60Si2CrVA弹簧断裂原因分析

通过断口分析、金相检验、硬度测试及化学成分分析等方法,对60Si2CrVA弹簧进行断裂原因分析。结果表明：该弹簧断裂失效性质为疲劳断裂;弹簧端圈磨削裂纹是导致弹簧断裂的根本原因;提出了防止磨削裂纹产生的建议．对指导生产有一定参考价值。     

黄台发电厂7#机末级叶片断口分析

对黄台发电厂７＃机末级叶片断口进行了分析。认为,在该叶片进汽侧靠近头部的硬质合金堆焊层中,由于成分偏析,夹杂等原因产生微小裂纹,并在运行中产生应力腐蚀或腐蚀疲劳裂纹并扩展,最终导致叶片断裂。     

GH2132三齿二级涡轮盘榫齿裂纹分析

对GH2132三齿二级涡轮盘在使用过程中第一榫齿产生的裂纹进行了光学金相和扫描电镜分析。结果表明，该裂纹属于高周疲劳裂纹，疲劳源区无冶金缺陷及加工刀痕。对失效件的化学成分、力学性能以及显微组织进行了检测，其结果均符合技术条件要求。疲劳裂纹产生的原因，是由于二级涡轮盘与二级涡轮叶片榫齿配匹不均匀，在发动机工作时，由于热应力作用，两种材料的线膨胀系数不一样(GH2132合金线膨胀系数大，而GH4037合金线膨胀系数小)，使之对盘的榫齿产生相当大的压应力，导致在榫齿配合面上产生了压陷，在交变载荷作用下，在离压陷边缘0．5mm处产生了疲劳裂纹。     

20CrNi2Mo钢齿轮磨削裂纹成因分析

采用宏观分析、化学成分分析、金相检验以及硬度测试等方法对某20CrNi2Mo钢制齿轮磨削裂纹产生原因进行了分析。结果表明:该齿轮磨削裂纹产生的主要原因是其渗碳区域存在严重的内氧化缺陷和魏氏渗碳体组织,降低了齿轮表层磨削面的残余压应力,增加了齿轮的磨削开裂敏感性,当磨削应力超过材料断裂强度时,便会产生磨削裂纹。     

地铁列车从动齿轮表面裂纹产生原因

采用磁粉检测、金相检验、硬度测试、化学成分分析等方法对地铁列车从动齿轮表面大量裂纹缺陷的产生原因进行了分析。结果表明：齿轮表面裂纹的性质为接触疲劳裂纹,早期开裂的原因是磨齿过程中齿面发生了磨削烧伤。     

活塞销失效原因分析

某发动机活塞销失效导致发动机损毁.采用磁粉探伤、宏微观断口分析、化学成分、金相组织及硬度分析等方法对失效的活塞销进行了分析,同时还对活塞销在服役过程中的应力状态进行了有限元模拟计算.结果表明,导致活塞销疲劳断裂的原因是活塞销端面存在磨削裂纹.     

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。     

48MnV非调质钢汽车发动机曲轴探伤磁痕现象分析及对疲劳性能的影响

对48MnV非调质钢汽车发动机曲轴探伤磁痕现象产生原因进行了分析,指出由于在锻造过程中原材料不均匀流变,造成原材料心部组织偏向连杆颈内侧部位,并在其后的机加工过程中心部组织外露,导致产生探伤磁痕现象。分析微观特征,结果证实其实质是心部碳偏析带在近表层的分布。分析了探伤磁痕现象对曲轴疲劳性能的影响,结果表明:对于按技术条件检验合格的原材料,曲轴出现的偏析现象不会成为疲劳裂纹优先萌生的条件,即偏析区与正常区域在零件受力中的行为没有明显差别,没有降低曲轴疲劳强度。     

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.     

离心叶轮叶片裂纹产生原因分析

某发动机离心叶轮叶片的排气边多处出现裂纹,通过理化检验和定量分析对裂纹产生原因进行了分析,并估算了叶片的裂纹扩展寿命及其占总寿命的百分比。结果表明:该裂纹为高低周复合疲劳裂纹,叶片在异常振动等大应力作用下产生了疲劳开裂。     

Investigation on the fatigue crack behavior of Zr702/TA2/Q345R composite plate with a crack normal to interface

In this paper, the effects of maximum load, load ratio, and average load on fatigue crack propagation of Zr702/TA2/Q345R composite plate with a crack normal to the interface are studied by experiment and finite element method. When crack propagates to the interface from the compliant material side, the crack growth rate decreases to the minimum at first. After crack penetrates through the interface, the fatigue crack growth rate accelerates continuously. When crack propagates to the interface from the stiff material side, the fatigue crack growth rate generally increases with the crack length. Regardless of the direction of crack growth, the increase of load ratio will weaken the difference of crack growth rate near the interface caused by material property mismatch. Finite element results show that elastic modulus mismatch significantly changes the variation of the stress intensity factor amplitude. All results demonstrate that crack growth rate is dependent on the competition of the stress intensity factor amplitude, the fatigue crack growth rate in the corresponding material, and the interface strength.     

Very-high-cycle fatigue crack initiation and propagation behaviours of magnesium alloy ZK60

The aim of this paper is to assess the very-high-cycle fatigue (VHCF) behaviour of a magnesium alloy (ZK60). Results indicate that the fatigue crack initiates from an area consisting of many distributed facets, while the region of early crack propagation is characterised by parallel traces, based on a fractographic analysis. The significant differences in morphology around the crack initiation area result from the interaction between the deformation twinning and the plastic zone at the crack tip. In addition, the fatigue crack propagation rate around the crack initiation site is also estimated based on a modified Murakami model. It is found that the formation stage for the fatigue crack is of great importance to the fatigue failure mechanism in the VHCF regime.     

Fatigue strength of small-notched specimens under variable amplitude loading within the fatigue limit diagram

Although the fatigue limit diagram is defined in principle for constant stress amplitude, it is often considered that fatigue failure would not occur, even in varying loading, if applied stresses were kept within the fatigue limit diagram. However, it was shown in the case of small‐notched specimens that fatigue failure occurred in some special cases of variable amplitude loading, even when all stress amplitudes were kept within the fatigue limit diagram. The cause of this phenomenon was examined using two‐step stress and repeated two‐step stress patterns in which the first step stress was chosen to be equal to the fatigue limit with zero mean stress and a mean stress was superposed on the second step stress. A non‐propagating crack was formed by the first step stress. This crack functioned as a pre‐crack for the second step stress with high mean stress. Consequently, fatigue failure occurred even when all stress amplitudes were kept within the fatigue limit diagram. It was an unexpected fracture caused by the interference effect of a non‐propagating crack and a mean stress change.     

Circumferential inner fatigue crack growth and penetration behaviour in pipe subjected to a bending moment

Surface defects in most pipe components under cyclic stress tend to be origins of fatigue crack growth, which may cause serious failure of the whole structure. An analysis of crack growth and penetration behaviour from these defects may therefore be one of the most important subjects on the reliability of the LBB (leak before break) design philosophy. However, studies on fatigue crack growth and COD (crack opening displacement) behaviour in a complex through-wall crack are relatively rare. To that purpose, a series of fatigue tests has been carried out at room temperature on carbon steel pipe which has an inner surface crack. Before crack penetration, leak-life, fatigue crack growth behaviour, e.g. aspect ratios and d a /d N versus Δ K were evaluated successfully by using a proposed plate model. After crack penetration, a new formula to evaluate K is proposed. For the complex crack created after through-wall penetration, fatigue life and fatigue crack growth behaviour were evaluated quantitatively by using the new formula and the model proposed in this study.     

TC6钛合金安装座荧光显示缺陷原因

某TC6钛合金安装座在航空发动机上试车后,拆机进行荧光检查,在该安装座圆弧处发现长度约4 mm的线性荧光显示。采用宏观观察、微观分析、金相检验、硬度测试、能谱分析等方法对荧光显示缺陷产生的原因进行了分析。结果表明:该安装座上的荧光显示缺陷为疲劳裂纹。安装座圆弧表面在人工砂轮打磨时完整性被破坏,形成了疲劳裂纹源,在试车过程中裂纹扩展,并与没有完全去除的锻造折叠裂纹相连接,最终形成了缺陷。     

渗注锆酸盐对AZ31镁合金疲劳裂纹扩展速率的影响

研究交变载荷作用下,在AZ31镁合金疲劳裂纹尖端渗注锆酸盐的沉积行为及其对疲劳裂纹扩展速率的影响。用扫描电镜(SEM)、能谱仪(EDS)及X射线衍射仪(XRD)观察分析裂纹尖端的形貌和物相成分,采取贴应变片方法确定渗注锆酸盐前后应力强度因子的变化。结果表明:锆酸盐转化液能在AZ31镁合金疲劳裂纹尖端形成锆酸盐ZrxOyZnxOy覆层;渗注锆酸盐后裂纹尖端应力强度因子降低约40%,能有效增强疲劳裂纹闭合效应,降低或延滞其疲劳裂纹扩展速率。     

Fatigue crack growth analysis of 2024 T3 aluminium specimens under aircraft service spectra

The fatigue crack growth behaviour of 2024 T3 aluminium was investigated experimentally. The fatigue experiments were performed under constant stress amplitude, constant amplitude with single and multiple overloads and aircraft service spectra. The fatigue spectra used correspond to the air-to-air, air-to-ground and instrumentation and navigation flight phases. They were applied for different stress levels. In total 11 different random flight service spectra were examined. The retardation effects caused by the overloads on the fatigue crack growth behaviour and the fatigue crack growth under aircraft service spectra were predicted using an in-house-developed code. The code makes use of the strip plastic zone approximation to account for material hardening effects along the path of prospective crack growth. Crack growth is treated incrementally and corresponds to failure of material elements ahead of an existing crack after a certain critical number of fatigue cycles. For the simulation of irregular service spectra by equivalent sequences of distinguished stress cycles a modified rainflow counting method is utilized. Spectrum simulation accounts also for non-linearity in fatigue damage accumulation and load sequence effects. The computed fatigue curves fit well with the experimental results.     

Investigation of small fatigue crack initiation and growth behaviour of nickel base superalloy GH4169

Surface replication method was utilized to monitor the small fatigue crack initiation and growth process of single‐edge‐notch tension specimens fabricated by nickel base superalloy GH4169. Three different stress levels were selected. Results showed that small fatigue cracks of nickel base superalloy GH4169 initiated from grain boundaries or surface inclusions. The small fatigue crack initiation and growth stages took up about 80–90% of the total fatigue life. Multiple major cracks were observed in the notch root, and specimen with more major cracks seemed to have smaller fatigue life under the same test conditions. At the early growth stage, small crack behaviour might be strongly influenced by microstructures; thus, the crack growth rates had high fluctuations. However, the stress level effect on the small fatigue crack growth rates was not distinguishable for the three different stress levels. And no clear differences were found among the crack initiation lives by using replication technique.     

A modification of UniGrow 2‐parameter driving force model for short fatigue crack growth

In this paper, a modification of the UniGrow model is proposed to predict total fatigue life with the presence of a short fatigue crack by incorporating short crack propagation into the UniGrow crack growth model. The UniGrow model is modified by 2 different methods, namely the “short crack stress intensity correction method” and the “short crack data‐fitting method” to estimate the total fatigue life including both short and long fatigue crack propagations. Predicted fatigue lives obtained from these 2 methods were compared with experimental data sets of 2024‐T3, 7075‐T56 aluminium alloys, and Ti‐6Al‐4V titanium alloy. Two proposed methods have shown good fatigue life predictions at relatively high maximum stresses; however, they provide conservative fatigue life predictions at lower stresses corresponding high cycle fatigue lives where short crack behaviour dominates total fatigue life at lower stress levels.     

Prediction of short fatigue crack growth of Ti‐6Al‐4V

It is observed that the short fatigue cracks grow faster than long fatigue cracks at the same nominal driving force and even grow at stress intensity factor range below the threshold value for long cracks in titanium alloy materials. The anomalous behaviours of short cracks have a great influence on the accurate fatigue life prediction of submersible pressure hulls. Based on the unified fatigue life prediction method developed in the authors' group, a modified model for short crack propagation is proposed in this paper. The elastic–plastic behaviour of short cracks in the vicinity of crack tips is considered in the modified model. The model shows that the rate of crack propagation for very short cracks is determined by the range of cyclic stress rather than the range of the stress intensity factor controlling the long crack propagation and the threshold stress intensity factor range of short fatigue cracks is a function of crack length. The proposed model is used to calculate short crack propagation rate of different titanium alloys. The short crack propagation rates of Ti‐6Al‐4V and its corresponding fatigue lives are predicted under different stress ratios and different stress levels. The model is validated by comparing model prediction results with the experimental data.