孔的开缝衬套冷挤压强化工艺研究  

Study on Cold Extrusion Strengthening Technology of Split Sleeve of Hole

作　　者：卢浩 魏永合[1] 江晓宇 廖波 LU Hao;WEI Yonghe;JIANG Xiaoyu;LIAO Bo(Shenyang Ligong University,Shenyang 110168,China;AVIC Yibin Sanjiang Machinery Corporation Ltd.,Yibin 644007,China)

机构地区：[1]沈阳理工大学,沈阳110168 [2]航空工业宜宾三江机械有限责任公司,宜宾644007

出　　处：《航空制造技术》2024年第21期98-105,共8页Aeronautical Manufacturing Technology

基　　金：国家自然科学基金(51875368)。

摘　　要：开缝衬套冷挤压强化孔工艺广泛应用于航空制造、维修等领域,用来提高飞机结构孔的疲劳寿命。采用仿真分析方法研究了开缝衬套冷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7050铝合金构件挤压强化有限元模型,得到了不同挤压量下的仿真结果,并分析了该模型的准确性;其次,在得到的强化模型结果基础上利用疲劳分析软件Fe-Safe对强化孔疲劳全寿命进行了预测;最后,开展了未挤压孔与开缝衬套挤压强化孔的疲劳试验对比。结果表明,设计挤压量在4.0%~4.5%时,可以获得最合理的残余应力分布,当挤压量超过4.5%时挤出端残余压应力最大值基本保持不变。挤压完成后,孔径向变形呈马鞍形状,孔壁金属向孔两端方向流出。该强化工艺对孔的疲劳增益效果明显,强化孔的疲劳寿命约为未强化孔的10倍。The technology of cold extrusion strengthening holes with split sleeve is widely used in aviation manufacturing,maintenance and other fields to improve the fatigue life of aircraft structural holes.The residual stress distribution and fatigue life of cold extrusion strengthened hole of split sleeve were studied by simulation analysis method.Firstly,based on the finite element software ABAQUS,a finite element model of extrusion strengthening of 7050 aluminum alloy components was established,and the simulation results under different extrusion amounts were obtained,and the accuracy of the model was analyzed.Secondly,based on the results of the strengthened model,the fatigue life of the strengthened hole was predicted by using the fatigue analysis software Fe-Safe.Finally,a fatigue test comparison between the unextruded hole and the extrusion-strengthened hole with split sleeve was carried out.The results show that the most reasonable residual stress distribution can be obtained when the designed extrusion amount is 4.0%–4.5%.When the extrusion amount exceeds 4.5%,the maximum residual compressive stress at the extrusion end basically remains unchanged.After extrusion,the hole diameter changes in a saddle shape along the axial direction,and the hole wall metal flows out toward both ends of the hole.This strengthening process has obvious effect on the fatigue gain of holes,and the fatigue life of strengthened holes is about 10 times that of unreinforced holes.

关 键 词：开缝衬套 冷挤压强化 残余应力 有限元仿真 疲劳寿命 

分 类 号：V261[航空宇航科学与技术—航空宇航制造工程] TG376.3[金属学及工艺—金属压力加工]