发动机风扇静子叶片裂纹失效分析

针对发动机风扇静子叶片出现裂纹故障进行失效分析。通过对故障叶片进行外观检查、断口分析、表面形貌检查、截面金相检查、材质分析及断口区域成分分析,并对叶片上缘板排气边转接区域的应力分布进行计算,确定了叶片裂纹性质和产生原因。结果表明:故障风扇静子叶片上缘板转接区域裂纹为高周疲劳性质,导致叶片过早出现疲劳裂纹的主要原因是机匣与上缘板焊接的热影响区进入叶片上缘板排气边转接处的应力集中区;同时叶片工作时受到的振动载荷也加速了疲劳裂纹的产生。并由此提出增加叶片上缘板排气边转接区和焊缝距离的改进建议。     

发动机架圈裂纹故障分析

发动机架圈在大修分解检查中发现耳片与圈体之间的焊缝熔合区存在裂纹,结合架圈的使用条件,通过裂纹分布与形貌分析、断口特征观察、硬度测试、化学成分分析和组织检查等方法,分析了裂纹产生的原因。研究结果表明:架圈裂纹为高周疲劳裂纹;焊接缺陷、零件表层氧化脱碳及载荷分布不均匀造成疲劳裂纹集中分布在应力较大的架圈耳片焊接接头熔合区是疲劳裂纹产生的原因。     

航空发动机滑油供油管裂纹分析

飞行时航空发动机滑油压力告警,分解检查后发现滑油供油管与盖板钎焊缝焊角处存在一条裂纹,裂纹沿周向扩展,约占整个圆周的4/5,采用断口观察、金相组织分析、有限元计算分析、装配应力和振动应力测试等方法,分析了滑油供油管裂纹产生的原因。结果表明:滑油供油管裂纹性质为高周疲劳开裂,裂纹起始于外壁表面钎焊缝焊角部位,裂纹位置处装配应力为280 MPa,振动应力为21 MPa,较大的振动应力和装配应力共同作用导致滑油供油管裂纹。通过增加卡箍,改善校形,可避免类似故障。     

电站凝汽器钛管断裂原因分析

电站在进行汽轮机试验时一根凝汽器钛管发生断裂。通过采取表面宏观检查、断口分析、材质检查等方法,对钛管断裂原因进行分析,并提出改进方案。结果表明:钛管的断裂性质为高周疲劳断裂,疲劳源位于钛管的焊缝位置;钛管断裂与蒸汽冲刷导致钛管振幅过大有关,从而在疲劳性能相对较差的焊缝处萌生裂纹源。通过增加防冲板的方式,可以有效避免类似故障。     

发动机喷管扩张密封片裂纹失效机理研究

航空发动机喷管扩张密封片采用JG4246A金属间化合物高温合金铸造。针对发动机工作过程中产生的扩张密封片裂纹故障,利用视频显微镜、扫描电镜等设备,通过对故障扩张密封片进行宏观检查、断口分析、表面形貌检查、材质分析以及JG4246A材料高温热模拟试验组织对比分析,确定扩张密封片裂纹的性质和失效机理。结果表明:扩张密封片裂纹为以热应力为主引发的疲劳裂纹;组织热模拟试验对比得出,故障部位承受的最高温度已超过JG4246A的许用温度1 200℃,组织中初生γ'相明显回溶,导致性能大幅降低;在冷热交变条件下,故障部位产生较大的热应力梯度,超过了材料的疲劳极限,从而最终导致疲劳开裂。提出提高铸造工艺和优化设计的改进建议。     

发动机燃油供油导管断裂失效分析

某型发动机连续发生两起由于与主输油圈连接的U形燃油供油导管在连接处断裂引起的空中漏油故障.对断裂导管的安装位置、结构特点及装配情况进行了检查,对同型发动机进行了开车试验,对导管断口进行了分析.结果表明,两根导管的断裂性质相同,均为起始应力较大的高周疲劳断裂,疲劳裂纹起始于U形导管内侧或外侧的焊缝部位.U形导管装配应力大是导致导管疲劳裂纹早期萌生的主要原因,高压燃油冲击和脉动引起的弯曲应力对裂纹的萌生也有一定的影响,导管焊缝处存在的焊接缺陷对裂纹的萌生具有促进作用.     

航空发动机风扇叶片裂纹失效分析

航空发动机风扇叶片产生了裂纹故障。通过对故障叶片进行外观检查、断口分析、叶尖端面检查、化学成分分析、硬度检测及金相组织分析,确定了风扇叶片裂纹的性质和产生原因。结果表明:风扇叶片裂纹为高周疲劳裂纹;钛合金风扇叶片与镍包石墨涂层摩擦相容性差,叶片与机匣镍包石墨涂层发生严重摩擦是导致叶片产生早期疲劳开裂的主要原因;同时,结构的应力集中以及振动应力也会引起疲劳裂纹的萌生及扩展;并提出了相应的改进建议,避免类似故障的发生。     

发动机压气机转子叶片裂纹分析

对发动机压气机转子叶片试验件裂纹进行失效分析。通过对故障叶片进行外观检查、断口分析、表面形貌检查、截面金相检查、材质分析及断口区域成分分析,并对叶片振动应力分布进行计算,确定叶片裂纹性质和产生原因。结果表明:故障压气机转子叶片裂纹为高周疲劳性质,导致叶片过早出现疲劳裂纹的主要原因是叶身表面振动应力最大区域抛光、喷丸效果差,存在原始机械加工痕迹;最后提出避免叶身表面残留原始机械加工痕迹的改进建议。     

某型发动机导管焊缝裂纹失效分析

通过对裂纹断口进行的宏、微观观察,成分检查和综合分析,结果显示,发动机导管焊缝的裂纹性质为疲劳裂纹,疲劳起始于焊缝靠近外表面处的疏松缺陷。钎焊部位存在疏松缺陷是导致焊缝产生裂纹的根本原因。     

K465合金涡轮叶片叶身开裂分析

发动机厂内试车后进行荧光检测,发现多件K465合金涡轮叶片在叶冠叶身出现裂纹。采用体视显微镜和扫描电镜对叶片进行裂纹形貌及断口分析、金相组织检查等。结果表明：裂纹性质为疲劳开裂,起源于内腔表面。裂纹产生原因是叶片采用铝基型芯浇注以及模组方式不当,使得该位置产生较大铸造应力。通过将铝基型芯改为硅基型芯、改进铸造工艺和优化模组方式,可降低叶片的铸造应力,预防此类故障。     

Fatigue characteristics of patch plate joints by fillet welding assisted with bonding

A series of fatigue experiments and elastic analysis were carried out for investigating fatigue characteristics of patch plate joints assembled by fillet welding assisted with bonding. In the case that fatigue cracks occurred at the weld toe by the four-point bending fatigue experiment, the fatigue life of joints assembled by welding and bonding (WB) specimens were almost the same as those by only welding (W) specimens. The elastic analysis simulating the four-point bending loaded situation on W and WB specimens was performed for elucidating its reason. The stress concentration at the weld toe was even high in the WB specimens. Therefore, the fatigue life of WB specimens was not longer than that of W specimens. On the other hand, the stress around the weld root of WB specimen was around 30% of that of W specimen. The possibility of stress reduction effect by bonding was indicated around the weld root rather than around the weld toe. In order to verify this possibility, the four-point bending fatigue experiment was performed by setting the specimens so that the tensile stress was applied on the weld root. It was confirmed that the fatigue cracks occurred from the weld root in both W and WB specimens. The fatigue life defined in this study of WB specimens was from 4 to 8 times longer than that of W specimens when the applied nominal stress range was under 175 MPa. The fatigue life defined in this study of WB specimens was from 2 to 3 times longer than that of W specimens when the applied nominal stress range was over 200 MPa. The results indicated the fatigue life improvement of patch plate joints by fillet welding assisted with bonding when the fatigue cracks occurred at the weld root.     

马氏体含量对双相钢焊点拉拉疲劳性能的影响

焊点的疲劳性能是决定车身安全性和可靠性的重要因素. 对不同强度的DP780,DP980和DP1180双相钢焊点进行了检验,在疲劳试验机上进行了拉剪疲劳试验,获得了焊点的疲劳寿命曲线,分析了焊点显微组织、硬度与疲劳性能的关系. 并对焊点的疲劳失效进行了分析. 结果表明:母材性能对其焊点的疲劳性能有较大影响. 母材强度越高即马氏体含量越多,其疲劳性能越优异,三种材料的失效模式均是沿着焊点圆周断裂,裂纹在熔核与母材交界的热影响区萌生,且先贯穿板厚,贯穿板厚的裂纹作为二次裂纹源向板宽方向扩展直至断裂.     

板厚对不锈钢车体激光叠焊接头抗剪强度和疲劳强度的影响

为了研究板厚对不锈钢激光叠焊接头抗剪强度和疲劳强度的影响,该文针对0.8 mm+2 mm和2 mm+2 mm²种不同板厚搭配的不锈钢激光叠焊接头分别进行了拉伸试验和疲劳试验。结果表明,2 mm+2 mm接头的抗剪强度和疲劳强度均高于0.8 mm+2 mm接头。失效分析发现,2种接头的拉伸破坏由焊肉部位剪断引起的;2种接头的疲劳裂纹均萌生于2 mm未焊透板,裂纹起始位置在2个焊板之间靠近焊核附近未焊透板的热影响区,裂纹沿着焊核边缘向未焊透板外表面方向扩展,直至穿透未焊透板。对焊接接头部位的有限元受力分析可知,2种接头的应力集中程度的不同是造成它们抗剪强度和疲劳强度差异的主要原因。     

NiTi coatings produced by the transferred plasma arc welding process and their wear characteristics

Summary

A physical interpretation is proposed for stress conditions at the toe of weld beads, the principal point of fatigue failure in welded structures. Global stress fields at the surface of joined sheets are composed of a structural stress state due to joint shape and a local stress state due to bead shape.

The proposed approach was applied to fillet welded joints, giving two different interpretations of the local stress field.     

Fatigue crack growth behaviour of pulsed current gas tungsten arc, friction stir and laser beam welded AZ31B magnesium alloy joints

The laser beam welded joints offered better resistance against the growing fatigue cracks compared to friction stir welded and pulsed current gas tungsten arc welded AZ31B magnesium alloy joints. The formation of very fine grains in weld region, higher fusion zone hardness, uniformly distributed fine precipitates and favourable residual stress field of the weld region are the main reasons for superior fatigue performance of laser beam welded joints of AZ31B magnesium alloy.     

Fatigue behaviour of out-of-plane gusset joints with one-side fillet weld

In previous studies, many fatigue tests have been performed to investigate the fatigue behaviour of out-of-plane gusset welded joints. However, fatigue behaviour of out-of-plane gusset joints with a one-side fillet weld has not yet been clarified sufficiently. In this research, in order to quantitatively clarify the behaviour, welding residual stress at the weld toes of the joint was measured by a cutting method. In addition to this, fatigue tests were carried out on the joints with a one-side weld and turn-around weld. The plate thickness is 9 mm and the weld size is 10 mm. Moreover, finite element stress analyses were conducted on the test specimen models and parametric models with different main plate and gusset plate thickness. Their results show that fatigue cracks for out-of-plane gusset joints with a one-side fillet weld initiate from both weld toes at the start and end points of weld beads and non-penetration weld of the gusset side. Also, the crack initiation points are different depending on the weld arrangement; however, their fatigue strengths are almost same.     

Mechanism of superiority of fatigue strength for aluminium alloy sheets joined by mechanical clinching and self-pierce riveting

The static and fatigue strengths of mechanically clinched and self-pierce riveted joints in aluminium alloy sheets were compared with those of a resistance spot welded joint. Both static and fatigue strengths of the joint for the self-pierce riveting were the highest. Although the static strength for the mechanical clinching was about half for the resistance spot welding, the fatigue strength was almost similar. The mechanism of superiority of fatigue strength for the mechanical clinching and self-pierce riveting and was examined from finite element simulation of elastic loading of the joints. In the resistance spot welding, the stress concentrates at the edge of the weld nugget due to the complete bonding, whereas the concentration of stress is relaxed by the slight slip at the interface between the sheets for the mechanical clinching and self-pierce riveting. In addition, the yield stresses for the mechanical clinching and self-pierce riveting are increased by the work-hardening undergone during the joining processes, whereas the yield stress for the resistance spot welding is reversely decreased by the annealing in the welding. It was found that the mechanical clinching and self-pierce riveting have superior fatigue strength.     

弯管接头开裂分析

某飞机飞行后例行检查时,2次发现回油路上与油滤相连的铝直角弯管接头出现漏油现象,经检查弯管接头螺纹部位发生开裂。通过外观检查、断口宏微观观察、断口定量分析、能谱分析、硬度检测和金相检验等方法对开裂铝直角弯管接头进行了分析。结果表明:弯管接头开裂性质为疲劳断裂,裂纹起源于弯管接头外壁表面;A弯管接头受到较大起始应力,在振动应力的作用下裂纹进一步扩展;B弯管接头螺牙底部的裂纹应在较大应力下快速扩展形成。     

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.     

基于局部应变能密度的厚板T形接头焊趾和焊根疲劳性能分析

以装载机前车架疲劳寿命评估为目的,从前车架焊接结构关键部位中提取三种典型焊接接头,对其进行疲劳试验和分析.以局部应变能密度法为理论基础,对获得的试验数据进行处理,得到了基于局部应变能密度的疲劳寿命曲线,并采用文献中十字接头的疲劳数据验证该理论的准确性和适用性.结果表明,局部应变能密度法既可用于焊根失效疲劳评估,也可以用于焊趾失效疲劳评估;不同位置的疲劳裂纹会影响结构的刚度,进而影响结构的疲劳寿命.此外,研究了焊脚尺寸和熔深对焊接接头疲劳寿命的影响,推导了基于局部应变能密度法的疲劳失效位置转换区间.并通过文献中的疲劳数据验证了文中提出的焊趾失效和焊根失效转换区间的准确性,为合理设计未焊透厚板T形接头抗疲劳性能提供依据.