TB6钛合金孔二次挤压残余应力及疲劳寿命仿真研究  

Simulation Study on Residual Stress and Fatigue Life of TB6 Titanium Alloy Hole After Double Cold Expansion

作　　者：姜廷宇 王洋[1] 王鹏 万志城 张全利 苏宏华[1] JIANG Tingyu;WANG Yang;WANG Peng;WAN Zhicheng;ZHANG Quanli;SU Honghua(College of Mechanical and Electrical Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;AVIC Changhe Aircraft Industry(Group)Corporation Ltd.,Jingdezhen 333000,China)

机构地区：[1]南京航空航天大学机电学院,南京210016 [2]航空工业昌河飞机工业(集团)有限责任公司,景德镇333000

出　　处：《航空制造技术》2021年第9期77-84,共8页Aeronautical Manufacturing Technology

摘　　要：二次挤压强化技术可以在保证底孔有足够的强化效果下,实现衬套与孔壁的紧密配合,从而有效提高连接件的疲劳寿命。采用仿真分析方法研究了二次挤压强化孔残余应力分布及疲劳寿命。首先,基于有限元软件ABAQUS建立了TB6钛合金构件二次挤压强化有限元模型,并分析了该仿真模型的准确性;其次,在有限元模拟结果的基础上利用疲劳分析软件MSC.Fatigue对二次挤压强化孔进行疲劳寿命分析;最后,分析了不同孔径偏差及挤压润滑情况对孔疲劳性能的影响。结果表明,二次挤压强化可以有效缓解孔壁应力集中现象,疲劳破坏位置由孔壁向远离孔壁位置转移;不同孔径最小截面方向存在一个应力不变点,相同挤压条件下,孔径偏差过大对孔的疲劳寿命有不利影响,孔壁润滑状况越好,强化后的孔疲劳性能越好。The double cold expansion strengthening technology can ensure that the hole has enough strengthened effect,and realize the close fit between bushing and the hole edge,so as to improve the fatigue life of connectors effectively.Residual stress distribution and fatigue life of double cold expanded hole were studied by simulation method.Firstly,a finite element model for the double cold expansion of TB6 titanium alloy components was established to analyze the accuracy of the simulation model.Secondly,based on the simulation results,the fatigue life of the double cold expanded hole was analyzed by MSC.Fatigue software.Finally,the effect of the hole diameter deviation and the expansion lubrication condition on the fatigue performance was taken into consideration.The results show that the stress concentration on the hole wall can be effectively alleviated by the double cold expansion process.The fatigue failure position transferred from the hole edge to the position far away.Furthermore,a constant stress level in the direction of the smallest cross-section with different apertures occurs.It is also found that the excessive diameter deviation has a negative effect on the fatigue life,where good lubrication condition is beneficial to the fatigue performance.

关 键 词：二次挤压强化 残余应力 疲劳寿命 有限元法 MSC.Fatigue仿真 

分 类 号：V261[航空宇航科学与技术—航空宇航制造工程]