航空材料学报2017，Vol.37Issue(6)：82-87,6.DOI:10.11868/j.issn.1005-5053.2017.000102
挤压强化对TC17钛合金孔结构疲劳寿命的影响
Effect of Cold Expansion on Fatigue Life of Hole Structure of TC17 Titanium Alloy
艾莹珺 1王欣 2宋颖刚 1王强 2罗学昆 1汤智慧 2赵振业1
作者信息
- 1. 中国航发北京航空材料研究院,北京100095
- 2. 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科技重点实验室,北京100095
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摘要
Abstract
In order to improve the fatigue performance of TC17 central hole specimen,the hole wall surface integrity was characterized by scanning electron microscopy (SEM),roughness meter,X-ray diffraction,and the influence of hole cold expansion(HCE) parameter on the fatigue performance of the hole specimens was investigated.The results show that the minimum fatigue life (14718 cycle) of the HCE specimens with an expansion value of 0.18 mm is higher than the original specimen (13965 cycle).Compared to the specimens with the expansion values of 0.28 mm and 0.38 mm,the fatigue life dispersion is less,no obvious stress concentration phenomenon is found,and it has the best fatigue performance than the other two.The surface roughness value of hole wall is the lowest after the HCE with 0.18 mm,the inner hole wall forms a certain depth of strengthened layer,the residual compressive stress produced in the hole side effectively suppresses the produce of fatigue cracks in the inner hole wall,so the fatigue performance of hole structure is improved.关键词
孔挤压/TC17钛合金/疲劳寿命/残余应力Key words
hole cold expansion/TC17 titanium alloy/fatigue life/residual stress分类
矿业与冶金引用本文复制引用
艾莹珺,王欣,宋颖刚,王强,罗学昆,汤智慧,赵振业..挤压强化对TC17钛合金孔结构疲劳寿命的影响[J].航空材料学报,2017,37(6):82-87,6.
