激光冲击强化对7050-T7451铝合金凹槽结构疲劳寿命的影响

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英文篇名：Effect of Laser Shock Peening on Fatigue Life of 7050-T7451 Aluminum Alloy Groove Structure 作者：李钢 ; 姚雄华 ; 郭超 ; 陈海波 ; 刘磊 ; 李博 英文作者：LI Gang;YAO Xionghua;GUO Chao;CHEN Haibo;LIU Lei;LI Bo;Institute of Structural Design of AVIC The First Aircraft Institute;Engineering Technology Center of AVIC XAC Commercial Aircraft Co.,Ltd.; 关键词：激光冲击强化 ; 疲劳寿命 ; 凹槽结构 ; 7050-T7451铝合金 英文关键词：laser shock peening(LSP);;fatigue life;;groove structure;;7050-T7451 aluminum alloy 中文刊名：SJGY 英文刊名：Hot Working Technology 机构：航空工业第一飞机设计研究院结构设计研究所;中航西飞民用飞机有限责任公司工程技术中心; 出版日期：2019-06-13 17:15 出版单位：热加工工艺 年：2019 期：v.48;No.514 基金：民用飞机专项科研项目(MJ-2016-F-16) 语种：中文; 页：SJGY201912023 页数：5 CN：12 ISSN：61-1133/TG 分类号：96-100

摘要

研究了激光冲击强化对7050-T7451铝合金凹槽结构疲劳寿命的影响。采用45°激光入射角对应力集中R区进行冲击强化,其余区域采用90°激光入射角冲击。随后对强化后和未强化的实验件分别进行拉-拉疲劳实验。结果表明,在置信度99%情况下,经强化的实验件比未经强化的疲劳寿命提高1.566～2.725倍;激光冲击强化处理后,断裂部位远离凹槽R区。激光冲击强化对凹槽强化效果明显。
        The effects of laser shock peeing(LSP) on the fatigue life of groove structure of 7050-T7451 aluminum alloy were investigated. 45° laser incident angle was used to shock stress concentration R region and then, 90° lase incident angle was used to shock the other zones. The fatigue life of the specimens with and without LSP was evaluated by using tensile-tensile test. The results show that the fatigue life of the specimen with LSP is 1.566-2.725 times higher than that of specimen without LSP under a confidence of 99%. After LSP treatment, the fatigue crack initiation is far away from the groove R region. The laser shock peening has obvious effects on the groove peening.

引文

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