2024铝合金搅拌摩擦焊接头的疲劳性能

对2024铝合金搅拌摩擦焊接头的疲劳特性进行了研究,建立了接头的S-N曲线.疲劳试验结果表明,搅拌摩擦焊接头表现出良好的疲劳性能.搅拌摩擦焊接头具有细小的等轴晶组织和狭窄的热影响区,阻碍了滑移带的形成和裂纹的扩展,从而提高了接头的疲劳性能.疲劳断口分析显示,裂纹在接头底部启裂,通过位错的塞积作用使得滑移带扩展逐渐萌生裂纹,在交变应力的作用下最终断裂.     

搅拌摩擦焊接接头的静载力学行为和疲劳特性

对LF2铝合金搅拌摩擦焊接接头的静载力学行为和疲劳特性进行了研究，建立了焊接接头的孓Ⅳ曲线。力学实验结果表明：LF2铝合金搅拌摩擦焊接接头的最高抗拉强度为252．8MPa，是母材抗拉强度的95．4％。疲劳实验结果表明：搅拌摩擦焊接接头表现出良好的疲劳性能，疲劳寿命N=10^5次的疲劳强度为59～65MPa。显微组织分析表明：搅拌摩擦焊接接头具有细小的等轴晶粒和狭窄的热影响区，阻碍了滑移带的形成和裂纹的扩展，从而提高了接头的疲劳性能。疲劳断口分析显示：随着驻留滑移带的扩展逐渐萌生裂纹，在交变应力作用下最终导致失效。     

铝合金搅拌摩擦焊接头疲劳断裂行为分析

提高和改善铝合金搅拌摩擦焊接头抗疲劳断裂性能是保证其焊接结构安全可靠的重要措施。阐述了国内外对铝合金搅拌摩擦焊接头的疲劳断裂行为的研究进展,包括铝合金搅拌摩擦焊接头的应力疲劳分析和应变疲劳分析;微结构、残余应力、表面处理对疲劳裂纹扩展速率的影响;焊接缺陷对疲劳断裂行为的影响;总结了在腐蚀介质中的疲劳裂纹形成特点和扩展规律及门槛值ΔKth。为建立铝合金搅拌摩擦焊接接头的疲劳设计规范、提高铝合金焊接结构的疲劳强度具有重要的理论意义和实践参考价值。     

搅拌摩擦焊AA7075-T651铝合金接头的疲劳裂纹扩展(英文)

研究12 mm厚AA7075-T651铝合金板搅拌摩擦焊接头的疲劳裂纹扩展行为。从搅拌摩擦焊接头以及母材中截取试样,对试样进行疲劳裂纹扩展实验。对搅拌摩擦焊接头以及母材的横向拉伸性能进行评估。用光学显微镜和透射电镜分析焊接接头的显微组织。用扫描电镜观察试样的断裂表面。与母材相比,焊接接头的ΔKcr降低了10×10-3 MPa·m1/2。搅拌摩擦焊AA7075-T651接头的疲劳寿命明显低于母材的,其原因可归结于焊缝区的析出相在搅拌摩擦焊接过程中的溶解。     

7075铝合金FSW接头腐蚀疲劳性能及断裂特征

以7075-T6铝合金搅拌摩擦焊接头为研究对象，对其显微组织结构、3.5% NaCl(质量分数)溶液腐蚀疲劳寿命和腐蚀疲劳断裂特征进行了研究，分析了7075铝合金搅拌摩擦焊接头的腐蚀疲劳性能及断裂过程.结果表明，7075-T6铝合金搅拌摩擦焊接头腐蚀疲劳S-N曲线方程为lgN=5.845-0.014S，随着应力幅增大，腐蚀疲劳寿命大幅度降低；腐蚀疲劳裂纹起源于接头的热影响区，逐渐扩展最终断裂于接头的焊核区.腐蚀疲劳断口存在多个裂纹源，且受到应力集中作用的影响，裂纹源萌生于腐蚀坑处.高应力作用加剧了试样边角部分的腐蚀损伤，导致边角比平面位置腐蚀程度更严重.裂纹扩展区出现了明显的晶间断裂和疲劳辉纹；在腐蚀介质和交变载荷的共同作用下，裂纹扩展区腐蚀程度最重，晶界处产生了阳极溶解现象并产生了“冰糖块状”和“蚁巢状”的形貌特征；瞬断区产生了大量解理台阶和二次裂纹，为脆性断裂，在第二相粒子分布区域存在孔洞形貌特征.     

航空铝合金搅拌摩擦焊疲劳裂纹扩展速率试验研究

通过高频疲劳实验,对航空铝合金LC4CS和7075-T6搅拌摩擦焊预制裂纹穿焊缝中心、预制裂纹穿焊缝前进边、预制裂纹穿焊缝后退边、预制裂纹垂直于焊缝四种形式的焊接接头疲劳性能进行了研究,LC4CS铝合金FSW接头抗疲劳裂纹扩展能力不如7075-T6铝合金搅拌摩擦焊接接头,但是相差不大.IIW疲劳试验设计标准对于FSW接头是比较保守的.该实验为建立合理的搅拌摩擦焊接接头的疲劳评定规范提供重要依据,从而推动了搅拌摩擦焊接技术在航天领域的广泛应用.     

GH536高温合金焊接接头疲劳裂纹萌生与扩展原位试验研究

采用原位疲劳试验方法,实时观察了GH536焊接接头疲劳裂纹的萌生和扩展行为,从而揭示了GH536焊接接头疲劳裂纹的萌生和扩展机制:疲劳加载过程中,位错沿滑移带在晶界前沿塞积,晶界阻碍位错运动,裂纹沿滑移带开裂,萌生疲劳裂纹;疲劳裂纹扩展初期,受单滑移的交替作用,裂纹呈“Z”字型向前扩展,随后裂纹的扩展逐渐以主应力控制为主,垂直于加载方向、平直向前扩展;GH536合金焊接接头组织中的晶界和碳化物会阻碍疲劳裂纹的扩展。     

7050铝合金FSW接头微区低周疲劳裂纹扩展行为

对5 mm厚铝合金7050搅拌摩擦焊接头微区进行了低周疲劳裂纹扩展试验，研究了焊核区、前进侧及后退侧热力影响区的疲劳裂纹扩展行为. 结果表明，焊核区的疲劳裂纹扩展速率最快，前进侧热力影响区次之，后退侧热力影响区最慢. 焊核区疲劳裂纹呈沿晶与穿晶混合方式扩展，热力影响区的裂纹主要以穿晶方式进行扩展. 裂纹偏转或裂纹产生分支是热力影响区疲劳裂纹扩展速率降低的原因. 疲劳裂纹扩展初期，焊核区断口有疲劳辉纹出现；热力影响区断口并没有找到疲劳辉纹，而是出现了轮胎压痕花样. 疲劳裂纹稳态扩展期，焊核区和热力影响区断口均有疲劳辉纹.     

2219铝合金搅拌摩擦焊焊接接头的疲劳性能

通过疲劳寿命试验、断口和金相组织观察,研究了2219铝合金搅拌摩擦焊接头的疲劳断裂特征,分析讨论了搅拌摩擦焊焊接过程中产生的焊缝根部"吻接"缺陷对其疲劳性能的影响.结果表明,焊缝根部"吻接"缺陷是影响搅拌摩擦焊接头疲劳行为的主要因素.无"吻接"缺陷试样断裂于焊缝前进边侧,疲劳裂纹起源于焊缝底部,接头具有较高疲劳寿命;有"吻接"缺陷试样断裂于焊核中心,疲劳裂纹起源于"吻接"处,接头疲劳寿命较短.     

A6N01-T5合金FSW和MIG焊接头疲劳裂纹扩展行为的对比

研究了6N01-T5铝合金搅拌摩擦焊(FSW)和氩弧焊(MIG)接头不同部位的疲劳裂纹扩展性能, 并对疲劳断口和接头组织进行了分析. 结果表明,对于FSW和MIG焊接头, 其裂纹扩展速率从高到低的部位依次为焊缝(核)区、热影响区和母材. 裂纹在FSW和MIG焊接头相同区域的扩展速率无明显差别, 然而裂纹在FSW接头细晶组织中开始扩展所需的门槛值ΔK要比对应的MIG焊接头高, 总体上其裂纹在FSW焊核区的抗疲劳裂纹扩展性能要优于对应的MIG焊缝区. 裂纹在FSW和MIG焊接头焊核(缝)区扩展的疲劳断口表现为脆性断裂, 而在热影响区则以规则和光滑的疲劳条纹形式扩展.     

60mm厚TC4钛合金电子束焊接头疲劳性能

针对大厚度钛合金在海洋领域的应用,开展了60 mm厚TC4钛合金电子束焊接(EBW)接头疲劳性能的研究. 对EBW接头和母材的疲劳性能进行测试,分析接头疲劳性能的均匀性,绘制S-N曲线对比分析母材与接头的疲劳性能,并采用扫描电镜观察疲劳试样断口以解明断裂路径. 结果表明,EBW接头疲劳性能测试断裂多发生在母材,少数断裂在热影响区,接头疲劳性能沿熔深方向由上至下逐步降低,电子束焊接接头比母材高出10%,接头疲劳试验断口可分为疲劳源区、裂纹稳定扩展区和瞬断区3个典型区域,裂纹起源于试件表面边缘处.     

气孔对铝合金焊接接头超长疲劳寿命的影响

采用超声疲劳试验方法对铝合金5052-H32焊接接头进行疲劳试验,研究其在超长寿命区间(107~109周次)的疲劳强度及失效机理.结果表明,相同疲劳寿命下焊接接头疲劳强度较母材下降了73.3%,在超高周疲劳区间仍然会发生疲劳破坏;断口观察发现焊接缺陷(气孔)是诱发疲劳裂纹萌生的主要原因.为揭示焊接缺陷对焊接接头疲劳裂纹萌生及扩展的影响,采用有限元技术分析了气孔对应力集中系数和裂纹尖端应力强度因子的影响.最后讨论了焊接缺陷对疲劳寿命的影响机制及裂纹扩展特性.     

Fatigue properties of friction stir welded joint of ultrafine-grained 2024 aluminium alloy

Ultrafine-grained (UFG) 2024 aluminium alloy prepared by the equal channel angular pressing was friction stir welded (FSW). The high cycle fatigue and crack growth behaviour of the FSW joint were investigated in air and NaCl solution, respectively. This study demonstrated that FSW was a viable technique for joining UFG materials. The UFG microstructure was retained in the nugget zone (NZ). Compared with the UFG base metal (BM), FSW joint exhibited lower ultimate tensile strength and hardness, and the minimum hardness value was located in the heat affected zone (HAZ). NaCl solution significantly reduced the fatigue strength of FSW joint. Fatigue crack propagation rates in the NZ and HAZ were slower than that in the BM in the whole fatigue life.     

Fatigue crack initiation for Al-Zn-Mg alloy welded joint

To investigate fatigue crack initiation characteristics of Al-Zn-Mg alloy welded joint, notched specimens were used in fatigue test for the base metal, welding bead and heat affected zone (HAZ). The fatigue fracture surface near the fatigue crack initiation site was observed by scanning electron microscope (SEM). The results show that the differences of fatigue crack initiation life among base metal, welding bead and HAZ are not obvious. Inhomogeneity in microstructure and mechanical performance of HAZ influences the fatigue crack initiation life. The ratio of fatigue crack initiation life (Ni) to fatigue failure life (Nf) for the base metal, welding bead and HAZ of A7N01 aluminium alloy welded joint are 26.32%, 40.21% and 60.67%, respectively. Fatigue crack initiation life can be predicted using a uniform model. Observation of fatigue fracture surfaces shows that for the welding bead a fatigue crack initiates from the smooth surface due to the welding process, the blowhole in HAZ causes fatigue crack and the crushed second phase particles play an important role in fatigue crack initiation for the base metal.     

Microstructure and fatigue properties of linear friction welded TC4 titanium alloy joints

The welded joints are often subjected to cyclic stresses and high-strain-rate deformation resulting in worrisome fatigue failure. Therefore, it is necessary to evaluate the fatigue resistance and cyclic deformation characteristics of these weldments. Ti–6Al–4V–0.3Fe–0.1C–0.05N–0.015H–0.2O (TC4) titanium alloy joints were produced via linear friction welding and a sound joint was obtained. It was observed that fine subgrains formed in the weld zone where the hardness became higher. The strain ratio had a strong effect on the cyclic deformation characteristics of the joint, with hysteresis loops being different at different strain ratios. However, the difference of fatigue life of the joint was small with varying strain ratios. The stress amplitude of linear friction welded TC4 joint showed essentially cyclic softening until failure at all strain ratios. Fatigue cracks initiated from the near-surface of base metal and propagated by the formation of fatigue striations together with secondary cracks.     

X80管线钢焊接热模拟热影响区疲劳裂纹扩展行为的分析及预测

通过焊接热模拟方法对X80双相管线钢不同焊接热影响区疲劳裂纹扩展行为进行了研究,并分析实际焊接试样与焊接热模拟试样的热影响区疲劳裂纹扩展行为的差异,讨论了焊接热模拟技术应用于疲劳裂纹扩展寿命预测的可行性。结果表明,当裂纹在粗晶热影响区(CGHAZ)和临界热影响区(ICHAZ)上扩展时,由实际焊接试样与焊接热模拟试样热影响区所测得的疲劳裂纹扩展速率曲线(da/dN-DK曲线)存在明显差异,其原因与显微组织变化引起的裂纹扩展阻力大小不同有关。因此,建议采用实际焊接试样完整的热影响区所测得的da/dN-DK曲线来评估疲劳裂纹扩展寿命。     

Fatigue crack growth in the welding nugget of FSW joints of a 6060 aluminum alloy

Friction stir welded butt joints were performed on 8 mm thick sheets made of AA6060 T6 aluminum alloy by means of a CNC machine tool, at feed rates between 117 and 683 mm/min and tool rotational speed between 838 and 1262 rpm. Tensile tests, metallographic analyses and micro-Vickers tests were carried out to evaluate the mechanical properties of the joints as a function of the process parameters. The fatigue behavior was studied by means of crack growth tests performed according to ASTM E647 standard on CT specimens, with propagation in the middle of joint along the weld nugget. The results show the influence of welding process parameters on mechanical properties and fatigue behavior. Reduction of UTS of about 20–30% with respect to base material occurred with rupture in the softened zone of welding, usually HAZ. In this range, slight variations of joint efficiency were observed with f/S ratio, while the width of the softening area increases for decreasing values of this parameter. Fatigue crack growth was always slower than that in the base material at low ΔK below 12 MPa m^1/2. The effect of non-optimal welding parameters was evident at intermediate and high ΔK, due to defects, such as tunnels, that cause dramatic increase of propagation rate up to five times higher than the base material.     

TC4钛合金薄板激光焊接接头的疲劳寿命及断口分析

研究了TC4钛合金薄板激光焊接接头及母材的疲劳性能,并对其疲劳断口进行了观察.结果表明,接头的疲劳寿命在低应力水平时高于母材,在高应力水平时低于母材.母材疲劳裂纹萌生于试样表面;在裂纹扩展区有平行排列的弯曲的二次裂纹和期间更细的疲劳辉纹,瞬断区为细小的等轴韧窝.焊缝疲劳裂纹起源于表面的气孔,源区有笔直且平行排列的二次裂纹;在裂纹扩展区,断口形貌与组织有关,细晶区为韧窝,在细晶与柱状晶交界处为敞口浅韧窝,柱状晶和粗晶区为晶粒大小的刻面,上有大量的微剪切滑移带,断裂机理为滑移带形成及开裂.     

压铸镁合金AZ91D高周疲劳性能研究

研究了压铸镁合金AZ91D在应力比R=0．1条件下的高周疲劳性能。结果表明：AZ91D压铸镁合金的室温条件疲劳强度在应力比R=0．1时大约相当于其抗拉强度的44％；AZ91D合金内部的一些缺陷如夹杂等，容易引起应力集中，从而导致裂纹的萌生；AZ91D合金的疲劳断口可以观察到3个典型区域：疲劳源区、疲劳裂纹扩展区和瞬断区。疲劳裂纹扩展区的疲劳裂纹不明显，疲劳断口呈现出准解理断口的形貌。