一种悬臂弯曲加载表面裂纹扩展试样及其应用

介绍了一种带有上下对称圆弧的板状试样,试样上圆弧几何中心预制有半椭圆表面裂纹,这种设计能够较好地模拟压力容器具有表面裂纹时的特点.利用这种试样,可以完成悬臂弯曲加载恒总应变控制下的低周疲劳表面裂纹扩展速率试验,获得表面裂纹扩展长度和深度的关系,最终建立表面和深度裂纹扩展速率与总应变的函数关系.据此,可为含有表面裂纹体的压力容器低周疲劳剩余使用寿命评估提供依据.     

表面压应力对10Ni5CrMoV钢疲劳性能的影响

分别采用精磨和冲击加工在IONi5CrMoV钢试样表面形成不同的残余压应力,对具有不同表面压应力的试样进行高周和低周疲劳试验,采用扫描电子显微镜对疲劳断口进行分析,并测试经不同周次高应变幅循环加载后的试样表面应力。结果表明,较高的表面压应力能有效抑制小应力幅下疲劳裂纹在表面的起裂,从而有效的提高了高周疲劳性能;在高应变幅作用下,初始的表面压应力迅速发生松弛而失去对疲劳裂纹在表面起裂的抑制作用,因而对低周疲劳性能无明显影响。     

高炉煤气透平动叶片裂纹分析

在对高炉煤气余压透平发电机转子动叶片进行表面渗透探伤时,发现Ⅰ级动叶片组中有6片叶片的叶榫部有裂纹.为探明裂纹的形成原因,对叶榫裂纹进行了化学成分、高、低倍组织及断口的宏、微观分析.分析结果表明,叶榫第一齿根裂纹属于疲劳裂纹.疲劳裂纹形成的原因主要与齿根底部过渡圆弧类似于直角、圆弧底部的加工条痕比较粗糙、显微组织粗大不均匀、铁素体条带分布不合理以及楔块装配面接触不良等因素有关.     

低周疲劳表面裂纹演化进程分析

低周疲劳表面裂纹演化可能具有非线性动力学特征。对 1Cr18Ni9Ti光滑试样进行了低周疲劳实验 ,在对裂纹进行分类的基础上 ,将裂纹演化划分为多裂纹相互作用和局域主裂纹控制两个阶段。从非线性动力学角度给出了短裂纹的新的定义。指出裂纹演化两个阶段对材料疲劳损伤破坏过程的贡献。     

低周疲劳表面裂纹演化进程分析

低周疲劳表面裂纹演化可能具有非线性动力学特征。对１Ｃｒ１８Ｎｉ９Ｔｉ光滑试样进行了低周疲劳实验，在对裂纹进行分类的基础上，将裂纹演化划分为多裂纹相互作用和局域主裂纹控制两个阶段。从非线性动力学角度给出了短裂纹的新的定义。指出裂纹演化两个阶段对材料疲劳损伤破坏过程的贡献。     

几种潜艇耐压壳体用钢的低周疲劳性能研究

本文叙述了作者及其合作者在潜艇耐压壳体钢低周疲劳性能研究工作中取得的进展,重点介绍了光滑板状弯曲试样的低周疲劳性能和板状弯曲加载条件下的表面裂纹扩展行为,讨论了表面裂纹扩展速率与总应变范围的关系和与塑性应变范围的关系。通过对弯曲低周疲劳表面裂纹扩展特征的研究,确立了低周疲劳表面裂纹扩展试验程序。并且通过对三种潜艇耐压壳体钢进行的表面裂纹扩展速率测定,获得了d(2c)/dN=A(ΔεT)~n的定量关系(ΔεT为总应变范围)。文中示出的低周疲劳曲线和d(2c)/dN-ΔεT曲线,可供材料研究、潜艇结构设计工作者使用。     

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...     

低周疲劳下16MnR微孔的裂纹萌生与扩展

采用宏观与微观结合的方法,在疲劳试验机上进行疲劳试验,在光学显微下观察裂纹的起裂与扩展.研究了压力容器用钢16MnR在低周疲劳下微孔(40～200μm)的裂纹萌生与扩展规律.研究表明裂纹的萌生机制:滑移带启裂和疏松带启裂,前者由剪应力起主要作用,后者由正应力起主要作用.而滑移带的局部性和裂纹开叉是低周疲劳下微裂纹的两大典型现象.微观缺陷尺寸、应力水平对疲劳寿命有显著影响,当应力水平较低时,微孔尺寸对寿命的影响明显.而当应力水平较高时(超过屈服极限),孔径对寿命的影响不敏感.在同一应力水平下,微缺陷尺寸存在临界值dt,当d＞dt时,疲劳寿命下降很多.     

4.5Ni钢表面裂纹的低周疲劳扩展行为研究

采用悬臂弯曲加载方式，以总应变范围作为受检和控制参数，分析了高强度４．５Ｎｉ钢表面裂纹的低周疲劳扩展行为，给出了裂纹扩展速率ｄ（２ａ）／ｄＮ与总应变范围ΔεＴ的关系式及关系曲线。同时对弯曲加载条件下低周疲劳损伤断口微观形貌进行了观察分析。指出４．５Ｎｉ钢的低周疲劳裂纹扩展方式主要是穿晶，疲劳辉纹为晶体学延性辉纹，疲劳裂纹扩展属于塑性钝化模型机制。     

TC17钛合金盘件的低周疲劳行为

研究了p锻TC17钛合金压气机盘件的应变控制低周疲劳性能及疲劳裂纹扩展途径.结果表明,当应变量△ε/2在0.5%～2.0%范围内,应变比R=-1和循环超过10次后,材料基本上表现为轻度的循环软化.疲劳裂纹萌生于试样表面.当疲劳裂纹与片状α或晶界α之间的夹角小于45°,裂纹沿片状α或晶界α的界面扩展;否则,疲劳裂纹将以穿过片状α或晶界α的方式增长.     

残余应变对表面裂纹扩展速率的影响

在悬臂弯曲加载方式下,采用逐级递增的多级名义应变控制表面裂纹前缘应变的试验方法,进行了在改换名义应变级别控制时残余应变调零和不调零时10CrNiMo结构钢的低周疲劳表面裂纹扩展速率试验,对试验结果进行了比较和分析,结果表明:残余应变会减缓表面裂纹的扩展速率,残余应变越大,这种减缓效果越显著;在过渡为下一级名义应变时残余应变调零将会获得较快的表面裂纹扩展速率。     

悬臂弯曲加载低周疲劳表面裂纹扩展路径的曲折性研究

通过悬臂弯曲加载方式,采用逐级递增的六级名义应变水平作为控制模式,完成了四件试样10CrNiMo钢的低周疲劳表面裂纹扩展速率(SCPR)试验。试验发现,在每级名义应变水平控制下,SCPR整体上趋于某一稳定值,但局部裂纹扩展出现时快时慢现象,在低名义应变水平控制下尤为明显。对上述现象进行了分析,结果表明:出现局部裂纹扩展不稳定的原因是由于表面裂纹扩展的路径呈现转折和分叉的曲折性特征,转折和分叉通常会降低表面裂纹的扩展速率,但有时也会加速表面裂纹的扩展。     

Cyclic deformation behaviour and fatigue crack propagation in AZ91HP and AM50HP

Abstract

The purpose of the present work was to investigate room temperature cyclic deformation and crack propagation behaviour in the most widely used die casting magnesium alloy AZ91HP with different heat treatments. In addition, examination of the low cycle fatigue properties of solid solution treated alloy AZ91HP-T4 was emphasised in comparison with AM50HP. Obvious cyclic strain hardening was found in low cycle fatigue tests, especially for AZ91HP-T4 at high cyclic strain amplitudes. Nevertheless, it was very difficult to evaluate differences in low cycle fatigue behaviour between die casting alloy AZ91HP-F, artificially aged alloy AZ91HP-T6, solution treated alloy AZ91HP-T4, and AM50HP(-F) because of the scatter of test data. However, it may be concluded that the last two alloys had greater plastic strain components during cyclic deformation, and AZ91HP-T4 exhibited a longer fatigue life than that of AM50HP at the highest strain amplitude. According to results of tests carried out on AZ91HP compact tension (CT) specimens, it was concluded that solution treatment could reduce the fatigue crack propagation rate, and plasticity induced crack closure was considered to have a predominant effect on fatigue crack propagation.     

基于材料低周疲劳的裂纹扩展预测模型

该文基于疲劳裂纹尖端循环应力-应变场, 定义了基于应变幅的平均单位循环损伤参量D, 并引入Miner累积损伤率, 从而从理论上建立起材料低周疲劳性能和疲劳裂纹扩展行为之间的联系。以裂尖扩展方向上的单调塑性区尺寸作为疲劳过程区大小, 并提出了基于弹塑性应变疲劳累积损伤的疲劳裂纹扩展预测模型。模型改进了前人提出的疲劳裂纹扩展预测模型, 考虑了单调塑性区内所有材料的弹塑性应变疲劳损伤贡献;模型中参数均有物理意义, 不需要人为调试。基于完成的Cr2Ni2MoV 材料的低周疲劳结果所建立的该文新模型对该材料裂纹扩展速率的预测结果与实验结果有良好一致性。并且, 借助手册数据, 在TC4钛合金材料上进一步得到了验证。     

Fatigue crack initiation and propagation in several nickel-base superalloys at 650°C

The modes of crack initiation and propagation of several nickel-base superalloys have been examined after fatigue and creep-fatigue testing at 650°C. In fatigue, crack initiation was transgranular and frequently associated with porosity or inclusions in the higher strength alloys. These defects were usually located at the surface, except for tests at low strain ranges where larger, internal defects often initiated failure. Although fatigue crack initiation was transgranular, in those alloys with grain sizes of less than 15 μm, fatigue crack growth quickly became intergranular. This transition was environmentally assisted and did not occur for subsurface cracks until the crack broke through to the atmosphere. In the creep-fatigue cycle, which included a 900 s tensile dwell, crack initiation and propagation wer e both intergranular in all alloys.     

Computer modelling application in life prediction of high temperature components

Defects introduced in pressure vessel components during fabrication processes act as potential sources for damage accumulation and subsequent catastrophic failure. Cracks nucleate at these stress risers and propagate aided by fatigue type of loading, corrosion and creep. Analysis of crack growth under conditions of ‘time-dependent fatigue’ is very important for the life prediction of pressure vessel components. In this paper the interaction of creep-hot corrosion and low cycle fatigue is analyzed based on the energy expended for the nucleation of damage at the advancing crack front. The total damage accumulation is divided into that due to (i) fatigue, (ii) corrosion and (iii) creep for modelling purpose. The analysis yields a relation in terms ofJ-integral which is applicable to both crack propagation and final failure. A corrosion-creep parameter (F _i ) has been introduced at the crack propagation stage and raw data from different sources have been analyzed for different types of loading and compared with the theoretical predictions. The total energy in tension which includes the tension going time, appears to be a good parameter for the prediction of time-dependent fatigue life.     

FATIGUE LIFE OF AN AUTOFRETTAGED THICK-WALLED PRESSURE VESSEL WITH AN EXTERNAL GROOVE

Abstract— Fatigue tests that simulate an autofrettaged thick-walled pressure vessel with an external groove under pulsating internal pressure loading conditions were performed using specimens taken from an autofrettaged thick-walled pressure vessel. Load-controlled simulation fatigue tests using rectangular, elliptic, and shot peened elliptic grooved specimens were performed for three different autofrettage levels of 50, 75, and 100% overstrains. In order to estimate the fatigue life of the thick-walled pressure vessel subjected to pulsating internal pressure, the local strain approach was considered to assess the crack formation life. A cyclic stress-strain relation and fatigue damage models determined from strain-controlled low cycle fatigue tests were employed to estimate the fatigue life of the autofrettaged thick-walled pressure vessel. Larger local stresses and strains were obtained from the Neuber's rule compared to the linear rule and these led to conservative fatigue life estimations. Estimated fatigue lives were obtained within factors of 2 to 4, compared to the experimental fatigue lives determined from the simulation fatigue tests.     

Fatigue crack initiation and propagation in electron beam vapor-deposited coatings for gas turbine superalloys

Thermal fatigue crack initiation and propagation in NiCoCrAlY-coated nickel base superalloys have been evaluated. At relatively low strain ranges, the cycles required to initiate coating cracking are a significant fraction of the total fatigue life of a component. Crack initiation occurs preferentially at pit and flake defects in the coating. The strain-temperature cycle shape has a significant effect on coating crack initiation; cycle I, which peaks tensile strains at the minimum temperature, is the most severe from a coatings standpoint. Cycle I thermal fatigue crack initiation and propagation in NiCoCrAlY coatings are dependent on the thermal expansion mismatch with the substrate. The rate of coating crack propagation is also dependent on coating thickness.     

Characteristics of hydrogen-assisted intergranular fatigue crack growth in interstitial-free steel: role of plastic strain localization

The behavior of intergranular fatigue crack growth in an interstitial-free (IF) steel in a hydrogen environment was investigated at different frequencies. Focusing on the plastic strain localization, we observed details of the striation-like feature on the intergranular fracture surface, slip behavior around microvoids, and crystallographic orientation gradient underneath the fracture surface. It was determined that the intergranular fatigue crack growth mechanism in the IF steel is microvoid formation at the crack tip and subsequent coalescence with the crack. Moreover, it was found that the grain boundaries, acting as propagation paths, suffer from pre-damage arising from plastic strain localization near the grain boundaries even before the main crack propagates to a certain location. Therefore, fatigue cracks in a hydrogen environment easily propagate to the grain boundaries. The frequency dependence of fatigue crack growth in the hydrogen environment is significantly smaller than that in a low carbon steel, probably because of the frequency dependence of the pre-damage evolution behavior.