孔挤压芯棒导端角对TC17钛合金孔结构表面完整性及疲劳性能的影响
Effect of lead angle of hole expansion mandrel on surface integrity and fatigue performance of TC17 titanium alloy hole structure
查看参考文献14篇
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文摘
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针对TC17钛合金,研究芯棒导端角对孔结构挤压强化效果的影响,表征不同导端角工艺参数下的孔挤压强化后的表面完整性,测试原始及强化试样的高温低周疲劳寿命,分析疲劳断口的形貌特征。结果表明:芯棒导端角对挤压后表面粗糙度有显著影响,挤压过程中孔壁表层金属塑性流动不均匀导致挤压后孔壁残余应力分布不均匀,挤压出口端残余应力幅值最大,且挤压后孔壁具有一定深度的残余压应力梯度场。芯棒过盈量一定时,随着芯棒后导端角的增大,疲劳寿命增大,后导端角为8°时,强化后中值疲劳寿命增益可达1.74倍,强化效果最好,其最小循环寿命为16331次,高于原始试样的最长循环寿命(13965次)。强化后,不同导端角的裂纹起源均由孔壁中部多源型转变为挤压进口端单源起裂特征。 |
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其他语种文摘
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For the TC17 titanium alloy, the influence of the leading end angle of the mandrel on the expansion strengthening effect of the hole structure was studied, the surface integrity of the hole expansion strengthened under different process parameters was characterized, the high temperature and low cycle of the original and strengthened samples were tested. Fatigue life and the morphological characteristics of fatigue fracture are analyzed. The results show that the lead angle of the mandrel has a significant effect on the surface roughness after expansion. The uneven plastic flow of the metal on the surface of the hole wall during the expansion process leads to uneven residual stress distribution on the hole wall after expansion, and the residual stress amplitude at the exit end of the expansion is the largest, and the hole wall has a certain depth of residual compressive stress gradient field after expansion. When the interference of the core rod is constant, the fatigue life increases with the increase of the rear lead end angle of the mandrel. When the rear lead end angle is 8°, the median fatigue life gain after strengthening can reach 1.74 times, and the strengthening effect is the best, its minimum cycle life is 16331 times, which is higher than the longest cycle life of the original sample (13965 cycles). After strengthening, the origin of the cracks is changed from the multi-source type in the middle of the hole wall to the single-source crack initiation at the inlet end of the expansion. |
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来源
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航空材料学报
,2021,41(4):75-82 【核心库】
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DOI
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10.11868/j.issn.1005-5053.2021.000060
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关键词
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孔挤压
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导端角
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TC17钛合金
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疲劳寿命
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残余应力
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地址
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中国航发北京航空材料研究院表面工程研究所, 北京, 100095
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中国航发北京航空材料研究院, 航空材料先进腐蚀与防护航空重点实验室, 北京, 100095
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语种
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中文 |
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文献类型
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研究性论文 |
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ISSN
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1005-5053 |
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学科
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金属学与金属工艺 |
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文献收藏号
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CSCD:7041419
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