高超载比超载对Q345钢的疲劳性能的影响

采用Q345钢制作成紧凑拉伸试样,并在裂纹萌生后进行超载.通过疲劳裂纹扩展试验,研究高超载比超载对疲劳裂纹扩展速率的影响,分析其延寿机理.研究发现:较高的超载比使试样引入了残余压应力,使得有效应力强度因子降低至应力强度因子门槛值附近.可以降低疲劳裂纹扩展速率,抑制裂纹扩展,延长试样的疲劳寿命,通过此方法提高了含裂纹结构的使用寿命.     

压缩超载残余应力对疲劳裂纹扩展的影响

对对称双V型缺口试件的疲劳试验结果表明,压缩超载后,缺口试件的疲劳裂纹扩展速率增大,其原因是由于压缩超载后在缺口根部产生了反向残余拉应力。对此残余应力分布,本文采用了弹塑性有限元方法进行计算,并运用R′法定量分析了压缩超载残余应力对疲劳裂纹扩展的影响。     

疲劳载荷作用下裂纹扩展速率的研究

主要研究含裂纹构件在具有不同应力比与不同加载频率的疲劳载荷作用下裂纹扩展速率公式新的表现形式。运用新裂纹扩展速率公式,定量地计算出具有不同应力比与不同加载频率的疲劳载荷作用下线弹性裂纹的扩展速率。综合考虑了疲劳作用应力,裂纹尖端应力强度因子的变化幅值,总结出新裂纹扩展速率公式的适用范围,检验了新裂纹扩展速率公式的准确性和实用性。     

焊接残余应力对疲劳裂纹萌生和扩展的影响

通过疲劳试验,研究焊接残余应力对疲劳裂纹萌生和扩展性能的影响,以及残余应力的再分配。试验结果表明,垂直于裂纹方向的纵向残余应力促进孔边疲劳裂纹的萌生和扩展;残余应力随焊缝金属的应变松弛而降低,它对疲劳裂纹扩展速率的影响相应减小;残余应力场中疲劳裂纹扩展速率仍可以用Ｐａｒｉｓ ／公式计算。     

S38C车轴表层梯度材料的疲劳裂纹扩展性能研究*

为研究S38C车轴表层梯度材料的疲劳裂纹扩展性能,直接从现车车轴截取试样,保持实际车轴表层具有的显微组织、硬度及其残余应力呈梯度变化的情况,采用三点弯曲加载方法,检测疲劳裂纹在硬化层、过渡层和芯部基体的扩展性能。结果表明,随着表层裂纹长度的增加,疲劳裂纹扩展速率呈现先增加后减小最后增加的趋势。通过测量不同表层深度位置的残余应力分布,发现距车轴表面深度0～3 mm内存在较大的残余应力压应力,使得疲劳裂纹扩展需要更大的驱动力,而距车轴表面深度3 mm后转变为拉应力,对疲劳裂纹扩展没有影响。     

16Mn钢焊接件疲劳裂纹扩展特性研究

本文研究了16Mn 钢焊接接头疲劳裂纹扩展特性。结果表明:影响焊接接头裂纹扩展速率的因素是焊接接头的残余应力和金相显微组织。当应力比 R<0.6时,残余应力是影响焊接接头疲劳裂纹扩展速率的主要因素,显徽组织次之;当应力比达到0.6时,残余应力影响减弱。根据实验结果提出了焊接接头疲劳裂纹扩展速率的预测模型,与实测结果相近,具有一定的实用价值。     

焊接残余应力对高强钢点焊接头裂纹扩展及疲劳性能的影响

点焊接头因高度应力集中,极易于熔核边缘萌生疲劳裂纹,点焊产生的残余应力会影响其扩展。为探究点焊残余应力对疲劳裂纹扩展的影响规律,建立DP600高强钢点焊接头三维裂纹有限元仿真模型。基于热-弹塑性理论求解点焊残余应力场,在此基础上计算有无残余应力时折线裂纹的局部应力强度因子(Stress Intensity Factor, SIF)解,通过分析两种条件下裂纹最深点局部SIF随裂纹深度比变化的曲线,研究点焊残余应力对折线裂纹扩展的影响规律;基于断裂力学理论,采用改进的双参数模型预测有无残余应力时的疲劳寿命。结果表明,点焊残余应力使局部SIF显著提高,且随着裂纹深度比的增加,残余应力对其的影响程度也增加;考虑残余应力后裂纹整体扩展趋势不变但扩展速率显著增加,疲劳寿命由35 616次下降至12 564次。     

恒幅和单峰超载疲劳裂纹尖端区域残余应力场的数值模拟

采用弹塑性有限元方法,对恒幅及不同超载比的单峰超载作用下的裂纹扩展进行有限元模拟.通过模拟得到的裂纹扩展过程中裂尖塑性区及应力(残余应力)场分析产生裂纹闭合的原因以及对裂纹扩展的影响.结果表明,从残余应力角度分析裂纹扩展是可行的,为建立基于残余应力的裂纹扩展模型提供分析基础.     

残余应力对材料疲劳性能影响的某些进展

材料经表面形变强化可有效地提高材料的疲劳性能.以往主要研究形变强化工艺与零件疲劳寿命的关系.为进一步发挥材料强度潜力,近年来着重研究形变强化后残余应力、组织强化及表面光洁度等各因素对不同强度、不同缺口形状等材料的影响。本文从经典理论及断裂力学两方面结合所作的工作,介绍残余应力对材料疲劳性能影响研究的一些新进展。残余应力对疲劳极限的影响涉及如何选取残余应力值,残余应力对不同强度材料的作用,残余应力的多轴性,残余应力在缺口处的集中效应及其对缺口疲劳极限的影响等。断裂力学方法适用于分析裂纹在残余应力场中的扩展问题。研究表明残余应力不仅改变了载荷比,而且还使裂纹的闭台力发生变化,改变了有效应力强度因子范围及相应的裂纹扩展速率,它和残余应力导致的闭合力变化有较好的对应关系.     

残余应力对疲劳的影响

前言残余应力对疲劳的影响是长期以来人们十分关注的课题,因为人们逐渐认识到许多疲劳现象都与残余应力相关。例如疲劳裂纹的形成与扩展、少数极高应力、平均应力、加载次序、裂纹迟滞效应、缺口应力集中等都与残余应力有密切关系。残余应力是影响疲劳的一个重要因素。因此,弄清残余应力的大小和分布,以及残余应力与上述疲劳现象之间的关系,对于评价结构的疲劳强     

基于新裂纹扩展驱动力参量的焊接接头疲劳裂纹扩展的研究

传统上疲劳裂纹扩展速率以一个参量——应力强度因子幅(PARIS模型)或有效应力强度因子幅(ELBER模型)来表达。PARIS模型不能统计应力比效应和变幅加载历史。ELBER裂纹闭合模型虽被广泛应用,但确定其开闭口载荷的测量方法很多,且测量结果均存在主观性。最近研究表明,疲劳裂纹扩展不仅依赖于应力强度因子幅,还与最大应力强度因子有关。并且KUJAWSKI提出了两参量模型,该模型避开了有争议的裂纹闭合效应。基于一个载荷循环中柔度变化与裂纹尖端开闭口与弹塑性行为的关系,提出一个新的具有物理意义的两参量驱动力模型。针对Q345钢焊接接头各区域进行两种应力比R=0.1和0.5的疲劳裂纹扩展试验。使用该模型针对Q345钢焊接接头各区域的疲劳裂纹扩展数据进行验证。结果表明,提出的新模型在预测应力比对裂纹扩展速率的影响时比上述三个模型更有效。     

疲劳门槛值统一理论模型的比较及验证

针对应力比对疲劳裂纹扩展及门槛值的影响，依据裂纹闭合与裂纹扩展驱动力机制的统一思想，阐述了Zhu-Xuan模型与Kwofie-Zhu模型的建立过程，并基于25Cr2Ni2MoV转子钢焊接接头的疲劳裂纹扩展试验数据对模型进行验证。结果表明，两种模型在近门槛值区和Paris区均有良好的预测效果，其中Zhu-Xuan模型形式简单，对CrMoV钢具有普适性，预测门槛值的误差在10%以内，而Kwofie-Zhu模型预测结果更准确，但应用过程涉及参数求解，过程较复杂。研究认为，裂纹闭合与扩展驱动力机制的统一模型描述疲劳裂纹扩展行为的应力比相关性是合理可行的，且具有较好精度。     

含缺口结构压疲劳失效研究

结构的疲劳失效与内部的应力水平有着紧密的联系。这里阐述了压应力作用下结构内部裂纹的萌生和扩展机理，并介绍了循环压应力下的裂纹扩展计算方程，结合现代疲劳研究方法的新成果新方法对压应力条件下疲劳破坏研究的未来提出展望。     

激光冲击强化对TC4钛合金单面修饰激光焊接接头疲劳性能的影响

对TC4钛合金单面修饰激光焊接接头进行激光冲击强化,对比强化前后焊接接头的疲劳寿命,在光学显微镜和扫描电镜下观察断口疲劳断裂特征,并从焊接接头的显微硬度、微观组织、残余应力分布等方面综合分析激光冲击强化对TC4钛合金单面修饰激光焊接接头的强化机理。试验结果表明：未强化和强化试样均在焊缝咬边处萌生疲劳裂纹,强化试样疲劳寿命是未强化试样疲劳寿命的3.77~9.15倍,强化试样焊缝咬边处马氏体细化,显微硬度提高,焊缝表面呈残余压应力分布,焊缝咬边处残余压应力达-564.37±9.85MPa。晶粒细化和高幅值残余压应力综合作用下抑制了焊缝咬边处疲劳裂纹的萌生,且增大了裂纹扩展阻力,从而提高了焊接接头疲劳性能。     

The effects of laser peening and shot peening on fretting fatigue in Ti-6Al-4V coupons

This paper describes testing of Ti-6Al-4V coupons in fretting fatigue and compares the effects of mechanical surface treatments on performance. Fretting fatigue tests were performed using a proving ring for fretting load, bridge-type fretting pads, and applied tension-tension cyclic fatigue stress. As-machined (AM), shot peened (SP), and laser peened (LP) coupons were evaluated, and data generated to compare residual stress, surface condition, lifetime, and fractographic detail encountered for each. Near-surface residual stress in SP and LP coupons was similar. The layer of compressive residual stress was far deeper in LP coupons than in SP coupons and, consequently, subsurface tensile residual stress was significantly greater in LP coupons than in SP coupons. SP coupons exhibited a rough surface and had the greatest volume of fretting-induced wear. LP coupons exhibited a wavy surface and had a small volume of wear localized at wave peaks. SP coupons had the greatest fretting fatigue lifetime, with significant improvement over AM coupons. Lifetimes of LP coupons were similar to those for SP coupons at high fatigue stress, but fell between AM and SP coupons at lower fatigue stress. Fractographic evaluation showed that fractures of AM samples were preceded by initiation of fretting-induced cracks, transition of a lead fretting crack to mode-I fatigue crack growth, and crack growth to failure. SP and LP samples exhibited behavior similar to AM samples at high fatigue stress, but in coupons tested at low stress the lead crack initiated subsurface, near the measured depth of maximum tensile residual stress, despite the presence of fretting-induced cracks. The level of fatigue stress above which lead cracks were initiated by fretting was higher for LP than for SP, and was predicted with good accuracy using an analysis based on linear elastic fracture mechanics, the fatigue crack growth threshold stress intensity factor range, and superposition of measured residual stress and applied fatigue stress.     

Review on Stress Corrosion and Corrosion Fatigue Failure of Centrifugal Compressor Impeller

Corrosion failure,especially stress corrosion cracking and corrosion fatigue,is the main cause of centrifugal compressor impeller failure.And it is concealed and destructive.This paper summarizes the main theories of stress corrosion cracking and corrosion fatigue and its latest developments,and it also points out that existing stress corrosion cracking theories can be reduced to the anodic dissolution(AD),the hydrogen-induced cracking(HIC),and the combined AD and HIC mechanisms.The corrosion behavior and the mechanism of corrosion fatigue in the crack propagation stage are similar to stress corrosion cracking.The effects of stress ratio,loading frequency,and corrosive medium on the corrosion fatigue crack propagation rate are analyzed and summarized.The corrosion behavior and the mechanism of stress corrosion cracking and corrosion fatigue in corrosive environments,which contain sulfide,chlorides,and carbonate,are analyzed.The working environments of the centrifugal compressor impeller show the behavior and the mechanism of stress corrosion cracking and corrosion fatigue in different corrosive environments.The current research methods for centrifugal compressor impeller corrosion failure are analyzed.Physical analysis,numerical simulation,and the fluid-structure interaction method play an increasingly important role in the research on impeller deformation and stress distribution caused by the joint action of aerodynamic load and centrifugal load.     

Fatigue growth simulation for cracks in notched and unnotched round bars

Fatigue crack growth for various cracks in both unnotched and notched round bars is directly modelled by using an automated numerical technique, which calculates the stress intensity factors at a set of points on the crack front through the three-dimensional finite element method and then applies an appropriate fatigue crack growth law to this set of points to obtain a new crack front. This technique also has the capability of automatic remeshing so that the crack propagation can conveniently be followed. The crack geometries modelled in the present paper include a small internal crack near the free boundary and several initially part-elliptical or irregular surface cracks in a smooth round bar under tension, a surface crack in different semi-circularly notched bars under both tension and bending, a surface crack initiated from the root of a V-notched bar and an initially twin crack configuration within a smooth tension bar. Some fatigue growth characteristics relevant to each type of cracks are also revealed. It is demonstrated that the fatigue growth analyses of various cracks commonly occurring in bars can reliably be made by using the automated finite element technique proposed.     

高频谐振载荷作用下Ⅰ型疲劳裂纹尖端力学参数变化规律

为研究高频谐振式疲劳裂纹扩展试验中带有Ⅰ型预制裂纹的紧凑拉伸(CT)试件裂纹尖端力学参数的变化规律,利用动态有限元方法,采用ANSYS和MATLAB软件编写程序,计算了CT试件在高频恒幅正弦交变载荷作用下,在一个应力循环及裂纹扩展到不同长度时裂纹尖端区域的位移、应变场及裂纹尖端的应力强度因子,并分析了其变化规律。在计算裂纹尖端应力强度因子时,首先采用静态有限元方法和理论公式验证了有限元建模和计算的正确性,然后采用动态有限元方法研究了裂纹扩展过程中裂纹尖端应力强度因子的变化规律。最后进行了高频谐振式疲劳裂纹扩展试验,采用动态高精度应变仪测量了裂纹扩展到不同阶段时裂纹尖端点的应变,并对有限元计算结果进行了验证。研究结果表明：在稳态裂纹扩展阶段,高频谐振载荷作用下Ⅰ型疲劳裂纹尖端位移、应变及应力强度因子均为与载荷同一形式的交变量;随着裂纹的扩展,Ⅰ型疲劳裂纹尖端的位移、应变及应力强度因子幅不断增大;静态应力强度因子有限元计算值和理论值的误差为2.51%,裂纹尖端点应变有限元计算结果和试验结果最大误差为2.93% 。     

Numerical studies on crack growth in a steel tubular T-joint

The results of a numerical investigation on fatigue crack growth of an offshore tubular T-joint under the action of axial, in-plane and out-of-plane bending loads are presented in this paper. Extensive stress analysis has been carried out to determine the location of the hot spot stress along the brace—chord intersection for each load case. Semi-elliptical cracks with varying crack lengths and crack depths were introduced at the hot spot location by means of line spring elements for stress intensity factor evaluation. The line springs were properly constrained to prevent the problem of crack surface penetration. The stress intensity factors obtained are then used in a crack growth law for life estimation.