某空压机曲轴断裂失效分析

某空压机曲轴在车辆行驶过程中于轴颈圆角处发生断裂。通过宏观分析、扫描电镜分析、金相分析、圆角表面粗糙度测试以及硬度测试等方法对空压机曲轴的断裂原因进行了分析。结果表明:曲轴断裂为低应力下的高周疲劳断裂;裂纹起源于轴颈与轴肩圆角过渡处的加工刀痕,经疲劳扩展后发生断裂;曲轴断裂的根本原因是圆角处加工刀痕粗大,表面粗糙度不满足加工标准要求,应力集中严重,以及曲轴基体硬度偏低。最后针对曲轴断裂失效原因,提出了相应的改进建议。     

QT700-2球墨铸铁发动机曲轴失效分析

目的某厂生产的QT700-2球墨铸铁曲轴在路试过程中出现断裂,需寻找失效原因并提出解决措施。方法通过应用金相组织分析、化学成分分析、表面残余应力测试和力学性能测试等方法,对该曲轴的失效原因进行了分析。结果测试后分析结果表明,曲轴是在较大扭转循环载荷下,在第四连杆颈滚压圆角边缘多点萌生裂纹而导致疲劳断裂是其失效的主要原因。结论建议改进热处理工艺,保证组织的均匀性;改进加工工艺,减少应力集中;并强化表面残余应力以提高曲轴的疲劳寿命。     

汽车发动机曲轴断裂分析

某6缸发动机曲轴在运行8910km时,第六曲拐颈断裂。对断裂曲轴进行了断口观察、化学成分复验、基体硬度和显微组织检验。结果表明,曲轴的拐颈断裂为扭转疲劳断裂,断裂疲劳源位于油道孔与倒圆角曲面交接处,此处的切削加工刀痕及金属损伤形成应力集中且处于最大主应力面上,因而引发扭转疲劳断裂。     

3Cr2W8V合金钢轴承套圈用热挤压芯棒断裂失效分析

某3Cr2W8V合金钢轴承套圈用热挤压芯棒发生断裂失效,通过断口宏观分析、化学成分分析、硬度测试、金相检验等方法,分析了其断裂失效的原因。结果表明:该芯棒的结构设计不合理且机加工表面质量不良,在拉-压交变应力和扭转应力复合作用下产生应力集中,于应力集中的过渡圆角部位的夹杂物相处开裂形成疲劳裂纹源,发生早期疲劳断裂。     

40Cr钢汽车转向弯臂断裂原因

某40Cr钢汽车转向弯臂出现断裂故障,通过宏观分析、微观分析、化学成分分析、硬度测试、金相检验、受力分析、强度校核等方法对转向弯臂的断裂原因进行了分析。结果表明:转向弯臂断裂形式为双向弯曲疲劳断裂。断裂的根本原因是在弯臂R角表面存在机加工刀痕,产生了应力集中,且感应淬火表面热处理强化作用不足,使截面变化的过渡区R角处未能有效淬火而存在残余拉应力,导致裂纹在此处萌生,在转向循环应力作用下裂纹扩展直至发生疲劳断裂。     

空压机曲轴断裂失效分析

某空压机曲轴在运行约5 000h后发生断裂失效,通过宏观检验、断口分析、金相检验以及硬度测试等方法,对空压机曲轴断裂原因进行了分析。结果表明:由于曲轴中存在严重的疏松缺陷,在运行过程中于曲轴轴颈和轴拐R过渡表面疏松处萌生裂纹,在交变应力作用下,裂纹以疲劳方式扩展直至曲轴断裂失效。     

HXD1机车牵引电机转轴组件断裂失效分析

HXD1型电力机车的牵引电机转轴和小齿轮轴采用圆锥过盈配合传动结构(下称转轴组件),使用中该组件出现了早期断裂失效.本文通过理化检测、断口和配合面宏/微观形貌观察等失效分析技术对失效组件进行了分析.结果表明,材料成分、组织和显微硬度正常,小齿轮轴和电机转轴的失效形式分别为高周疲劳断裂和微动疲劳断裂.造成组件失效的原因和过程是,小齿轮轴近齿端油槽-油孔交界线处有较大的结构应力集中,油槽底部周向加工刀痕造成附加应力集中,在应力集中和旋转弯曲疲劳载荷作用下油孔边两个应力集中点萌生了疲劳裂纹并扩展;随小齿轮轴裂纹的不断扩展转轴组件结构刚度减小,继而诱发了与小齿轮轴匹配的电机轴配合面的微动疲劳,电机轴疲劳裂纹萌生于微动区的边缘处;电机转轴先于小齿轮轴完全断裂.基于本文的分析结果提出了提高组件抗疲劳断裂的技术措施.     

分动箱齿轮断裂原因

某分动箱的20CrMnTi钢齿轮在工作过程中发生断裂.采用宏观分析、微观分析、化学成分分析、硬度测试、硬化层深度测量、非金属夹杂物分析、金相检验等方法对齿轮的断裂原因进行了分析.结果表明:齿面上残留的加工刀痕导致应力集中,在周期载荷的作用下,疲劳裂纹源首先在残留的加工刀痕较深处形成,随后裂纹逐渐扩展,最终齿轮发生疲劳断...     

自由锻电液锤锤杆断裂分析

某5 t自由锻电液锤锤杆在锻打过程中突然发生断裂,采用宏观检验、化学成分分析、金相检验和力学性能测试等方法对锤杆断裂原因进行了分析。结果表明:由于该锤杆活塞和杆的圆弧过渡处未按设计要求做到光滑过渡,机加工刀痕明显,造成该处应力集中严重,促使裂纹源在此处萌生;加之锤杆的力学性能也略低于技术要求,导致锤杆在拉-压载荷的作用下发生了低应力高周早期疲劳断裂。     

电梯驱动轴断裂原因分析

某电梯公司生产的材料为Q345A钢的电梯驱动轴在短期内发生断裂失效,采用化学成分分析、金相检验、硬度测试、扫描电子显微镜分析等方法对驱动轴断裂原因进行了分析。结果表明:该驱动轴断裂属性为多源旋转弯曲疲劳断裂;断裂源位于驱动轮盘和驱动轴过渡的环焊缝热影响区的应力集中处,加之驱动轴表面加工刀痕明显,且存在硬而脆的马氏体非正常组织,进一步加剧了该处的应力集中,在扭转力作用下萌生多源裂纹,裂纹不断扩展最终导致断裂。     

挤出机摩擦离合器螺栓断裂分析

某挤出机中气动摩擦离合器与减速器端连接的螺栓在使用过程中经常发生断裂,改用另一种材料的螺栓后情况未有很好改善。采用化学成分分析、力学性能测试、断口分析和金相检验等方法,对螺栓断裂的原因进行了分析。结果表明：起裂源位于螺栓的加工刀痕、表面擦伤处及因微动疲劳所致的螺纹微裂纹处,这些部位均存在应力集中,在振动作用下,萌生的裂纹不断扩展,使有效承载面积不断减小,最终引起螺栓疲劳断裂。     

Failure Analysis of a Truck Diesel Engine Crankshaft Made from Spheroidal Cast Iron

A diesel engine crankshaft fractured in service after 13,656 km of operation. The fracture took place on the sixth, the fifth, and the fourth crankpins and the fracture surfaces have a 45° inclination with respect to the axial of crankshaft. The cracks of the sixth and the fifth crankpin are across the oil hole and a complete fracture took place at the sixth crankpin which bore the maximum torque load. On the fourth crankpin, crack is only through the thin wall side of oil hole. The results indicate that fatigue fracture is the dominant failure mechanism of the crankshaft. It was observed that the fatigue cracks in the crankpins initiated at machining dents present on the wall of oil hole. The appearance of the machining dents on the wall of oil hole suggests improper machining and these dents supplied the stress concentration site that was mainly responsible for the fatigue fracture of crankshaft.     

蜗轮连接螺栓断裂失效分析

装卸料机上的蜗轮连接螺栓材料为35钢,强度等级为10.9级,在设备运行大约10a后发生断裂。对断裂螺栓进行宏观、化学成分、硬度、金相、能谱和断口分析后得出,该螺栓的断裂性质为双向弯曲疲劳断裂,螺栓表面的脱碳和螺纹颈部的应力集中降低了该部位的疲劳性能。通过综合分析和螺栓受力估算后得出,螺栓断裂的主要原因是螺栓和内齿轮螺栓孔之间存在较大的间隙,使螺栓的受力状态和受力大小过早地发生了变化,造成连接螺栓疲劳断裂。     

Failure and Fracture Analysis of Bolt Assembled on the Fan Used in the Internal Combustion Engine

Three connecting bolts fractured, which were assembled on the fan used in the internal combustion engine. Detailed fractographic study and metallurgical analysis were focused on the fractured bolts. Fractographic and metallurgical studies indicate that the fracture surface and the microstructure of three bolts exhibit similar features. The fatigue fracture is the main failure mechanism of the bolts. Appearance of the micro-cracks in the thread tip of the fractured bolts makes the stress at the thread regions increase intensively so that the fatigue cracks initiated from the thread regions. Due to the presence of dynamic load, the bolts were never properly tightened during installation which should be responsible for the formation of the cracks.     

Failure Analysis of a Vehicle Engine Crankshaft

An investigation of a damaged crankshaft from a horizontal, six-cylinder, in-line diesel engine of a public bus was conducted after several failure cases were reported by the bus company. All crankshafts were made from forged and nitrided steel. Each crankshaft was sent for grinding, after a life of approximately 300,000 km of service, as requested by the engine manufacturer. After grinding and assembling in the engine, some crankshafts lasted barely 15,000 km before serious fractures took place. Few other crankshafts demonstrated higher lives. Several vital components were damaged as a result of crankshaft failures. It was then decided to send the crankshafts for laboratory investigation to determine the cause of failure. The depth of the nitrided layer near fracture locations in the crankshaft, particularly at the fillet region where cracks were initiated, was determined by scanning electron microscope (SEM) equipped with electron-dispersive X-ray analysis (EDAX). Microhardness gradient through the nitrided layer close to fracture, surface hardness, and macrohardness at the journals were all measured. Fractographic analysis indicated that fatigue was the dominant mechanism of failure of the crankshaft. The partial absence of the nitrided layer in the fillet region, due to over-grinding, caused a decrease in the fatigue strength which, in turn, led to crack initiation and propagation, and eventually premature fracture. Signs of crankshaft misalignment during installation were also suspected as a possible cause of failure. In order to prevent fillet fatigue failure, final grinding should be done carefully and the grinding amount must be controlled to avoid substantial removal of the nitrided layer. Crankshaft alignment during assembly and proper bearing selection should be done carefully.     

Failure analysis on fracture of worm gear connecting bolts

The worm gear connecting bolts of refueling machines of a nuclear power plant, with implementing standard of ANSI/ASME B18.3 and ASTM A574-08 and strength grade of 10.9, fractured at the thread neck position after running for about 10 years, and means such as macro examination, chemical compositions analysis, hardness testing, metallographic examination and fracture analysis, were used to analyze the fracture property and reasons of the bolts. The results show that the fracture of the bolts is due to two-way bending fatigue fracture. Surface decarburization of the bolts and stress concentration at the bolt thread neck decreased the fatigue strength of this position and resulted in the initiation of fatigue cracks. By comprehensive analysis and stress estimating, it was concluded that the main reason for fracture of the bolts is that there was a big gap between the bolts and the bolt holes, which resulted in fatigue fracture of the worm gear connecting bolts.     

A case study of cracks in aeroengine compressor discs

Cracks were found in four aeroengine compressor discs. These cracks initiated from holes in the discs and propagated in a radial direction. An analysis of one disc is presented in this paper. The cracks are fatigue cracks from high alternating stress. The reason why cracks initiated at holes is that there were coarse machining marks and a resonance stress at the edge of the hole.     

轮胎钢圈开裂失效分析

某公司生产的轮胎钢圈在安装服役15d左右后出现批量开裂现象,采用宏观分析、化学成分分析、力学性能测试、金相检验及断口分析等方法对轮胎钢圈的开裂原因进行了分析。结果表明:该批轮胎钢圈失效为早期疲劳开裂;轮胎钢圈轮辋侧焊缝熔合线处存在机加工刀痕,产生缺口应力集中,加之裂源处焊缝熔深不足降低了其疲劳性能,加速了疲劳裂纹的萌生和扩展,最终导致轮胎钢圈早期疲劳开裂。     

Fatigue crack growth simulation in a first stage of compressor blade

A first-stage rotary compressor blade of a Model GE-F6 gas turbine failed due to vibration in early March 2008. Initial investigations showed that pitting on the pressure side of the blade caused micro cracks, leading to larger cracks due to high cycle fatigue. To assess this failure, a series of experimental, numerical, and analytical analyses were conducted. Fractography of the fractured surface of the blade indicated that two semi-elliptical cracks incorporated and formed a single crack. In this study, static and dynamic stress analyses were performed in Abaqus software. Moreover, fracture mechanics criterion was accomplished to simulate fatigue crack growth. This was carried out using a fracture analysis code for 3-dimensional problems (Franc3D) in two states. Firstly, stress intensity factors (SIFs) for one semi-elliptical surface crack and then SIFs for two semi-elliptical surface cracks were taken into account. Finally, the Paris and Forman–Newman–De Koning models were used to predict fatigue life. Since stress level and crack shape in both conditions are the same and the SIF at the crack tip reaches the fracture toughness of the blade, SIFs results indicate that insertion of a second crack has no effect on the final SIF, however, the second crack facilitates the process of reaching the critical length. So, fatigue life in two-crack condition is less than in the one-crack state.