发动机安装座焊缝开裂分析

采用宏观观察、SEM断口检查、材料检查、金相检查方法对某发动机部件安装座焊缝裂纹进行了检查及分析,确认了该裂纹产生是由于在发动机该部件的薄壁上焊接该安装座时,存在焊接应力;装配焊接定位时产生校正应力;加之导管传给安装座的振动应力,叠加产生较大的应力,在此大应力的作用下,由安装座焊缝边缘应力集中的薄弱部位产生疲劳裂纹.提出了预防安装座焊缝疲劳裂纹失效的防范措施.     

滤清器外壳开裂分析

滤清器外壳安装在汽车发动机台架上试验500 h后出现裂纹,采用宏观和微观分析、化学成分分析和金相检验等方法对开裂原因进行了分析。结果表明:滤清器外壳的外壁局部区域在拉延时产生了微裂纹,在交变应力作用下形成疲劳裂纹,并导致早期疲劳开裂。     

高炉煤气透平动叶片裂纹分析

在对高炉煤气余压透平发电机转子动叶片进行表面渗透探伤时,发现Ⅰ级动叶片组中有6片叶片的叶榫部有裂纹.为探明裂纹的形成原因,对叶榫裂纹进行了化学成分、高、低倍组织及断口的宏、微观分析.分析结果表明,叶榫第一齿根裂纹属于疲劳裂纹.疲劳裂纹形成的原因主要与齿根底部过渡圆弧类似于直角、圆弧底部的加工条痕比较粗糙、显微组织粗大不均匀、铁素体条带分布不合理以及楔块装配面接触不良等因素有关.     

轮胎螺栓断裂失效分析

某汽车轮胎螺栓在使用过程中发生断裂。采用宏、微观检验和化学成分分析等方法对失效件进行了检测。结果表明，其断裂形式为弯曲疲劳断裂。疲劳裂纹的形成是由于螺纹牙底存在脱碳和折叠裂纹等缺陷，这些缺陷的存在使该材料产生了较大的应力集中，从而导致螺栓开裂失效。     

螺杆泵主轴裂纹分析

某公司生产的螺杆泵主轴在运行过程中发生漏水,磁粉探伤表明沿圆盘根部有裂纹。采用化学成分分析、力学性能试验、金相检验、扫描电镜观察等方法对裂纹形成原因进行分析。结果表明:螺杆泵主轴失效的主要原因是过渡圆弧角较小,导致应力集中,促使疲劳裂纹形成。     

TC6钛合金压气机叶片裂纹产生原因

某型航空发动机在完成总运转时间2 081 h后进行拆解检查,在一件TC6钛合金高压压气机Ⅵ级转子叶片上发现沿叶片纵向分布有两条裂纹。通过宏观观察、断口分析、金相检验、能谱分析及硬度测试等方法对裂纹产生原因进行了分析。结果表明:该裂纹为试车过程中产生的疲劳裂纹。发动机在完成阶段性试车后进行拆解检查,复装后叶尖间隙不满足设计要求,导致在随后的试车过程中叶尖与机匣封严涂层发生严重刮擦,造成局部超温、掉块,形成疲劳裂纹源并最终扩展为裂纹。     

一种悬臂弯曲加载表面裂纹扩展试样及其应用

介绍了一种带有上下对称圆弧的板状试样,试样上圆弧几何中心预制有半椭圆表面裂纹,这种设计能够较好地模拟压力容器具有表面裂纹时的特点.利用这种试样,可以完成悬臂弯曲加载恒总应变控制下的低周疲劳表面裂纹扩展速率试验,获得表面裂纹扩展长度和深度的关系,最终建立表面和深度裂纹扩展速率与总应变的函数关系.据此,可为含有表面裂纹体的压力容器低周疲劳剩余使用寿命评估提供依据.     

压力容器用钢低周疲劳表面裂纹扩展速率试验研究

压力容器的表面裂纹常常会导致低周疲劳破坏.因此,研究压力容器用钢的低周疲劳表面裂纹扩展规律,具有重要意义.本文在带有上下对称圆弧板状试样的上圆弧几何中心,加工预制了半椭圆表面裂纹,以模拟压力容器具有表面裂纹时的特点.同时,在上圆弧一侧设计加工了特定形状和尺寸的刀口,装卡COD位移规,用来控制表面裂纹前缘的应变.以10C...     

疲劳短裂纹形成和扩展行为研究

平均应力是影响材料疲劳行为的重要因素,选择平均应力下疲劳短裂纹行为作为研究对象,应用裂纹位错理论和椭球体异性夹杂理论对疲劳短裂纹问题进行了深入的分析和探讨,在以下几方面取得了新的进展。 首先对不同应力条件下光滑试样的疲劳短裂纹行为进行了系统的试验研究,考察了应力幅、平均应力及微观结构等因素对疲劳短裂纹生长的影响,并给出了一个关于疲劳短裂纹形成和扩展的划分定义;建立了循环应力下的疲劳短裂纹位错模型,通过对疲劳短裂纹及其顶端塑性区与晶界交互作用的分析,建立了疲劳短裂纹门槛应力条件,并由此推导出一个双曲线形式的疲劳极限图线。提出了应用裂纹顶端塑性位移幅度描述疲劳短裂纹生长速率的方法,由疲劳短裂纹形成位错模型给出了一个振荡形式发展的疲劳短裂纹生长速率表达式.其范围包络线可以较好地覆盖疲劳短裂纹速率的试验数据;应用Eshelby椭球体本征应变问题解,求得了裂纹顶端延伸位移。提出应用有效裂纹顶端延伸位移幅度来处理各种应力条件下疲劳短裂纹扩展速率的方法,使得疲劳短裂纹扩展速率在描述上实现了归一。     

ZM6尾减机匣开裂失效分析

某型号飞机尾减机匣试验过程中出现异常,荧光检查发现裂纹.通过故障机匣外观检查、裂纹断口宏微观观察及能谱分析、材料硬度检测、金相检查等试验得出结论,尾减机匣失效属低周疲劳开裂,机匣表面Nd元素偏析是导致机匣疲劳裂纹形成的直接原因,材料韧性不足一定程度上促进了裂纹的疲劳扩展,根据分析结果,给出提高尾减机匣受力部位的疲劳抗力,避免故障再次发生的有效方法.     

波音747SP飞机主起落架收放作动筒断裂分析

采用宏、微观检验方法对国外某航空公司波音747SP飞机主起落架收放作动筒断裂性质和原因进行了分析。查明作动筒断裂性质为腐蚀疲劳，腐蚀疲劳起源于作动筒外壁表面的网状裂纹，而这些网状裂纹产生于电镀之前，是一种加工缺陷。作动筒表面裂纹的网状形态以及初始深度符合磨削裂纹的特点。     

曲轴疲劳试样表面磁痕分析

采用宏观和微观检验等手段对曲轴疲劳试样不同部位磁痕产生的原因进行了分析。结果表明:磁痕是由于带状组织、疲劳裂纹和磨削裂纹等原因造成的。磨削裂纹主要是由于磨削时摩擦应力过大造成的。原材料中存在较严重的带状组织,导致淬火组织和残余应力不均匀,对磨削裂纹的产生起到了促进作用。     

Offshore fatigue crack repair by grinding and wet welding

A fatigue crack repair option based on crack removal by grinding and subsequent filling of the resultant groove by wet welding is presented. Author's experimental and fracture mechanics analysis experience on fatigue crack removal by grinding has demonstrated that a fatigue life extension factor of 2 to 3 is feasible for crack removal done before crack penetration has reached 30% of the plate thickness. However, it has also been demonstrated when groove is left empty, that fatigue life extension after crack removal is mainly due to the stage of fatigue initiation because crack propagation after removal has a higher rate than in as‐welded condition. To overcome this situation, this work proposes for an underwater application like in the offshore industry, that filling the grinded groove by means of wet welding would produce a crack repair with a longer fatigue life than the empty groove case.     

电解充氢对堆焊熔合区疲劳裂纹扩展行为的影响

研究了阴极充氢前后堆焊熔合区疲劳裂纹扩展行为,发现堆焊熔合区对疲劳裂纹的扩展有阻碍作用,充氢对裂纹扩展速率无明显影响,但使熔合区出现大量二次裂纹,随着充氢时间的延长,二次裂纹将更加严重。     

曲轴弯曲疲劳试验裂纹研究与失效判定

通过对疲劳裂纹的产生、扩展机理研究和试验,结合疲劳试验数据分析了疲劳裂纹扩展与疲劳寿命的关系。试验结果及分析表明,大量经圆角滚压强化的球墨铸铁曲轴,疲劳试验运行107次在连杆颈与曲柄臂过度圆角产生微裂纹,该裂纹属于非扩展裂纹,继续试验时裂纹不扩展,试样在该载荷下具有无限疲劳寿命。     

Fatigue life assessment of nodular cast iron containing casting defects

The fatigue behaviour of a nodular cast iron containing casting defects has been investigated in the high-cycle fatigue regime. In this paper, we propose a fatigue life assessment model for flawed materials based on a fracture mechanics approach which takes into account the position and size of the defect, short crack behaviour and the notch effect introduced by the defect. The fatigue behaviour of smooth samples, and long and short crack behaviour have been experimentally determined in order to identify the relevant mechanical parameters; these being introduced into the model. An experimental study has been made both in air and in vacuum in order to account for the position of the defect, noting that internal defects are supposed to be under vacuum conditions. Experimental results, which are based on a two-crack front-marking technique specially developed for this study, show that the propagation of natural cracks is controlled by the effective stress intensity factor in air as well as in vacuum. The K calculation for a short crack in the stress field of a notch is analysed using numerical elastic–plastic results. Comparison between experimental results and the computation of fatigue life for fatigue lives less than 10⁶ cycles shows that the fatigue behaviour of nodular cast iron is controlled by a propagation process. The model proposed is thus relevant for fatigue lives less than 10⁶ cycles so that the defect can be considered as a crack and the initiation stage neglected. Closer to the fatigue limit, this study shows that the initiation stage should be considered in the assessment of fatigue life of nodular cast iron, because a single macroscopic propagation assessment is not enough to describe the whole fatigue life. The defect cannot be considered as a pre-existent crack in the high-cycle fatigue range (>10⁶ cycles), and the initiation stage that contains microcrack propagation around the defect should be evaluated when assessing the high-cycle fatigue life of nodular cast iron.     

Effect of defects on the fatigue limit of Ni‐based superalloy 718 with different grain sizes

Tension‐compression fatigue tests were performed on two types of Ni‐based superalloy 718 with different microstructures in which small artificial defects of various sizes and shapes were introduced. The susceptibility of the fatigue strength to the defects varied significantly with the microstructure morphology, ie, a smaller grain size made the alloy more susceptible to defects. The fatigue limit as a small‐crack threshold was successfully predicted using the parameter model. The evaluation of the fatigue limit was classified into the following three stages depending on the defect size: (a) harmless defect regime, (b) small‐crack regime, and (c) large‐crack regime. Such a classification enabled comprehensive evaluation of the fatigue limit in a wide range of defect size, considering (a) defect size over a range of small crack to large crack and (b) characteristics of matrix represented by grain size and hardness.     

进料泵传动轴断裂分析

采用显微组织分析、扫描电镜分析和拉伸试验等方法对进料泵传动轴的断裂进行了失效分析。结果表明,泵轴断裂属疲劳失效,轴中段键槽处在制造过程中存在淬火裂纹是导致疲劳断裂的主要原因。     

Fatigue crack initiation and growth in solder alloys

In modern electronic packaging, especially surface mount technology (SMT), thermal strain is usually induced between components during processing, and in service, by a mismatch in the thermal expansion coefficients. Since solder has a low melting temperature and is softer than other components in electronic packaging, most of the cyclic stresses and strains take place in the solder. Fatigue crack initiation and fatigue crack propagation are likely to occur in the solder even when the cyclic stress is below the yield stress. It is an objective of this research to study the behaviour of fatigue crack initiation and propagation in both lead‐containing solder (63Sn‐37Pb), and lead‐free solders (Sn‐3.5Ag). The effect of alloying (Cu and Bi addition), frequency, tensile hold time and temperature on low cycle fatigue (LCF) behaviour of the solders is discussed. Mechanisms of LCF crack initiation and propagation are proposed and LCF life prediction, based on the various models, is carried out.