孔强化对7050铝合金残余应力分布的影响  

Effect of Strengthened Hole on Residual Stress of 7050 Aluminium Alloy

作　　者：黄宏[1] 赵庆云[1] 刘风雷[1] 

机构地区：[1]中航工业北京航空制造工程研究所,北京100024

出　　处：《航空制造技术》2016年第19期80-82,共3页Aeronautical Manufacturing Technology

摘　　要：采用开缝衬套冷挤压工艺对飞机用7050铝合金进行挤压强化,针对不同挤压量及铰削量对孔边残余应力分布的影响进行对比,分析得到挤压量及铰削量与残余应力分布的关系。研究表明:采用冷挤压孔强化技术可以改善孔边应力分布,形成有利的残余压应力层。强化后铰孔会减弱残余压应力,对于φ6mm孔铰削量应控制在0.16mm范围内。残余压应力随强化量的增加而增大,5%的挤压量残余压应力值最大达到-276MPa。Split-sleeve cold expansion processing is employed on the 7050 aluminum alloy plate that used on airplane. The effects of residual stress are compared according to different expansion and reaming values, then the relationship of expansion and reaming is analyzed. The results show that the split-sleeve cold expansion can improve the distribution of the hole＇s residual stress, and form beneficial rasidual compressive stress. The rasidual compressive stress is decreased when reaming after expansion. The reaming value is within 0.16 mm for the φ6mm hole. The rasidual compressive stress is increases with the expansion increment. The rasidual compressive stress value reaches the maximum-276 MPa with 5%expansion.

关 键 词：孔强化 7050铝合金 残余应力 

分 类 号：V261[航空宇航科学与技术—航空宇航制造工程] V252.2[一般工业技术—材料科学与工程]