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振动时效处理对7055-T7751铝合金疲劳性能的影响
引用本文:马永波,崔腾飞,潘一帆,成书民,刘道新. 振动时效处理对7055-T7751铝合金疲劳性能的影响[J]. 机械工程材料, 2019, 43(8): 35-40
作者姓名:马永波  崔腾飞  潘一帆  成书民  刘道新
作者单位:航空工业西安飞机工业(集团)有限责任公司,西安,710089;西北工业大学航空学院,西安 710072;中国直升机设计研究所,景德镇 333001;西北工业大学航空学院,西安,710072
基金项目:国家自然科学基金;装备预研项目
摘    要:对7055-T7751铝合金预拉伸板(预应变为1%~3%)进行振动时效处理,并在不同最大应力(300,350,400,500MPa)下进行疲劳试验,研究了振动时效处理对合金显微组织、显微硬度、表面残余应力和疲劳性能的影响。结果表明:振动时效处理对显微组织和显微硬度的影响很小,振动时效后的组织仍为轧制板材织构取向组织;振动时效处理后,合金中纵向和横向残余拉应力发生明显松弛,且纵向残余应力分布有所均化;振动时效处理明显提高了纵向和横向试样的疲劳性能,在最大应力350MPa条件下,纵向和横向试样的疲劳寿命分别提高了219.0%和29.1%,疲劳极限分别提高了9.9%和5.1%。

关 键 词:7055-T7751铝合金  振动时效  疲劳性能  残余应力  整体机翼壁板

Effect of Vibratory Stress Relief Treatment on Fatigue Property of 7055-T7751 Aluminum Alloy
MA Yongbo,CUI Tengfei,PAN Yifan,CHENG Shumin,LIU Daoxin. Effect of Vibratory Stress Relief Treatment on Fatigue Property of 7055-T7751 Aluminum Alloy[J]. Materials For Mechanical Engineering, 2019, 43(8): 35-40
Authors:MA Yongbo  CUI Tengfei  PAN Yifan  CHENG Shumin  LIU Daoxin
Affiliation:(Aviation Industry Xi′an Aircraft Industry(Group)Co.,Ltd.,Xi′an 710089,China;School of Aeronautics,Northwestern Polytechnical University,Xi′an 710072,China;China Helicopter Design Institute,Jingdezhen 333001,China)
Abstract:7055-T7751 aluminum alloy pre-stretching plate(pre-strains of 1%-3%)was subjected to vibratory stress relief treatment,and then to fatigue tests under different maximum stresses(300,350,400,500 MPa).The effects of vibratory stress relief treatment on microstructure,microhardness,surface residual stress and fatigue property of the alloy were studied.The results show that the vibratory stress relief treatment had little effect on the microstructure and microhardness;the microstructure after vibratory stress relief was still the texture orientation structure of the rolled plate.After the vibratory stress relief treatment,the longitudinal and transverse residual tensile stresses in the alloy were obviously relaxed,and the longitudinal residual stress distribution was homogenized.The vibratory stress relief treatment improved the fatigue performance of the longitudinal and transverse specimens significantly.Under the maximum stress of 350 MPa,the fatigue lives of the longitudinal and transverse specimens increased by 219.0% and 29.1%,and the fatigue limits were improved by 9.9% and 5.1%,respectively.
Keywords:7055-T7751 aluminum alloy  vibratory stress relief  fatigue property  residual stress  integral wing panel
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