Ce对Al－Li合金物理短裂纹扩展特性的影响

本工作研究了２０９０和８０９０合金名义门槛值、本征门槛值和闭合效应对裂纹尾迹的响应关系。Ａｌ－Ｌｉ合金具有优良的疲劳长裂纹门槛值和强的短裂纹效应，其物理本质是高的裂纹闭合效应和裂纹闭合效应的尾迹依赖性．２０９０合金微小裂纹的扩展抗力劣于７０７５合金，系因△Ｋｉ低；８０９０合金的△Ｋｉ与２０２４合金相当，其短裂纹扩展抗力相当或优于２０２４合金，微量稀土元素Ｃｅ可显著改善２０９０合金的本征门槛值，有益于裂纹闭合效应，较大幅度提高其疲劳长、短裂纹扩展抗力。Ｃｅ降低８０９０合金的本征门槛值，有损于其疲劳长、短裂纹扩展抗力。     

STUDY ON FATIGUE CRACK GROWTH BEHAVIOR OF HIGH AND LOW-STRENGTH STEELS

本文研究了5C钢和两种不同强度的40CrNiMo钢长、短裂纹近门槛区域的疲劳裂纹扩展性能。并测定了它们的闭合效应和断面粗糙度,结果表明:长、短裂纹的扩展速率和门槛值差别与钢强度有关,5C钢短裂纹的门槛值只是长裂纹的一半。长、短裂纹疲劳特性的差别可用闭合效应来解释。     

高、低强度钢疲劳短裂纹扩展特性

本文研究了5C钢和两种不同强度的40CrNiMo钢长、短裂纹近门槛区域的疲劳裂纹扩展性能。并测定了它们的闭合效应和断面粗糙度,结果表明:长、短裂纹的扩展速率和门槛值差别与钢强度有关,5C钢短裂纹的门槛值只是长裂纹的一半。长、短裂纹疲劳特性的差别可用闭合效应来解释。     

高速列车车轴用EA4T钢腐蚀疲劳性能研究

目的 研究腐蚀环境中EA4T车轴钢疲劳性能,为车轴的腐蚀检测和使用寿命评估提供依据.方法 采用旋转弯曲疲劳试验机,在人造雨水模拟的腐蚀环境和空气环境中,对EA4T车轴钢试样进行疲劳试验,以获得不同环境下试样的疲劳S-N曲线、表面损伤以及裂纹扩展规律.然后对扩展裂纹进行概率统计,通过扫描电镜对疲劳失效的断口进行观察,并分析对比不同环境中裂纹扩展门槛值的变化.结果 空气环境中,试样的疲劳极限为355 MPa,而在腐蚀环境中,试样不存在疲劳极限,107循环周次对应的疲劳强度降低到245 MPa,相比空气环境中降低了31％.Gumbel分布统计与Weibull双参数分布统计相比,更适合描述EA4T车轴钢试样表面腐蚀裂纹长度随加载次数的变化.腐蚀环境中,疲劳裂纹萌生于表面腐蚀坑,并存在多个裂纹源.腐蚀环境显著降低了试样裂纹扩展门槛值,空气环境下,该值为6.29 MPa·m1/2,腐蚀环境下降低到4.1 MPa·m1/2.结论 腐蚀环境降低EA4T钢疲劳寿命的主要原因是,腐蚀环境降低了裂纹扩展门槛值,加快了裂纹萌生以及短裂纹扩展.而当裂纹达到一定长度时,腐蚀环境对裂纹扩展几乎没有影响.     

不锈钢在循环扭转载荷下近门槛值的疲劳裂纹扩展行为

研究了带环状预裂纹不锈钢圆棒试样在循环扭转载荷下、门槛值附近的疲劳裂纹扩展行为,用应力强度因子表征了裂纹扩展开始的门槛值．随着裂纹的扩展,裂纹扩展速率由于裂纹面的滑移接触而减小．通过外插裂纹扩展速率与裂纹长度之间的关系,可近似得到裂纹长度为零时无裂纹面滑移接触影响的裂纹扩展速率．施加的应力强度因子范围可分解为推动裂纹扩展的有效值和由于裂纹面的滑移接触而屏蔽掉的两部分．预测了疲劳裂纹的萌生和断裂极限,预测值和实验值相当一致．     

8090Al—Li合金疲劳短裂纹门槛值的研究

本文研究了8090Al-Li合金穿透疲劳短裂纹的门槛值,测定了不同长度短裂纹的门槛值和裂纹闭合效应,探讨了该合金疲劳短裂纹门槛值、裂纹尾迹和裂尖屏蔽之间的关系,给出了该合金穿透疲劳短裂纹的上界值和理论最低门槛值。     

TiAl合金高温疲劳小裂纹与长裂纹扩展行为

采用原位观察疲劳试验方法研究了变形TiAl合金在650℃下的三维小裂纹扩展行为,利用传统疲劳裂纹扩展试验方法研究了该合金在650～800℃温度范围内的长裂纹扩展行为。结果显示,650℃下,变形TiAl合金的三维小裂纹在低于长裂纹扩展门槛值的区域依然能够扩展,并且扩展速率高于长裂纹;位于试样棱边的横向机械加工刻痕是合金三维小裂纹萌生的主要位置之一,小裂纹在扩展过程中发生偏折并在偏折处合并,合金的疲劳寿命对试样表面的不规则条状加工缺陷不敏感;在650～800℃温度范围内,合金的疲劳长裂纹稳态扩展速率对温度变化不敏感,裂纹扩展过程均显示为解理断裂,裂纹扩展门槛值受韧/脆转变温度影响,韧/脆转变温度以下温度的门槛值较低。     

Ce对Al—Li合金物理短裂纹扩展特性的影响

本工作研究了２０９０和８０９０合金名义门槛值、本征门槛值和闭合效应对裂纹尾迹的响应关系。Ａｌ－Ｌｉ合金具有优良的疲劳长裂纹门槛值和强的短裂纹效应，其物理本质是高的裂纹闭合效应和裂纹闭合效应的尾迹依赖性。２０９０合金微小裂纹的扩展抗力劣于７０７５合金，系因ΔＫｉ低；８０９０合金的ΔＫｉ与２０２４合金相当，其短裂纹扩展抗力相当或优于２０２４合金。微量稀土元素Ｃｅ可显著改善２０９０合金的本征门槛值，有益     

考虑应力比和门槛值的海水腐蚀疲劳裂纹扩展预测模型

采用自行改造的海水腐蚀疲劳试验机,研究了3 Hz频率、不同应力比R (0.1、0.3、0.5)下,海洋工程用结构钢DH36Z35在空气和人造海水中疲劳裂纹扩展动力学行为。结果表明:相同裂纹尖端应力场强度因子幅值ΔK下,空气和海水环境中都显示疲劳裂纹扩展速率随着应力比R的增加而增加的规律,在近门槛值区间1×10-7mm/cycle≤da/d N≤1×10^-6mm/cycle该现象尤其明显;在疲劳裂纹扩展速率da/d N>1×10-6mm/cycle的中速区间,空气中和海水中疲劳裂纹扩展速率出现拐点,高于该拐点海水加速裂纹扩展,低于该拐点海水抑制裂纹扩展,且应力比R越大,拐点对应裂纹扩展速率越高。依据空气和海水中不同应力比和门槛值条件下疲劳裂纹扩展速率实验结果,提出了一种修正的Walker模型,可通过空气中疲劳裂纹扩展速率预测不同应力比下海水环境中疲劳裂纹扩展速率。     

超高强度钢超高周循环下疲劳裂纹扩展寿命研究

以Paris裂纹扩展理论为基础,根据不同阶段裂纹扩展速率不同,将裂纹扩展分为三个阶段:低于始裂门槛值阶段、短裂纹扩展阶段和长裂纹扩展阶段.在每个阶段对Paris裂纹扩展公式分别进行积分,最后将三个阶段寿命相加,即可得到裂纹扩展总寿命.此方法所得到的裂纹扩展寿命较Paris公式略高,但是不会改变疲劳总寿命主要由疲劳裂纹萌生决定,裂纹扩展寿命远小于试验总寿命这一事实.     

GROWTH OF SHORT CRACKS OF A537CLI STEEL UNDER FATIGUE LOADING IN 3.5% NaCl SOLUTION

The effects of environmental media,both in atmosphere and in 3.5% NaCl aqueous solution,on the growth of short cracks in comparison with the long ones have been investigated underfatigue loading on the specimens of single-edge crack about 0.05—0.15 mm for A537CLIsteel.The growth rate of short cracks is faster than those of long ones around the threshohtstress intensity.The threshold stress intensity for short crack growth decreases with de-creasing crack length.The acceleration effect of the salt water,as compared with atmosphereenvironment,on the growth of short cracks under fatigue is much greater than that on thegrowth of long cracks.     

FATIGUE CRACK PROPAGATION IN Al-Li ALLOY 8090

Fatigue crack growth rates of Al-Li alloy 8090 in air were found to be strongly dependent up-on the aging conditions.The naturally aged and underaged specimens showed the highest re-sistance to the fatigue crack propagation.The fatigue crack growth resistance of the overagedspecimen is the lowest and that of the peakaged specimen in between.As compared to air,3.5% NaCl solution does not change the effect of aging conditions on the fatigue crackgrowth,but causes a decrease of the resistance to the fatigue crack growth under the same ag-ing condition.Both short cracks from notch and physically short cracks showed much higherrates of fatigue crack propagation in comparison with long cracks under the same aging condi-tion and stress intensity level.The growth behavior of the short crack depends on its type.Thegrowth rate of short crack from notch decreases first to a minimum and then increases with in-creasing △K.However,the physically short crack grows at a progressively increasing rate.The effects of aging conditions are explained in terms of the slip planarity of dislocations andthe cyclic slip reversibility.The observed short crack behavior is considered to be dependent onthe crack closure and the local plasticity near the crack tip.     

30CrMnSiNi2A高强钢的疲劳小裂纹扩展特性及寿命预测

研究了３０ＣｒＭｎＳｉＮｉ２Ａ高强钢在恒幅载荷下的小裂纹起始特征和裂纹扩展特性。试验结果表明，小裂纹起始于缺口表面初始缺陷（如夹杂或孔洞）处。在应力比Ｒ＝０的恒幅载荷下，未显示小裂纹效应：在Ｒ＝－１的恒幅载荷下，则显示出小裂纹效应的存在。利用裂纹闭合模型和微观结构缺陷作为初始裂纹尺寸的方法预测了小裂纹扩展速率和疲劳全寿命，预测值与实验值符合良好。     

8090Al—Li合金的疲劳裂纹扩展

研究了8090型Al—Li合?疲劳裂纹扩展行为以及组织结构和环境的影响,结果表明,在空气中,自然时效和欠时效?现出最好的疲劳裂纹扩展阻力,其次是峰时效状态,而过时效状态的疲劳裂纹扩展阻力最低,在3.5%NaCl水溶液中,时效状态对疲劳裂纹扩展行为有着同空气中相同的影响规律,但在同样的时效条件下,在3.5%NaCl水溶液中的疲劳裂纹扩展阻力要比空气中的低,在相同的应力强度因子范围△K作用下,缺口短裂纹和物理短裂纹均表现出比长裂纹高的扩展速率,用位错的平面滑移性和循环滑移可逆性解释了时效的影响,用裂纹的闭合效应和裂纹尖端塑性区尺寸说明了长短裂纹扩展行为的差别。     

考虑形状比的焊趾裂纹扩展行为的数值仿真分析

针对焊趾处初始裂纹的不同形状比,基于NASGRO裂纹扩展速率模型对裂纹扩展过程进行了数值仿真. 以具有不同形状比的半椭圆表征焊趾表面裂纹,考虑短裂纹扩展阶段,采用M积分计算整个裂纹前沿的应力强度因子,并将裂纹前沿应力强度因子中值点作为裂纹扩展的主要控制参量,模拟并分析了不同形状比条件下裂纹前沿的形状演变和应力强度因子的分布及变化特点. 结果表明,随着裂纹的扩展,短裂纹阶段的不同形状比变化将趋于一致;短裂纹的形状比对早期裂纹扩展有较大影响,并最终导致整体疲劳寿命的显著差异性;综合初始形状比对裂纹前沿应力强度因子、扩展形状以及疲劳寿命的影响,可将其作用效果的强弱拐点作为界定短裂纹与长裂纹的有效参考. 开展了十字焊接接头疲劳验证试验,试验结果与仿真结果具有较好的一致性.     

Fatigue lives of friction stir spot welds in aluminum 6061-T6 sheets

The fatigue lives of friction stir spot welds in aluminum 6061-T6 lap-shear specimens under cyclic loading conditions are investigated in this paper. The paths of fatigue cracks near friction stir spot welds in lap-shear specimens are first examined. The experimental observations suggest that under cyclic loading conditions, the fatigue crack is initiated near the possible original notch tip in the stir zone and propagates along the circumference of the nugget, then through the sheet thickness and finally grows in the width direction to cause final fracture. A fatigue crack growth model based on the Paris law for crack propagation and the local stress intensity factors for kinked cracks is then adopted to predict the fatigue lives of friction stir spot welds. The global and local stress intensity factors are used to estimate the local stress intensity factors of kinked cracks with experimentally determined kink angles. The results indicate that the fatigue life predictions based on the Paris law and the local stress intensity factors as functions of the kink length agree well with the experimental results.     

Fatigue threshold and crack propagation in γ-TiAl sheets

The fatigue crack propagation behaviour of two different microstructures — a coarse-grained designed fully lamellar (DFL), and a fine-grained near γ (FG) — of a Ti–46.5 at.% Al–4 at.% (Cr, Nb, Ta, B) alloy was studied. Both the threshold of stress intensity range and standard long crack growth behavior were determined. A special technique was applied to separate the different mechanisms — intrinsic and extrinsic effects — and their changes with crack length. The fatigue crack propagation rate of long cracks is much smaller in the DFL microstructure than in the FG microstructure at the same stress intensity range. The effective threshold of stress intensity range of both microstructures is about 1.7 MPa√m. The threshold of stress intensity range shows a strong R-curve behavior. In other words the propagation–non-propagation conditions of cracks are significantly influenced by the crack extension. The long crack thresholds of stress intensity range at the stress ratio 0.1 are relatively large; they are about 4.5 and 8 MPa√m in the DFL and the FG microstructure, respectively. The differences in the crack growth behavior between the two microstructures are mainly induced by extrinsic resistance mechanisms.     

THRESHOLD OF SHORT FATIGUE CRACK FOR Al-Li ALLOY 8090

Threshold of fatigue for short through cracks for Al-Li alloy 8090 was evaluated to be lowerthan that of long cracks,and to decrease with the shortening of the crack length.The correla-tion among the threshold,crack wake,and crack tip shielding of the short fatigue cracks wasdiscussed.The super demarcation length and lowest theoretical threshold of short through fa-tigue cracks were presented.     

Short fatigue crack growth behaviour of a ferritic steel weld metal

Abstract

The present study deals with the short fatigue crack growth behaviour of a ferritic steel (nuclear grade SA 333 Grade 6 steel) weld metal at two load ratios R of 0.1 and –1. Single edge notched weld joint specimens were tested at different stress levels. The acceleration and deceleration in short crack growth with increasing stress intensity factor range was explained in terms of microstructure of weld metal. Acicular ferrite and grain boundary ferrite acted as barriers to crack growth. Non-propagating cracks were observed due to multiple cracks and blocking by ferrite grain boundaries. Transition crack length, the limiting crack length above which the crack exhibited a typical long crack behaviour, was determined to be 1 mm at R=0.1 and 1.5 mm at R=2 1.     

BEHAVIOUR OF INITIATION AND GROWTH OF SHORT FATIGUE CRACKS

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