Effects of Drilling and Reaming on the Fatigue Life of Aluminum Alloy Specimen with a Fastener Hole
摘 要
为研究钻、铰工艺对紧固孔件疲劳寿命的影响, 分别对LY12CZ硬铝合金疲劳试样采用钻、铰两种工艺加工出孔并进行了疲劳试验, 对钻、铰工艺下孔壁的表面形貌和粗糙度、切向残余应力以及试样的疲劳断口特征进行了测定和分析。结果表明: 钻削后孔壁的表面较粗糙, 其表面粗糙度为12.92 μm, 而铰削后孔壁表面非常光滑, 其表面粗糙度为1.57 μm; 钻削孔壁表层的应力为残余拉应力, 幅值为165 MPa, 而铰削孔壁表层的应力为残余压应力, 幅值为78 MPa; 相比于钻孔试样, 铰孔试样的疲劳条带间距较窄, 裂纹扩展速率较低, 其疲劳寿命是钻孔试样寿命的1.81倍。
Abstract
In order to investigate the effects of drilling and reaming on the fatigue life of LY12CZ aluminum alloy specimen, a fastener hole was machined by drilling and reaming process, respectively, and fatigue tests were carried out. And the surface morphology, roughness and tangential residual stress of the hole wall were measured and analyzed as well as the fatigue fracture characteristics. The results show that the surface of hole wall after drilling was rough and its average surface roughness was 12.92 μm, while the surface of hole wall after reaming was much smooth and its average surface roughness was 1.57 μm. Moreover, the stress in the surface of hole wall after drilling was tensile residual stress and its magnitude reached to 310 MPa, while it was compressive residual stress after reaming and its magnitude reached to 78 MPa. Compared with the drilled specimen, the reamed specimen had narrower fatigue slip striation, and lower fatigue crack growth rate. The average fatigue life of the reamed specimen was 1.81 times as long as the drilling specimen.
中图分类号 TH114
所属栏目 试验研究
基金项目 国家自然科学基金资助项目(511750021); 安徽省自然科学基金资助项目(090414156)
收稿日期 2014/6/8
修改稿日期 2014/6/26
网络出版日期
作者单位点击查看
备注章艳(1990-), 男, 安徽马鞍山人, 硕士研究生。
引用该论文: ZHANG Yan,ZHANG Xing-quan,DUAN Shi-wei,ZHOU Yu,HUANG Zhi-lai. Effects of Drilling and Reaming on the Fatigue Life of Aluminum Alloy Specimen with a Fastener Hole[J]. Materials for mechancial engineering, 2014, 38(8): 16~19
章艳,张兴权,段仕伟,周煜,黄志来. 钻、铰工艺对铝合金紧固孔件疲劳寿命的影响[J]. 机械工程材料, 2014, 38(8): 16~19
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【10】LIU J, YUE Z F, LIU Y S. Surface finish of open holes on fatigue life[J].Theoretical and Applied Fracture Mechanics,2007,27(1): 35-45.
【11】高玉魁.孔挤压强化对23Co14Ni12Cr3MoE钢疲劳性能的影响 [J].金属热处理, 2007, 32(11): 34-36.
【12】王生武, 温爱玲, 邴世君, 等.滚压强化的残余应力的数值仿真及工艺分析 [J].计算力学学报, 2008, 25(S1): 113-118.
【13】王学德, 李启鹏, 王路成, 等.激光冲击强化对LY2铝合金残余应力显微组织及疲劳性能的影响[J].机械工程材料,2012,36(11): 82-84.
【14】何世平, 张 曦, 伍小平.铰孔和疲劳对冷挤压孔周残余应力的影响[J].试验力学, 1996, 11(4): 463-467.
【15】王珉.抗疲劳制造原理与技术[M].南京: 江苏科学技术出版社, 1998.
【16】ZHANG Xing-quan, CHEN Liu-san, YU Xiao-liu, et al. Effect of laser shock processing on fatigue life of fastener hole[J].Transactions of Nonferrous Metals Society of China,2014,24(4): 969-974.
【17】刘新灵, 张峥, 陶春虎.疲劳断口定量分析[M].北京: 国防工业出版社, 2010.
【18】张东初, 裴旭明, 陈五一, 等.紧固孔的加工工艺对其表面残余应力的影响[J].航空制造技术, 2003(5): 40-42.
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