两级低-高加载下拉剪点焊试样的疲劳损伤研究

对拉剪点焊试样进行了两组不同载荷水平的两级低-高循环加载试验,得到随第一级载荷下循环数变化,点焊试样的剩余寿命和总疲劳寿命变化规律。使用Miner线性累积损伤理论计算得到两种不同载荷水平下试样总的疲劳损伤。结果表明:对于低-高加载,随着低载水平下循环数的增多,高载荷水平下的剩余寿命以及损伤值呈逐渐减小趋势,总疲劳寿命逐渐增大。当低载水平载荷幅值较小时,点焊试样破坏时的累计损伤值普遍存在小于1的现象,且这种现象可能对疲劳寿命估算存在一定的影响。     

基于固有频率变化和载荷特性的点焊疲劳寿命预测

基于疲劳试验和动态响应试验,对单点拉剪点焊试件在恒幅、变幅和随机疲劳过程中的固有频率变化特性进行了研究.通过恒幅、变幅疲劳损伤过程中的频率响应函数曲线和各阶模态固有频率的比较,提出以载荷和频率变化率作为描述点焊疲劳损伤的特征参量,并利用剩余寿命比,建立了频率变化率与参量的线性关系,并以此关系描述随机载荷的疲劳过程.根据加载载荷、频率变化率和当前循环数来预测寿命,适用于载荷谱已知,固有频率可测情况下的疲劳寿命预测,预测值与试验值吻合较好.     

ST12汽车钢板拉剪点焊接头的疲劳强度

针对车身使用的ST12低碳钢板,利用生产线上焊接设备制备了电阻点焊接头拉剪疲劳试件.对点焊接头区域进行了金相组织观测,测量了焊点附近的维氏硬度值分布.在MTS材料疲劳试验机上进行了恒幅疲劳加载,得到了ST12低碳钢板的电阻点焊接头的S-N曲线.基于所得的S-N曲线进行了两级疲劳加载试验,对两级加载下的线性累积疲劳损伤进行了分析.累积损伤结果分析表明,ST12低碳钢板电阻点焊件在两级加载下存在加载次序效应,高-低加载次序下加载次序效应更为明显.     

基于累积损伤理论的ST12钢T型点焊件寿命研究

对低碳钢T型撕裂拉伸点焊试件分别进行低-高和高-低两级加载疲劳试验,并利用线性和非线性疲劳累积损伤理论进行寿命预测。对于低-高加载,非线性预测结果较线性稍好一些;对于高-低加载,由于高载下的"过载效应",线性预测结果与非线性预测结果都不太理想。针对高-低加载下的寿命预测误差,本文提出一种基于CHABOCHE修正模型的非线性疲劳累积损伤模型,分别考虑了两级应力幅以及疲劳塑性指数的影响。通过对比后发现,修正后的模型预测点焊寿命能力较原模型有所改善。     

两级加载下拉剪点焊试件的疲劳累积损伤

对单点点焊试样进行恒幅和两级低-高、高-低加载试验,采用最小二乘法得出恒幅加载条件下的S-N曲线拟合方程。同时由试验数据得出低-高、高-低加载与总寿命有一定的对应关系,可很好地表述低载"锻炼效应"和高-低加载下高应力下裂纹易于形成,致使后继的低应力能使裂纹扩展的效应。对于加载次序对累积损伤的影响,需要把试件的疲劳断裂过程分为裂纹形成和裂纹扩展两个阶段。在裂纹形成阶段,可用疲劳裂纹的超载效应因子予以定量表征。裂纹扩展阶段在考虑载荷次序效应的条件下,必须考虑过载迟滞效应和低载导致裂纹扩展加速的效应。而由曼森和哈尔福德提出的双线性累积损伤准则正好与此对应。     

两级加载下两焊点拉剪点焊接头的损伤

对带有两个焊点的拉剪点焊试样进行了两级变幅疲劳加载,应力幅和平均应力均不相等.结果表明,两级变幅加载下存在应力次序效应.在低—高加载时存在"锻炼效应",线性累积损伤的值大于1;在高—低加载时存在"过载效应",高—低加载下的线性累积损伤值也大于1.在高—低加载方式下,高水平应力作用后,低水平应力剩余疲劳寿命大于按线性疲劳累积损伤法则所估算的剩余寿命,低应力作用下的剩余寿命甚至大于低应力单独作用下的全寿命.高—低加载下的线性累积损伤结果表明,焊点边缘更象是一个缺口.     

TC4钛合金的多轴高周疲劳损伤及强度退化研究

不同工况下TC4(Ti-6Al-4V)钛合金疲劳累积损伤及强度退化存在较大差别。为了充分表征载荷参数的影响,基于Chaboche损伤模型以及改进的多轴疲劳损伤准则,提出新的强度退化模型,开展了TC4钛合金的多轴高周疲劳(HCF)寿命预测和强度退化评估。首先,开展TC4合金在一系列加载路径下的多轴比例和非比例疲劳试验。将Chaboche非线性损伤准则和临界平面法与提出的损伤控制参数相结合,描述了TC4合金的非线性疲劳损伤计算和寿命预测。其次,进一步建立了基于累积损伤的非线性强度退化模型,并证明了该模型在不同载荷工况下均可以获得更高的精度。实验结果表明,由于考虑载荷参数的影响,提出的TC4钛合金疲劳寿命与强度退化预测结果精度远高于其他的预测模型。     

超声频分量双周疲劳载荷作用下焊接接头疲劳行为

使用带超声频载荷分量的双周疲劳试验装置对Q345钢焊接接头分别进行纯低周、纯高周以及双周循环加载条件下的疲劳试验.应力比R为O.5,高周载荷频率约19 kHz.结果表明,叠加于大幅低周循环载荷上的小幅高周循环载荷及叠加于大幅高周循环载荷上的小幅低周循环载荷都能够对焊接接头造成严重的疲劳损伤.通过按外包络线表征双周疲劳强度,如果疲劳寿命使用低周载荷循环周次表征,低估了高周载荷分量对焊接接头造成的损伤;如果疲劳寿命使用高周载荷循环周次表征,又高估了低周载荷分量对焊接接头造成的损伤.     

基于非线性连续损伤的机床轴结构疲劳研究

运用MINER线性累积损伤理论对机床轴结构进行疲劳研究时,由于不能连续描述损伤与载荷之间的关系,在高周疲劳寿命预测过程中其计算结果不能令人满意。为此,基于CHABOCHE提出的单轴非线性连续累积损伤理论,通过对45钢进行疲劳试验获得了轴结构材料的S-N曲线,在对机床载荷谱简化处理的基础上,建立了适于机床轴结构寿命预测的多轴非线性连续损伤累积模型。实例计算证明,该模型能准确描述机床轴结构损伤累积过程,计算结果更符合工程实际。     

电阻法检测金属构件损伤及预测疲劳寿命

基于非线性连续疲劳损伤理论,考虑应力幅带来的非线性累积效应,以电阻值定义金属构件损伤参量,提出基于电阻变化的金属高周疲劳损伤累积模型及疲劳载荷应力幅对损伤参量的影响函数,给出通过测量电阻来检测金属构件疲劳损伤状态的方法及预测高周疲劳剩余寿命的理论公式,并通过45号钢高周疲劳试验进行验证。     

CuW80铜钨合金疲劳损伤过程的研究

借助扫描电镜研究了CuW80铜钨合金电触头材料在循环载荷作用下微观组织的变化过程,用系统分析的方法定义CuW80铜钨合金疲劳损伤参数,并对其三点弯曲疲劳损伤过程进行了定量跟踪分析.试验结果表明,CuW80铜钨合金疲劳的损伤过程可以分为三个阶段,具有双线性损伤过程的特征,分别对应于疲劳裂纹萌生阶段(EF)和扩展过程(FH)两个线性阶段,且分别占疲劳总寿命的60%和33%;在循环载荷作用下CuW80铜钨合金的疲劳裂纹主要萌生于铜钨合金铜相的晶体内,而非发生于铜、钨界面,并且疲劳裂纹在铜相晶体内不断扩展直至断裂.     

MULTIAXIAL CREEP-FATIGUE LIFE EVALUATION UNDER PROPORTIONAL LOADING

A new method was proposed for the multiaxial creep-fatigue life evaluation under proportional loadings. Because this method was derived from the strain range partitioning method with a multiaxiality factor, it was possible to consider the influence of both creep-fatigue interaction and multiaxial stress state on fatigue life. In order to predict the combined axial-torsional fatigue life the damage under combined loading was defined as linear summation of the damages under axial loading and torsional loading. Axial-torsional creep-fatigue tests were carried out using tubular specimens of 316LC austenitic stainless steel and the ferritic rotor steel. This rotor steel was developed for the permanent magnet type eddy current retarder in heavy trucks. Experimentally obtained lives of both steels were well corresponded with the lives predicted by the proposed method. It was found that the proposed method was effective in multiaxial fatigue life evaluation under proportional creep-fatigue Ioadings.     

Fatigue behavior of aluminum stiffened plate subjected to random vibration loading

Vibration tests were carried out on three types of stiffened aluminum plates with fully clamped boundaries under random base excitation. During the test, the response of the specimens was monitored using strain gauges. Based on the strain history, the accumulation of fatigue damage of the stiffened plates was estimated by means of the rainflow cycle counting technique and the Miner linear damage accumulation model in the time domain. Utilizing the change of natural frequencies, a nonlinear model was fitted for predicting the fatigue damage of plate and then the foregone failure criterion of 5% reduction in natural frequency is improved. The influence of section and spacing of the stiffeners on the vibration fatigue behavior of the aluminum plate was investigated. The results show that the fatigue life of aluminum plate increases with adding either T or L section riveted stiffeners. With the same cross-sectional area of stiffener, the T section stiffened plate shows longer fatigue life than L section stiffened plate. Meanwhile, the vibration fatigue life also shows great sensitivity to the spacing between the stiffeners.     

A CUMULATIVE FATIGUE DAMAGE RULE UNDER THE ALTERNATIVE OF CORROSION OR CYCLIC LOADING

Fatigue damage increases with the applied loading cycles in a cumulative manner and the material deteriorates with the corrosion time. A cumulative fatigue damage rule under the alternative of corrosion or cyclic loading was proposed. The specimens of aluminum alloy LY12-CZ soaked in corrosive liquid for different times were tested under the constant amplitude cyclic loading to obtain S-N curves. The test was carried out to verify the proposed cumulative fatigue damage rule under the different combinations among corrosion time, loading level, and the cycle numbers. It was shown that the predicted residual fatigue lives showed a good agreement with the experimental results and the proposed rule was simple and can be easily adopted.     

Fatigue-life prediction of SiC aluminum composite using a Weibull model

The feasibility of the acoustic emission technique in predicting the residual fatigue life of 6061-T6 aluminum matrix composite reinforced with 15 vol.% SiC particulates (SiC_p) is presented. Fatigue damages corresponding to 40, 60 and 80% of total fatigue life were induced at a cyclic stress amplitude. The specimens with and without fatigue damage were subjected to tensile tests. The acoustic emission activities were monitored during tensile tests. The number of cumulative AE events increased exponentially with the increase in strain during tensile tests. This exponential increase occurred when the material was in the plastic regime and was attributed mainly to SiC particulate/matrix interface decohesion. Cumulative events during post fatigue tensile tests reduced with a decrease in the residual fatigue life. Based on the high cycle fatigue damage accumulation model, a Weibull probability distribution model is developed to explain the post fatigue AE activity of specimens during tensile tests. Using the model, the residual fatigue life can be predicted by testing the specimen in tension and monitoring the AE events. In high cycle fatigue, it was observed that the residual tensile strengths of the material did not change significantly with prior cyclic loading damages since the high cycle fatigue life was dominated by the crack initiation phase.     

基于红外热像法的AZ31B镁合金疲劳寿命预测

采用红外热像法测量AZ31B镁合金板材在疲劳过程中表面温度场的变化,结果表明,当疲劳载荷大于疲劳强度时,镁合金试样表面的温度变化经历5个阶段:温度上升阶段、温度下降阶段、稳定阶段、断裂前的温升阶段和断裂后温度下降阶段。通过疲劳过程中镁合金试样表面的温度变化规律,基于不同的理论提出了2种预测疲劳寿命的方法:由试验过程中试样表面温升(?TM)特征确定其疲劳寿命,?TM–Nf曲线拟合结果表明,?TM=3.89℃为温升极限值,即?TM>3.89℃时,试样会发生断裂,与实测疲劳试样的温升值(3.68℃)相比,误差为5.7%;利用能量法提出了镁合金疲劳寿命的计算公式,用能量法和传统试验方法分别绘制S-N曲线,结果具有很好的一致性,用2种方法分别计算了循环次数为1×107时的疲劳强度ΔσeΦ=99.3 MPa、ΔσeSN=99.8 MPa,误差为0.5%。采用红外热像法估算疲劳寿命具有简单、省时等优势。     

Influence of weld geometry and process on fatigue crack growth characteristics of AISI 304L cruciform joints containing lack of penetration defects

Abstract

The influence of weld geometry in conjunction with the gas tungsten arc welding (GTAW) and gas metal arc welding (GMAW) processes on fatigue properties of AISI 304L load carrying transverse fillet welded cruciform joints, containing lack of penetration (LOP) defects, has been studied. The fatigue lives of the joints were evaluated using conventional S -N (stress - number of cycles to failure) and fracture mechanics methods. The fatigue lives were calculated according to the two stage approach in which both the fatigue crack initiation and the crack propagation phases were considered. Constant amplitude fatigue experiments with stress ratio R=0 were carried out using a 100 kN servohydraulic Dartec universal testing machine at a frequency of 30 Hz. An automatic crack monitoring system based on crack propagation gauges was used to obtain the crack initiation and propagation data during the fatigue process. The predicted life was compared with the experimental values. It was found that the fatigue lives of the joints fabricated via GTAW were longer than those of the corresponding GMAW joints. It was also observed that the fillet geometry plays a major role in determining the failure mode and life. Test results have been compared with the BS 5400 design curve.