TC11钛合金电子束焊接接头超高周疲劳性能

采用天津大学自行研制的TJU-HJ-I型超声疲劳试验系统研究了TC11钛合金电子束焊焊接接头的超高周疲劳性能. 试验结果表明,TC11钛合金电子束焊接接头在107周次以上仍然会发生疲劳失效,S-N曲线呈现连续下降的趋势,没有明显的转折. 试件的断裂位置大多数为母材处,焊缝和热影响区的疲劳性能要比母材好,这与焊接接头的微观组织有关. 通过SEM对超声疲劳断口形貌进行观察发现,断裂试件的疲劳裂纹大部分在表面萌生,然而在应力范围较低时,疲劳裂纹的萌生位置有从表面转向次表面的趋势.     

Hastelloy C-276薄板激光焊接接头疲劳性能EI北大核心CSCD

对0.5 mm厚Hastelloy C-276薄板激光焊接接头进行疲劳试验,结合应力-寿命(S-N)曲线和疲劳断口形貌,研究母材及焊接接头的疲劳性能,分析母材和焊接接头的疲劳断裂机理。结果表明:0.5 mm Hastelloy C-276薄板焊接接头和母材的S-N曲线斜率基本相同,焊接接头疲劳性能和母材的基本相当;母材疲劳断口疲劳裂纹起源于试样侧表面,主要沿宽度方向扩展,随着应力的减小,疲劳源数目减少,疲劳裂纹扩展速率减小;焊接接头在母材和焊缝处随机断裂,焊接接头母材区断口形貌和母材断口形貌基本一致,而焊接接头焊缝区断口的疲劳裂纹起源于侧表面棱角处和焊缝表面,焊缝表面是主要疲劳源,裂纹主要沿厚度方向进行扩展,疲劳裂纹扩展区呈现出准解理断裂特征。     

Hastelloy C-276薄板激光焊接接头疲劳性能

对0.5 mm厚Hastelloy C-276薄板激光焊接接头进行疲劳试验,结合应力-寿命(S-N)曲线和疲劳断口形貌,研究母材及焊接接头的疲劳性能,分析母材和焊接接头的疲劳断裂机理。结果表明:0.5 mm Hastelloy C-276薄板焊接接头和母材的S-N曲线斜率基本相同,焊接接头疲劳性能和母材的基本相当;母材疲劳断口疲劳裂纹起源于试样侧表面,主要沿宽度方向扩展,随着应力的减小,疲劳源数目减少,疲劳裂纹扩展速率减小;焊接接头在母材和焊缝处随机断裂,焊接接头母材区断口形貌和母材断口形貌基本一致,而焊接接头焊缝区断口的疲劳裂纹起源于侧表面棱角处和焊缝表面,焊缝表面是主要疲劳源,裂纹主要沿厚度方向进行扩展,疲劳裂纹扩展区呈现出准解理断裂特征。     

TC4-DT钛合金电子束焊接接头的拉伸性能

用电子束焊接50 mm厚TC4-DT钛合金板,对母材、焊缝金属和焊接接头的拉伸性能进行测试,获得了母材和焊缝金属的基本拉伸性能数据,分析了电子束焊接接头显微组织对拉伸性能的影响.结果表明,电子束焊接使TC4-DT钛合金焊缝金属强度增加,塑性和韧性降低,应变硬化能力增强.焊接接头拉伸试验的断裂位置均在离焊缝边缘较远的母材上,母材为整个接头的薄弱环节.母材和焊缝金属拉伸断口均表现出延性韧窝断裂特征.与母材金属相比,焊缝金属拉伸性能的变化与电子束焊接过程中冷却速度快、在焊缝区形成了粗大β柱状晶及针状马氏体有关.     

TA15钛合金电子束焊焊接接头力学性能

钛合金材料以及相关制造技术是实现飞机先进性的重要基础之一,电子束焊接是钛合金板材一种先进的焊接形式.对TA15钛合金板材电子束焊接试样进行了金相分析和静力试验、疲劳试验和扫描电镜(SEM)分析.结果表明,TA15板材电子束焊焊接接头的焊缝、热影响区和母材的微观组织差别明显;焊缝韧性降低,抗拉强度高于母材;热影响区尺寸较小,在1～2 mm左右,是焊接接头的薄弱部位;疲劳裂纹大多萌生于焊接热影响区区域,疲劳破坏试样断口的SEM分析表明,疲劳裂纹大多起源于焊接热影响区的气孔处.     

TC4-DT钛合金电子束焊接接头的疲劳断口研究

采用单边缺口试样,用扫描电镜观察了TC4-DT钛合金母材及电子束焊接接头焊缝区与热影响区的疲劳断口,分别分析了疲劳裂纹起裂源、扩展区及瞬断区的断口形貌特征.结果表明,疲劳裂纹均起裂于试样缺口根部,并由试样的一侧扩展到另一侧,裂纹扩展初期均沿一定的结晶面扩展,属于脆性穿晶断裂;母材和热影响区的瞬断部位均有明显的韧窝出现,属于塑性沿晶断裂,而焊缝区断口上韧窝不明显;热影响区疲劳断口有疲劳条带出现,但在母材和焊缝区断口上很难看见.     

TA15钛合金焊接接头性能与断裂行为研究

对TA15钛合金氩弧焊和电子束焊焊接接头的性能与微观组织进行了分析研究,并结合断口观察,对其断裂行为进行了研究.结果表明,两种焊接接头强度均与母材相当,而塑性明显降低.焊接接头热影响区组织均呈现从粗大等轴组织到魏氏组织的过渡变化特征.疲劳断裂位置一般位于靠近熔合线的焊缝区域,主要原因是此区域存在组织突变和熔合线气孔.焊接气孔对接头疲劳性能影响较大.两种焊接接头疲劳断口特征存在明显区别.     

TA15钛合金薄板激光-TIG复合焊接头疲劳性能研究

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。     

TC11/TC17线性摩擦焊接头疲劳性能及断口分析

针对TC11/TC17线性摩擦焊接头及母材进行了高周疲劳性能测试。结果表明,接头的高周疲劳强度与TC11母材相当,断裂发生在TC11母材一侧。通过对断口形貌进行分析,发现疲劳断口分为明显的3个区域:裂纹萌生区、裂纹扩展区、最终断裂区,且疲劳断口裂纹萌生于试件近表面处。裂纹扩展区较平整,在整个断口中占了较大的比例;裂纹扩展的初始阶段可观察到二次裂纹和由塑性变形引起的撕裂棱存在,裂纹扩展区后期阶段断口形貌以塑性撕裂为主。最终断裂区与裂纹扩展区不在一个平面上,TC11/TC17线性摩擦焊接头的疲劳断口为沿晶断口和撕裂棱的混合断口。     

焊接速度对TC18钛合金厚板电子束焊接接头疲劳性能的影响

采用电子束焊接的方法,实现了15mm TC18钛合金厚板的焊接。利用光学显微镜、扫描电镜及透射电子显微镜对接头的宏观形貌、显微组织及断口特征进行分析,并用电子万能试验机测试了接头的疲劳性能,研究了不同焊接速度(10 mm/s、20mm/s、30mm/s)对TC18钛合金厚板电子束焊接接头疲劳性能的影响。结果表明,焊缝熔合区主要由柱状的β相和针状的α马氏体相组成。随着焊接速度的增加,焊缝区上熔宽、中熔宽、下熔宽都呈明显减少,焊缝区晶粒细化,导致焊接接头疲劳性能增加。在Nf =107时,随焊接速度从10mm/s增加到30mm/s,焊缝疲劳极限提高近29%。接头疲劳试验断口可分为疲劳裂纹源区、裂纹扩展区和裂纹瞬断区三个典型区域,疲劳裂纹都起源于试件表面,随着焊接速度增大,瞬断区占的比例减小,疲劳性能增强。     

TC4-DT电子束焊接头显微组织及疲劳裂纹扩展行为

在光学显微镜下对TC4-DT钛合金电子束焊接头显微组织进行了分析,讨论了接头不同位置显微组织特征.比较了疲劳裂纹始于焊接接头不同位置时的宏观裂纹扩展路径及裂纹扩展速率,依据焊接接头显微组织特点讨论了显微组织对疲劳裂纹扩展行为的影响.结果表明,电子束焊接头沿熔深方向显微组织存在一定的差异;文中条件下,与母材区相比焊缝熔合区及热影响区具有较高的疲劳裂纹扩展抗力,导致裂纹扩展路径逐步偏向母材区,最后讨论了裂纹扩展路径的偏折对裂纹扩展速率的影响.     

转向架用SMA490BW钢焊接接头超高周疲劳性能

采用超声疲劳试验方法对SMA490BW钢焊接接头的超高周疲劳性能进行研究,通过X射线应力仪对焊接试样残余应力进行测试,采用扫描电镜对疲劳裂纹的萌生、扩展及疲劳断裂机理进行观察和分析. 结果表明,SMA490BW钢母材的疲劳性能远高于焊接接头,在1 × 108循环周次条件下,接头的疲劳强度为141 MPa,仅为母材的44.2%. 接头裂纹主要萌生于焊趾表面缺陷处,疲劳断裂机理表现为准解理断裂, 并伴有塑性变形痕迹. 焊趾处几何不连续造成的应力集中和焊缝及其附近区域一定的残余拉应力,以及接头各微区组织和性能的不均匀性,是导致焊接接头疲劳性能偏低的主要原因.     

Microstructure and Fatigue Properties of Laser Welded DP590 Dual-Phase Steel Joints

In this paper, cold-rolled DP590 dual-phase steel sheets with 1.5 mm thickness were butt-welded by a fiber laser, and the evolution and effect on microhardness, tensile property and fatigue property of the welded joint microstructure were studied. The results showed that the base metal is composed of ferrite and martensite, with the martensite dispersed in the ferrite matrix in an island manner. The microstructure of the weld zone was lath-shaped martensite that can be refined further by increasing the welding speed, while the heat-affected zone was composed of ferrite and tempered martensite. The microhardness increased with increasing welding speed, and the hardness reached its highest value—393.8 HV—when the welding speed was 5 m/min. Static tensile fracture of the welded joints always occurred in the base metal, and the elongation at break was more than 16%. The conditional fatigue limits of the base metal and the weld joints were 354.2 and 233.6 MPa, respectively, under tension–tension fatigue tests with a stress rate of 0.1. After observation of the fatigue fracture morphology, it was evident that the fatigue crack of the base metal had sprouted into the surface pits and that its expansion would be accelerated under the action of a secondary crack. The fatigue source of the welded joint was generated in the weld zone and expanded along the martensite, forming a large number of fatigue striations. Transient breaking, which occurred in the heat-affected zone of the joint as a result of the formation of a large number of dimples, reflected the obvious characteristics of ductile fracture.     

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.     

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.     

基于原位SEM的激光-MIG复合焊接7075-T6铝合金疲劳裂纹扩展行为

通过扫描电镜原位观察激光复合焊接头各区裂纹的扩展行为. 结果表明,焊缝各区组织的不同使得疲劳裂纹扩展行为发生明显改变,疲劳裂纹位于焊缝中心时,裂纹总体沿着垂直于载荷主轴的方向扩展;疲劳裂纹位于热影响区时,裂纹大致成"Z"字型路径进行扩展;疲劳裂纹在焊缝中心和热影响区扩展时都存在二次裂纹;疲劳裂纹在母材区扩展时,呈现出单一和典型的裂纹扩展模式. 此外,通过原位SEM观察获得不同循环周期下的裂纹扩展长度,进而推算得到7075-T6铝合金接头各区内疲劳裂纹扩展速率的Paris公式.     

A7N01铝合金焊接接头的疲劳特性及寿命预测(英文)

研究A7N01铝合金焊接接头的疲劳特性,提出基于疲劳裂纹萌生寿命的寿命预测模型。母材、热影响区和焊缝三个区域内的疲劳裂纹萌生寿命差异较小。在这三个区域内,疲劳裂纹萌生寿命与疲劳总寿命之比是一个依赖于材料的参数,对于母材、热影响区和焊缝分别为26.32%、40.21%和60.67%。提出的疲劳寿命预测模型与实验结果和Basquin’s模型预测结果吻合良好。利用扫描电子显微镜(SEM)对疲劳断口进行观察,发现焊缝区域的裂纹萌生于焊接过程中产生的光滑表面。热影响区内疲劳裂纹萌生于熔合区气孔。母材中破碎的第二相是引起疲劳裂纹的主要原因。     

ON FATIGUE CRACK PATH DEVIATION AT ELEVATED TEMPERATURE IN ELECTRON BEAM REPAIRED WELDMENTS OF TURBINE DISK

Fatigue crack growth behaviors in electron beam weldments of a nickel-base superalloy are. studied. The objective of this paper is to discuss effects of the inhomogeneity of mechanical performance on fatigue crack growth (FCG) rate and crack path deviation (CPD). The base metal served in a turbine disk of aerospace engine was selected to fabricate bead-on-plate weldments by using electron beam welding. Some wedge-type opening loading specimens, notched in three different zone of weld metal, HAZ and base metal, were employed and performed fatigue crack growth tests at 650℃. The results show that the fatigue crack growth of electron beam welded joints is instable due to the influence of mechanical heterogeneities. Owing to the crack deviation at the weld metal and heat-affected-zone (HAZ), the effective growth driving force at the tip of fatigue crack was reduced with the reduction of the effective stress intensity factor (SIF) which finally causes fatigue crack rate decrease. Fatigue crack was strongly affected by size and the symmetrical characteristics of the plastic zone at the crack tip, which means that the integrity of the welded structure containing the fatigue crack mainly depended on the toughness of the low strenqth zone.     

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.