摘要
针对复合热源焊接在钛合金航空结构件的应用,开展了2.5 mm厚TA15钛合金薄板激光-TIG电弧复合热源对接结构焊接试验。并对TIG焊接头、复合热源焊接接头和母材进行了疲劳测试分析,分别计算各自在不同应力水平下的中值疲劳寿命,采用扫描电镜(SEM)对复合热源焊接接头疲劳试样断口进行观察以了解断裂路径。结果表明:复合热源焊接接头疲劳断裂发生在热影响区,复合热源焊接接头疲劳寿命大于TIG焊接头,在560、672、784、896 MPa应力水平下时复合热源接头疲劳寿命分别为母材的91.5%、90.6%、82.7%、84%。。断口由疲劳源区、裂纹稳定扩展区和瞬断区组成,起裂源位于试件表面。
Aiming at the application of hybrid heat source welding in titanium alloy aviation structural parts,the butt welding experiment of 2.5 mm thick TA15 titanium alloy thin plate with laser-TIG arc hybrid heat source was carried out.The fatigue test analysis of the TIG welded joint,hybrid heat source welded joint and base metal was carried out,and the median fatigue life under different stress levels was calculated respectively.The fatigue specimen fracture of the hybrid heat source welded joint was observed by scanning electron microscope(SEM)to study the facture path.The results show that the fatigue fracture of the hybrid heat source welded joint occurs in the heat affected zone,and the fatigue life of the hybrid heat source welded joint is bigger than that of the TIG welded joint.Under 560,672,784 and 896 MPa stress levels,the fatigue life of the hybrid heat source welded joints reaches 91.5%,90.6%,82.7%and 84%of base metal,respectively.The fracture consists of fatigue source zone,crack stable extension zone and instantaneous zone,and the crack initiation source is located on the surface of the sample.
作者
刘晓寒
倪家强
刘艳梅
LIU Xiaohan;NI Jiaqiang;LIU Yanmei(Technology Research Institute,Shenyang Aircraft Corporation,Shenyang 110034,China)
出处
《热加工工艺》
北大核心
2019年第3期15-18,23,共5页
Hot Working Technology
基金
国家科技重大专项项目(2013ZX04001041)
