲劳试验，得到其疲劳寿命。结果表明：寿命预测值与试验结果吻合较好；对未强化件进行平均应力修正后，前3种模型误差分别为31.2%、22.6%和40.7%，而SWT模型的计算结果过于保守；对强化件进行最大正应力修正后，前3种模型误差分别为1.84%、24.0%和46.4%，而SWT模型的计算结果过于危险。

关键词: 7050-T7451铝板, 凹槽, 激光冲击强化, 残余应力, 临界平面法, 疲劳寿命预测

Abstract: Laser Shock Peening (LSP) is an important means to improve the structural fatigue performance. It is difficult to simulate the multi-point impact process of complex structures by traditional numerical simulation methods. In this paper, a continuous dynamic impact method is used to simulate the LSP of 7050 aluminum plate with groove. The stable residual stress field after impacts is obtained. By comparing with the measured values of residual stress, the higher accuracy and efficiency of this method are verified. Four strain models based on the critical plane method, the normal strain model, the shear strain model, the BM model, and the SWT model are used to predict fatigue life of unreinforced and reinforced samples. The fatigue tests of strengthened and unreinforced samples are carried out and their fatigue lives are obtained. The results showed that predicted lives are in good agreement with experimental results. After mean stress correction for unreinforced sample, the errors of the first three models were 31.2%, 22.6%, and 40.7%, while the result of SWT model is obviously too conservative. After the maximum normal stress correction for strengthened sample, the errors are 1.84%, 24.0%, and 46.4%, while the result of SWT model is obviously too dangerous.

Key words: 7050-T7451 aluminum plate, groove, laser shot peening, residual stress profile, critical plane method, fatigue life prediction

中图分类号:

V216.8

苟磊, 马玉娥, 杜永, 刘磊, 郭超, 李钢. 7050凹槽铝板激光冲击强化残余应力分布与疲劳寿命[J]. 航空学报, 2019, 40(12): 423096-423096.

GOU Lei, MA Yu'e, DU Yong, LIU Lei, GUO Chao, LI Gang. Residual stress profile and fatigue life of 7050 aluminum plate with groove under laser shot peening[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2019, 40(12): 423096-423096.

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7050凹槽铝板激光冲击强化残余应力分布与疲劳寿命

Residual stress profile and fatigue life of 7050 aluminum plate with groove under laser shot peening

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