Research on fatigue crack propagation behavior and fatigue life of AA2524 sheet after laser heating − Laser shot peening

IF 4.4 2区工程技术 Q1 ENGINEERING, MECHANICAL

Engineering Failure Analysis Pub Date : 2025-05-26 DOI:10.1016/j.engfailanal.2025.109760

Songbai Li, Peijun Li, Qiyun Zhu, Mei Yin, Xinhua Zhu, Hui Long

{"title":"Research on fatigue crack propagation behavior and fatigue life of AA2524 sheet after laser heating − Laser shot peening","authors":"Songbai Li, Peijun Li, Qiyun Zhu, Mei Yin, Xinhua Zhu, Hui Long","doi":"10.1016/j.engfailanal.2025.109760","DOIUrl":null,"url":null,"abstract":"<div><div>In order to prolong the service life of AA2524 panel, a composite process of laser heating(LH) and laser shot peening(LSP) was proposed to modify the surface of AA2524 panel. The compressive residual stress(CRS) on the panel surface was induced to delay the fatigue crack growth rate(FCGR) and prolong the service life. A single LH-LSP was performed on the AA2524 specimen. The surface residual stress and surface hardness of specimen were measured, the FCGR of specimen was evaluated under different stress ratios, and the microstructure of the fatigue fracture of specimen was observed. The fatigue life of the specimen was predicted by weight function combined with fatigue crack growth rate formula. The results show that compared with specimen after single LH and single LSP, specimen after single LH-LSP can induce greater surface CRS, and has the best life prolonging effect. When <em>R</em> = 0.1, the FCGR of the specimen after composite process is about 31.2 % lower than that of the base material specimen. The root-mean-square error(RMSE) (3.83 %) of fatigue life prediction by Wu + Walker model is smaller than that by Wu + Forman model (5.72 %) and Wu + Elber model (7.68 %). The composite process can better prolong the life of aviation AA2524 panel.</div></div>","PeriodicalId":11677,"journal":{"name":"Engineering Failure Analysis","volume":"179 ","pages":"Article 109760"},"PeriodicalIF":4.4000,"publicationDate":"2025-05-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":"0","resultStr":null,"platform":"Semanticscholar","paperid":null,"PeriodicalName":"Engineering Failure Analysis","FirstCategoryId":"5","ListUrlMain":"https://www.sciencedirect.com/science/article/pii/S1350630725005011","RegionNum":2,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":null,"EPubDate":"","PubModel":"","JCR":"Q1","JCRName":"ENGINEERING, MECHANICAL","Score":null,"Total":0}

引用次数: 0

Abstract

In order to prolong the service life of AA2524 panel, a composite process of laser heating(LH) and laser shot peening(LSP) was proposed to modify the surface of AA2524 panel. The compressive residual stress(CRS) on the panel surface was induced to delay the fatigue crack growth rate(FCGR) and prolong the service life. A single LH-LSP was performed on the AA2524 specimen. The surface residual stress and surface hardness of specimen were measured, the FCGR of specimen was evaluated under different stress ratios, and the microstructure of the fatigue fracture of specimen was observed. The fatigue life of the specimen was predicted by weight function combined with fatigue crack growth rate formula. The results show that compared with specimen after single LH and single LSP, specimen after single LH-LSP can induce greater surface CRS, and has the best life prolonging effect. When R = 0.1, the FCGR of the specimen after composite process is about 31.2 % lower than that of the base material specimen. The root-mean-square error(RMSE) (3.83 %) of fatigue life prediction by Wu + Walker model is smaller than that by Wu + Forman model (5.72 %) and Wu + Elber model (7.68 %). The composite process can better prolong the life of aviation AA2524 panel.

查看原文本刊更多论文

AA2524板材激光加热-激光喷丸后疲劳裂纹扩展行为及疲劳寿命研究

为了延长AA2524面板的使用寿命，提出了激光加热（LH）和激光喷丸（LSP）复合工艺对AA2524面板表面进行改性处理。通过诱导板面残余压应力（CRS）延缓板面疲劳裂纹扩展速率（FCGR），延长板面使用寿命。对AA2524试样进行单次LH-LSP处理。测量了试样的表面残余应力和表面硬度，评价了不同应力比下试样的FCGR，观察了试样疲劳断口的显微组织。采用权函数结合疲劳裂纹扩展速率公式预测试样的疲劳寿命。结果表明：与单次LH和单次LSP处理试样相比，单次LH-LSP处理试样能诱导更大的表面CRS，具有最佳的延长寿命效果；当R = 0.1时，复合后试样的FCGR比基材试样低约31.2%。Wu + Walker模型预测疲劳寿命的均方根误差（RMSE）为3.83%，小于Wu + Forman模型（5.72%）和Wu + Elber模型（7.68%）。复合工艺能较好地延长航空AA2524板的使用寿命。

本文章由计算机程序翻译，如有差异，请以英文原文为准。

求助全文

约1分钟内获得全文求助全文

来源期刊

Engineering Failure Analysis 工程技术-材料科学：表征与测试

CiteScore

7.70

自引率

20.00%

发文量

956

审稿时长

47 days

期刊介绍： Engineering Failure Analysis publishes research papers describing the analysis of engineering failures and related studies. Papers relating to the structure, properties and behaviour of engineering materials are encouraged, particularly those which also involve the detailed application of materials parameters to problems in engineering structures, components and design. In addition to the area of materials engineering, the interacting fields of mechanical, manufacturing, aeronautical, civil, chemical, corrosion and design engineering are considered relevant. Activity should be directed at analysing engineering failures and carrying out research to help reduce the incidences of failures and to extend the operating horizons of engineering materials. Emphasis is placed on the mechanical properties of materials and their behaviour when influenced by structure, process and environment. Metallic, polymeric, ceramic and natural materials are all included and the application of these materials to real engineering situations should be emphasised. The use of a case-study based approach is also encouraged. Engineering Failure Analysis provides essential reference material and critical feedback into the design process thereby contributing to the prevention of engineering failures in the future. All submissions will be subject to peer review from leading experts in the field.