不同时效态3J21合金疲劳行为

在MTS万能实验机上对室温大气环境下欠时效态、峰时效态和过时效态3J21合金的疲劳行为进行研究,并采用扫描电镜(SEM)对宏观断口及微观断口进行分析.结果表明:不同时效态疲劳裂纹均呈穿晶扩展,欠时效态3J21合金疲劳裂纹萌生寿命最长,扩展途径比较曲折,扩展速率最小,表现出最大的疲劳裂纹扩展抗力,疲劳寿命最长.而过时效态3J21合金的疲劳裂纹萌生寿命最短,沿晶扩展的比例增加,扩展途径相对平直,扩展速率最大,裂纹扩展抗力最小,疲劳寿命最低;峰时效态合金介于两者之间.不同时效态的疲劳断口均由疲劳源、疲劳裂纹扩展区和瞬断区组成.在低速扩展区,欠时效态断口呈现小平面,峰时效态和过时效态断口呈现冰糖状花样,在中速扩展区均未看到长的疲劳条纹,仅发现个别细小的疲劳条纹.     

低合金高强度钢疲劳裂纹扩展速率和扩展寿命的断口反推估算

通过对疲劳失效件的断口扫描电镜分析和二次复型电镜分析,对等幅载荷的疲劳试验零件的疲劳裂纹扩展速率及扩展寿命进行了估算。估算结果表明,从微观角度获得的数据与宏观分析结果符合得很好,从而认为在等幅载荷的情况下,把疲劳裂纹扩展条带对疲劳裂纹扩展寿命进行估算用于低合金超高强度钢是可行的。     

室温大气环境下峰时效态3J21合金疲劳行为

在MTS万能实验机上对室温大气环境下峰时效态3J21合金的疲劳行为进行研究,并采用扫描电镜(SEM)对宏观断口及微观断口进行分析。结果表明,峰时效态3J21合金的疲劳裂纹主要呈穿晶扩展,沿晶扩展的所占比例较小,疲劳裂纹萌生寿命较低,扩展路径比较平直,扩展速率较大,裂纹扩展抗力较小,疲劳寿命较低;峰时效态3J21合金疲劳断口由疲劳源、疲劳裂纹扩展区和瞬断区组成。在低速扩展区,峰时效态断口呈现冰糖状花样,在中速扩展区未看到长的疲劳条纹,仅发现个别细且短小的疲劳条纹,瞬断区可观察到二次裂纹、准解理和韧窝。     

超声载荷下TC4钛合金的疲劳寿命分析

通过计算裂纹尖端应力强度因子及疲劳裂纹扩展速率da/d N,由C.Paris模型推导出安全寿命Nf,由Bathias公式计算"哑铃"状钛合金试样的裂纹扩展寿命。通过理论计算和有限元分析超声疲劳"哑铃"状试样,得出应力最大位置。利用有限元仿真和实验数据分析TC4钛合金疲劳寿命。在20 k Hz的超声疲劳试验中,试样的断口位置表明:TC4钛合金材料内部缺陷是试样萌生裂纹使断裂位置偏离最大应力处的主要原因。并得出疲劳裂纹萌生阶段寿命决定"哑铃"状试样的疲劳寿命。     

室温大气环境下过时效态3J21合金疲劳行为

在MTS万能实验机上对室温大气环境下过时效态3J21合金的疲劳行为进行研究,并采用扫描电镜(SEM)对宏观断口及微观断口进行分析.结果表明,过时效态3J21合金的疲劳裂纹呈穿晶扩展和沿晶扩展,且沿晶扩展的比例较大,疲劳裂纹萌生寿命短,扩展途径相对平直,扩展速率大,裂纹扩展抗力小,疲劳寿命低;过时效态3J21合金疲劳断口...     

疲劳载荷下工业纯铁表面与内部裂纹长度的研究初探

疲劳裂纹扩展试验中,采用表面裂纹长度作为疲劳裂纹长度进行疲劳裂纹扩展计算和疲劳裂纹扩展模型建立的过程中,会导致计算的最终结果和模型产生一定的误差。对工业纯铁板材试样进行疲劳裂纹扩展试验,分析疲劳裂纹扩展过程中裂纹长度与裂纹扩展速率的关系,以及对疲劳裂纹扩展断口形貌特征进行观察。结果表明,上述2种方法均可来确定表面裂纹长度和内部裂纹长度之间的关系。     

超细晶纯钛疲劳裂纹的扩展行为

对纯钛进行2道次室温等径弯曲通道变形(ECAP)、等径弯曲通道变形加旋锻复合变形(ECAP+RS)并在旋锻后在300℃和400℃退火1 h,制备出4种具有不同组织的超细晶纯钛。对这4种超细晶纯钛进行疲劳裂纹扩展实验并观察分析超细晶纯钛的显微组织和疲劳断口的形貌,研究了裂纹的扩展行为。结果表明：显微组织对超细晶纯钛的疲劳裂纹扩展门槛值和近门槛区有显著的影响;超细晶纯钛的疲劳裂纹扩展门槛值随着塑性变形量的增大而增大,随着旋锻后退火温度的提高而降低;疲劳裂纹扩展速率曲线因超细晶纯钛晶粒尺寸和强度的影响出现转折,转折前ECAP+RS复合变形纯钛的抗疲劳裂纹扩展能力比ECAP变形强,且随着退火温度的提高而降低;转折后4种超细晶纯钛的疲劳裂纹扩展速率相差较小,呈现出相反的结果。疲劳裂纹扩展寿命中转折前近门槛区裂纹扩展寿命占绝大部分,因而转折前的门槛值与近门槛区的扩展速率对抗裂纹扩展能力更为重要。     

喷射成形GH738合金的疲劳裂纹扩展行为

进行了不同温度、频率和应力比条件下喷射成形GH738合金紧凑拉伸(CT)试样的疲劳裂纹扩展试验,分析了相应条件下的疲劳裂纹扩展速率及其对疲劳裂纹扩展行为的影响规律。结果表明:随着温度的升高,裂纹扩展速率略有加快;加载频率降低,疲劳裂纹扩展加速;裂纹扩展速率da/d N随应力比R的增大而增大。疲劳断口呈现多裂纹源特征,裂纹稳定扩展为疲劳条带机制。     

用直流电压降法研究高温下GH3230合金的疲劳裂纹扩展行为

采用直流电压降法对GH3230合金进行了高温下的疲劳裂纹扩展试验,分析了温度及应力强度因子对GH3230合金疲劳裂纹扩展速率的影响,并利用扫描电子显微镜对断口进行分析。结果表明：在相同的应力强度因子下,随着温度的升高,合金的裂纹扩展速率增大;温度从750℃升高到850℃时,裂纹扩展速率明显增大,从850℃升高到950℃时,小应力强度因子下的裂纹扩展速率相差不大,随着应力强度因子的增大和温度的升高,裂纹扩展速率的差距增大;观察断口表面可知,在裂纹扩展区和瞬断区,断口表面呈现典型的疲劳辉纹和韧窝特征,随着温度的升高,断口表面的氧化物颗粒增多,裂纹扩展区的疲劳辉纹不明显。     

液体介质对聚氯乙烯疲劳裂纹扩展的影响

本文研究了环境介质对聚氯乙烯疲劳裂纹扩展的影响。结果表明:1.溶剂可使硬聚氯乙烯的疲劳裂纹扩展速率下降至空气中的1/3—1/10;2.硬聚氯乙烯在溶剂中的疲劳裂纹扩展速率下降的幅度随着其与溶剂之间的溶解度参数差值变小而增大;3.硬聚氯乙烯在溶剂中的疲劳裂纹扩展断口比在空气中的表现出较大的塑性。本文还从液体压力所致裂纹闭合效应和裂纹-银纹应力场这两个方面讨论了环境介质降低硬聚氯乙烯的疲劳裂纹扩展速率的机理。     

GH33A合金在蠕变-疲劳交互作用下的裂纹扩展特性

通过对 GH33A 合金在蠕变与疲劳复合加载条件下的系列试验,发现拉伸保时使蠕变与疲劳发生了交互作用,加快了疲劳裂纹扩展速率,加速裂纹早期进入失稳扩展,大大降低了疲劳寿命。GH33A 合金具有良好的抗蠕变裂纹扩展能力,但疲劳裂纹扩展阻力较低。由此讨论了拉伸保时对裂纹扩展的影响,并对在蠕变-疲劳交互作用下的裂纹扩展模型作了探讨。     

On the relation between micro- and macroscopic fatigue crack growth rates in aluminum alloy AMS 7475-T7351

This paper discusses the relationship between striation spacing, i.e., the microscopic crack propagation rate, as measured in postmortem fractographic inspection of fatigue fractured surfaces, and the macroscopic crack propagation rate, i.e., da/dN, as monitored during fatigue crack growth tests. Compact tensile specimens C(T) in prevalent plane-strain conditions were extracted in LT orientation from the center of a 2-in. thick rolled plate of a SAE-AMS 7475-T7351 Al alloy. Testpieces were fatigue tested according to ASTM-E647 standard, at room temperature in a servo-hydraulic closed-loop MTS testing machine operating with the unloading elastic compliance technique. da/dN-ΔK data points were collected in the Paris’ law validity region, with crack growth rates typically ranging from 0.18 to 2.02 μm/cycle. Topographical survey was conducted on the test specimen fracture surfaces in a scanning electronic microscope in order to determine striation spacing created during the fatigue test. Macro- and micro-crack growth rates were compared and good correlation have been obtained for the data within the range of ΔK assessed in the study. Results of crack growth rates have been quantitatively evaluated in terms of fatigue life estimation.     

结构钢S355N及S355N-Z25的低温CTOD断裂韧性及其da/dN研究

分别采用三点弯曲SE(B)与紧凑拉伸C(T)试样,通过-20℃的低温裂纹尖端张开位移CTOD断裂韧性试验及疲劳裂纹扩展速率da/dN试验,研究了S355N及S355N-Z25结构钢的裂纹启裂与扩展的抗力.研究结果表明:S355N钢抵抗裂纹启裂及前期扩展的能力比S355N-Z25钢强,但前者抵抗裂纹后期扩展的能力比后者弱...     

Study of the fatigue lifetimes and crack propagation behaviour of a high speed steel as a function of the R value

High speed steels, such as the alloy H‐13, when used as forging dies are subjected to both wear and cyclic loading, and both of these factors can affect the useful life of such dies. It follows that it is of some importance to determine the fatigue characteristics of such steels. However, fatigue studies of such alloys are limited, especially with respect to fatigue crack propagation (FCP) behaviour as a function of mean stress, and therefore more detailed studies are necessary. In the present study, the fatigue lifetimes and the crack propagation behaviour of a high speed steel were experimentally investigated in laboratory air under different stress ratios, R. A modified linear‐elastic fracture mechanics (LEFM) approach was applied to analyze the experimentally‐obtained FCP behaviour. The predicted S–N curves and crack growth behaviour for a wide range of R ratios agree well with the experimental data, and the modified LEFM approach is therefore considered to be useful for evaluation of the fatigue behaviour of this class of high strength steels.     

30Cr1Mo1V钢汽轮机转子高应力段的疲劳裂纹扩展速率

在某已服役了16 a的30Cr1Mo1V钢汽轮机转子的高应力段取样制作成紧凑拉伸试样,用MTS 810.50试验机进行室温和538℃下的疲劳裂纹扩展速率试验。结果表明：该钢疲劳裂纹稳定扩展阶段的疲劳裂纹扩展速率适用于Paris公式,室温下的疲劳裂纹扩展速率方程为da/dN=2.2101×10-8（ΔK）2.9163,538℃下的疲劳裂纹扩展速率方程为da/dN=9.8794×10-8（ΔK）2.6844;对于30Cr1Mo1V转子钢,温度升高,疲劳裂纹扩展速率加快;30Cr1Mo1V转子钢在疲劳裂纹稳定扩展阶段存在转折点,将该阶段又细分为两段,经过转折点后疲劳裂纹扩展速率的增速减慢;与原始材料相比,已服役16 a的30Cr1Mo1V钢汽轮机转子高应力段材料的疲劳裂纹扩展速率增大。     

Weld root crack propagation under mixed mode I and III cyclic loading

This study examined fatigue propagation behaviour and fatigue life of weld root cracks under mixed mode I and III loading. Fatigue tests were performed on butt-welded joints with a continuous lack-of-penetration (LOP) inclined at angles of 0°, 15°, 30° or 45° to the normal direction of the uniaxial cyclic load. Branch and/or co-planar crack propagation was observed, depending on the initial mode I stress intensity factor (SIF) range. Co-planar crack propagation predominated when the SIF range was large. The fatigue crack propagation mode affected fatigue life; the life of branch crack propagation was longer than that of co-planar crack propagation. Using an initial equivalent SIF range based on a maximum strain energy release rate criterion, the results obtained from the 0°, 15°, 30°, and 45° specimens indicated almost the same fatigue lives, despite the different inclination angles.     

Verfahren zur vollständigen Ermittlung der R‐Abhängigkeit des Rissausbreitungsverhaltens mit nur einer Probe

Procedure for the determination of the complete R‐dependency of the crack growth behaviour with only one specimen A new concept for fatigue crack propagation tests has been developed. Using a single specimen, it is possible to determine fatigue crack growth curves (da/dN ‐ ΔK) for every stress ratio between R = 0.9 and R = ‐1. Additionally, the new concept also provides threshold values for fatigue crack growth for different values of R and K_max. In combination with a continuous crack length measurement tool (such as the DC potential drop method) this testing procedure can be performed with minimal effort of personnel and time. The test procedure consists of a sequence of K_max‐constant tests with decreasing crack growth rates. As the applied K_max is increasing stepwise there should be no load history effects. According to the procedures described in the ASTM Standard E 647, the results using this new testing procedure fit very well to the da/dN ‐ ΔK curves generated with different specimens. The tests also fulfil all the requirements of ASTM Standard E 647.     

Effects of Shot‐Peening on Fretting Fatigue Crack Growth Behavior in Ti‐6Al‐4V

Abstract: The effects of shot‐peening on fretting fatigue crack growth behaviour in titanium alloy, Ti‐6A1‐4V were investigated. Three shot‐peening intensities: 4A, 7A and 10A were considered. The analysis involved the fracture mechanics and finite element sub‐modelling technique to estimate crack propagation lives. These computations were supplemented with the experimentally measured total fretting fatigue lives of laboratory specimens to assess the crack initiation lives. Shot‐peening has significant effect on the initiation/propagation phases of fretting fatigue cracks; however this effect depends upon the shot‐peening intensity. The ratio of crack initiation and total life increased while the ratio of the crack propagation and total life decreased with an increase of shot‐peening intensity. Effects of residual compressive stress from shot‐peening on the crack growth behaviour were also investigated. The fretting fatigue crack propagation component of the total life with relaxation increased in comparison to its counterpart without relaxation in each shot‐peened intensity case while the initiation component decreased. Improvement in the fretting fatigue life from the shot‐peening and also with an increase in the shot‐peening intensity appears to be not always due to increase in the crack initiation resistance from shot‐peened induced residual compressive stress.     

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.     

TA5钛合金的疲劳裂纹扩展门槛值与疲劳裂纹扩展速率的关系

研究了大规格ＴＡ５钛合金热轧环村的疲劳裂纹扩展门槛值ΔＫ＿（ｔｈ）与疲劳裂纹扩展速率加ｄａ／ｄＮ之间的关系。结果表明，Δｋ＿（ｔｈ）值可由近门槛区的ｄａ／ｄＮ表达式直接按定义ｄａ／ｄＮ值算，而无需进行繁琐的试验测定。这一结果同样适用于β区加热热轧ＴＡ５钛合金板材。