动载滑动轴承疲劳失效过程研究

研究了动载滑动轴承疲劳失效过程,观察到轴瓦表面裂纹、第二相裂纹等类型。通过润滑计算得到轴心轨迹、油膜压力和合金层应力分布,对轴瓦失效过程进行了分析,结果表明,轴怕疲劳裂纹由轴瓦宏观应力分布和微观应力集中共同作用,当基体与第二相的Ｅ、μ相关工不多时,应力集中不明显,当基体与第二相的Ｅ、μ相差较多时,应力集中产生的影响不可忽略。     

摩擦损耗对发动机连杆轴瓦寿命的影响

采用线性力学的方法对发动机连杆轴瓦摩擦损耗导致的疲劳破坏失效问题进行了研究,对微裂纹形成的原因进行了分析,经过试验证明可以通过降低摩擦损耗区内的单位分布能量,以及提高材料抗生成、扩展初始微裂纹的能力的方法来提高连杆轴瓦的使用寿命。     

C1001B空压机可倾瓦轴承疲劳寿命分析

通过疲劳寿命计算得出三级轴瓦的疲劳寿命，对比三级轴瓦实际的失效周期，说明失效的轴瓦上的可见裂纹不是由疲劳引起的，而是由于轴与轴瓦发生干摩擦所导致的。     

非金属夹杂物对AlSn20内燃机轴瓦疲劳磨损强度影响的研究

本文提出了在轴瓦材料熔铸过程中使用不同的精炼剂,会影响轴瓦中非金属夹杂物的含量,而非金属夹杂物的存在影响轴瓦的疲劳寿命.试验结果表明使用Zncl(?)精炼剂较之其他种类精炼剂,可使轴瓦中非金属夹杂物对轴瓦的疲劳寿命影响较小.图7表3参4     

20CrMnTi齿轮钢疲劳裂纹扩展试验与数值模拟研究

为了研究20CrMnTi齿轮钢的疲劳裂纹扩展问题,首先,将材料20CrMnTi制成紧凑拉伸试样,在疲劳拉伸试验机上进行载荷比R=0.3的疲劳裂纹扩展试验;然后,应用数值模拟软件Abaqus对疲劳裂纹扩展过程进行数值模拟.结果表明,数值模拟结果和试验结果具有相同的变化趋势,二者的差别在误差允许范围内;数值模拟方法能够很好地描述紧凑拉伸试样疲劳裂纹扩展过程.为20CrMnTi齿轮钢疲劳裂纹扩展过程及疲劳寿命的研究提供了一种有效的试验和模拟分析方法.     

疲劳短裂纹形成和扩展的划分定义探讨

根据对疲劳短裂纹生长行为的分析,将疲劳短裂纹形成和扩展过程划分为微观结构显著影响阶段和稳定生长阶段。综合考虑力学和材料两方面因素,给出了如下划分定义：疲劳短裂纹形成阶段为微观结构显著影响阶段;疲劳短裂纹扩展阶段为稳定生长阶段。通过有关文献分析并结合本试验观察,确定了疲劳短裂纹形成和扩展划分的临界裂纹长度为平均晶粒尺寸的５倍。     

考虑过载效应的金属材料疲劳裂纹扩展试验数据拟合及疲劳裂纹扩展速度计算方法研究

提出一种拟合金属材料疲劳裂纹扩展试验数据,并计算疲劳裂纹扩展速度的通用方法。该方法采用递增的三次多项式函数拟合疲劳试验数据,并采用平均加权方式计算各局部函数拟合的结果,提高了试验数据的拟合精度和疲劳裂纹扩展速度的准确性。通过在疲劳裂纹长度和扩展速度拟合结果的加权计算过程中引入delta函数,该通用方法能够有效地拟合常幅和存在过载载荷的疲劳裂纹扩展试验数据,并计算各试验点的裂纹扩展速度,同时保证了三次多项式拟合过程的连续性。通过多组常幅和存在过载载荷的疲劳试验数据拟合和现有方法及扩展有限元预测结果的对比分析,验证了该通用方法的有效性。     

直齿轮弯曲疲劳裂纹的扩展行为预测与分析

以渐开线圆柱齿轮为研究对象,在其齿根部存在初始裂纹的前提下,研究齿根疲劳裂纹扩展特性及其寿命;将齿轮啮合过程的动力学计算等效为多个啮合位置的静力分析,得到不同位置的应力强度因子;根据线弹性断裂力学,将裂纹扩展过程线性等效,以K判据分析裂纹是否发生扩展,根据Paris准则计算裂纹扩展量,采用最大周向应力准则确定裂纹扩展角度,得到整个计算周期的应力强度因子、疲劳裂纹扩展路径及疲劳寿命;采用高频试验台对齿轮进行疲劳试验,得到齿轮的疲劳扩展路径,与有限元计算结果进行对比验证;最后分别分析了初始裂纹的尺度、位置和载荷的不同对疲劳裂纹的扩展及疲劳寿命的影响。     

基于图像处理的疲劳裂纹扩展长度在线测量方法

为了在金属疲劳裂纹扩展试验中采用直观、准确、可靠的方法获得高精度裂纹长度尺寸,提出了基于图像处理技术的疲劳裂纹扩展长度在线测量方法。首先,采用大尺寸黑白全帧面阵CCD和微距显微镜头对疲劳裂纹扩展过程中的图像进行采集,分析疲劳裂纹的图像形态特征,采用亚像素边缘定位方法对预制裂纹边缘进行检测,求出疲劳裂纹起点位置。然后,对裂纹扩展区域进行图像子区划分,对图像子区采用基于灰度统计数据的自适应分割方法进行裂纹分割,采用单区域增长算法进行二值化裂纹图像连接得到裂纹主干。最后,进行了系统标定和疲劳裂纹长度在线测量试验。试验结果表明：本方法测量精度高、抗干扰能力强、数据稳定可靠,裂纹长度测量精度为0.03mm,满足裂纹扩展试验国际标准的要求。     

汽车后桥疲劳试验时裂纹扩展与应变变化的试验研究

在汽车后桥疲劳试验时监测记录了应变的变化过程,并测得了疲劳裂纹扩展的长度。通过分析研究,得到裂纹扩展与应变变化的关系,提出一种应用计算机实时监测应变变化来分析疲劳裂纹产生、扩展的方法。     

Sub-surface damage investigation by high frequency ultrasonic echography on 100Cr6 bearing steel

This paper presents an original ultrasonic technique devoted to the early detection of sub-surface fatigue cracks in 100Cr6 bearing steels. Echographic experiments were carried out during interrupted rolling contact fatigue tests. Crack initiation and crack propagation stages were both investigated. Quantitative measurements of sub-surface crack position, depth and angle with respect to the bearing surface are presented. Experimental results are analysed and discussed in relation to rolling contact fatigue theories. Contrary to what is generally accepted the presented results show that the crack propagation stage could represent an important part of bearing life.     

轮毂轴承单元凸缘的旋转疲劳强度试验

为考察第2代、第3代汽车轮毂轴承单元凸缘的疲劳强度,引入基于旋转弯曲和共振条件的疲劳强度试验方法。以A车型的第3代汽车轮毂轴承为例,根据迈因纳线性损伤理论对该轴承进行了仿真分析,并且使用SO33旋转疲劳共振试验机对该车型的第3代汽车轮毂轴承进行了试验,结果表明该试验方法准确可靠。     

轧机油膜轴承锥套接触疲劳损伤的机理分析

研究了油膜轴承锥套与辊颈接触表面在轧制载荷作用下发生微动疲劳损伤的力学机理。在分析油膜轴承油膜压力分布特征的基础上,采用有限元法给出了锥套与辊颈接触区边缘产生接触应力集中和微滑移的分布规律,阐明了弹性结合连接的锥套与辊颈接触表面产生微动疲劳损伤的原因。利用断裂力学裂纹尖端应力场与接触边缘区域应力局部渐近场的等效原则,给出了疲劳裂纹自点蚀处萌生与扩展的力学条件。上述结果为锥套和辊颈的实际损伤状态及模拟试验所验证。     

基于Lamb波的平尾大轴裂纹扩展监测

平尾大轴作为在役飞机的主承力构件,其轴内变厚度截面处存在应力集中现象,是疲劳断裂高发的关键部位。针对平尾大轴变截面处裂纹损伤,研究其基于主动Lamb波的裂纹深度在线监测方法。首先,通过线切割制造真实损伤,对压电传感器采集的监测信号进行Shannon连续复数小波变换,去噪提取Lamb波信号;其次,重点研究了不同模式Lamb波的4种损伤因子对大轴裂纹深度的表征能力,结果表明,基于A_0模式的互相关损伤因子对裂纹深度的表征效果最佳;最后,利用A_0模式的互相关损伤因子实现了平尾大轴裂纹萌生及裂纹尺寸的定量化监测,为平尾大轴的在线监测提供了方法基础。     

某型飞机机翼Ⅱ梁框疲劳寿命研究

某型飞机机翼Ⅱ梁框是重要的受力部件,必须准确估计疲劳寿命,以预防疲劳事故的发生。采用名义应力法和局部应变法两种方法及Miner累积损伤理论估计疲劳裂纹形成寿命;在随机载荷谱转化为等幅载荷谱的基础上通过Walker方程求得疲劳裂纹扩展寿命,从而估算出某型飞机机翼Ⅱ梁框的疲劳寿命。估算结果与试验结果吻合很好。     

热处理参数对高碳钢低周疲劳裂纹扩展行为的影响

研究了高碳钢（1.0%C碳工钢;1.0%C,1.5%Cr轴承钢）经不同热处理后的疲劳裂纹扩展行为。试验结果表明：1.淬火温度、回火温度、疲劳裂纹扩展机制、二次碳化物尺寸、试样的淬硬深度等因素,均影响疲劳裂纹扩展速率da/dN。2.疲劳裂纹的扩展临界长度a c,仅受回火温度的影响。其它因素对a c值无可见的影响。3.高温淬火并低温回火后,疲劳裂纹沿原奥氏体晶界扩展。     

Effects of compressive stresses on torsional fatigue

Rolling contact fatigue (RCF) is the dominant failure mode in properly installed and maintained ball and roller element bearings. Lundberg and Palmgren in their seminal publication indicated that this failure is due to the alternating component of shear stress. Thus, torsional fatigue experiments have been used to predict the RCF behavior of bearing materials. In non-conformal contacts, due to Hertzian pressure the contact experiences large compressive stresses. Hence, it is critical to take into account the effect of these large compressive stresses in torsional fatigue to better simulate RCF conditions. This paper presents an investigation of torsional fatigue of bearing steels, while the effects of combined compressive stress and its relevance to material behavior in rolling contact fatigue is examined. An MTS test rig was used to investigate the fatigue life of several bearing steels and their failure mechanisms were evaluated through fractography. Then the effects of compressive stresses on torsional fatigue were investigated. A set of custom designed clamp fixtures were designed, developed and used to apply Hertzian pressures of up to 2.5 GPa on the torsion specimens. The experimental results indicate that at high cycle fatigue, a combination of shear and biaxial compression, by application of Hertzian contact, is more detrimental to fatigue life than shear alone; however, as expected it has little to negligible effects in the low cycle fatigue regime. Also the failure mode changes such that fracture planes form a cup and cone pair with multiple internal cracks as opposed to helical planes observed in pure torsion which are formed by a single crack. A 3D finite element model (using ABAQUS) was developed to investigate the fatigue damage accumulation, crack initiation, and propagation in the material. The topology of steel microstructure is modeled employing a randomly generated Voronoi tessellation wherein each Voronoi cell represents a material grain and the boundaries between the cells are assumed to represent the weak plane in the steel matrix. Continuum damage mechanics (CDM) was used to model material degradation during the fatigue process. A comprehensive damage evolution equation is developed to account for the effect of mean stress on fatigue. The model predicts the fatigue lives and crack patterns successfully both in presence and absence of compressive stresses.     

超声疲劳裂纹扩展与摩擦生热研究

在高频循环载荷作用下,材料疲劳裂纹的萌生与扩展过程伴随着明显的温度变化,该温度变化反映材料内部结构的损伤特征。通过20 kHz的超声疲劳试验,研究一种碳锰钢在超高周疲劳加载条件下的内部疲劳裂纹萌生与扩展过程中温度的演化过程。通过对该材料在疲劳损伤过程中,内部裂纹间的摩擦生热机理分析,从微观角度出发,结合分形理论,建立内部裂纹微观结构的摩擦模型,数值模拟超声疲劳过程中材料内部疲劳裂纹面间的摩擦生热情况,并定量地计算该过程中由裂纹间摩擦所导致的温度上升,将模拟结果与试验结果进行比较。探究高频疲劳载荷下微裂纹扩展与摩擦生热的关系,并结合超高周疲劳裂纹扩展公式,建立超声疲劳过程中的裂纹扩展与裂纹面温度演化关系的模型。     

DIAGNOSTICS OF FATIGUE CRACK IN ULTERIOR PLACES OF LARGER-SCALE OVERLOADED SUPPORTING SHAFT BASED ON TIME SERIES AND NEURAL NETWORKS

To improve the diagnosis accuracy and self-adaptability of fatigue crack in ulterior place of the supporting shaft, time series and neural network are attempted to be applied in research on diag-nosing the fatigue crack’s degree based on analyzing the vibration characteristics of the supporting shaft. By analyzing the characteristic parameter which is easy to be detected from the supporting shaft’s exterior, the time series model parameter which is hypersensitive to the situation of fatigue crack in ulterior place of the supporting shaft is the target input of neural network, and the fatigue crack’s degree value of supporting shaft is the output. The BP network model can be built and net-work can be trained after the structural parameters of network are selected. Furthermore, choosing the other two different group data can test the network. The test result will verify the validity of the BP network model. The result of experiment shows that the method of time series and neural network are effective to diagnose the occurrence and the development of the fatigue crack’s degree in ulterior place of the supporting shaft.     

A Critique of Rolling Contact Fatigue Criteria for Bearing Rings with Hoop Stresses

Tensile residual and interference fit stresses not treated in classical bearing formulations are known to reduce bearing rolling contact fatigue (RCF) life. Recent modifications of such theory to account for these stresses have simply included them in the computation of a single yield stress type criterion—either maximum shear or equivalent stress. An alternative modification is proposed and demonstrated for fatigue crack initiation that recognizes the primary influence of the maximum range of shear stress but includes the effect of normal stress on the critical planes, as in other successful bulk fatigue criteria for multiaxial nonproportional stress cycle fatigue.