疲劳裂纹扩展的非比例过载效应SCIEI

本工作研究了比例(Ⅰ型)过载及非比例(复合型)过载对常幅Ⅰ型疲劳裂纹扩展的影响。结果表明:Ⅰ型过载所引起的裂纹滞后扩展效应远较复合型为强。因此,在估算疲劳寿命时将零、构件实际承受的过载(大都为非比例过载)简单地当作比例过载处理,可能会过高地估计寿命,带来不安全因素。文章从Ⅰ型及复合型过载所引起的裂纹钝化、裂端塑性区的形状、尺寸及裂纹闭合等方面讨论了它们对裂纹扩展滞后效应的影响。     

海洋柔性立管用钢的疲劳断裂行为

采用GPS100高频疲劳试验机研究了海洋柔性立管用钢在温轧工艺下的疲劳断裂行为。结果表明,海洋柔性立管用钢疲劳寿命随加载应力幅的升高而不断下降;疲劳裂纹产生于试样表面,裂纹源区可见变形带及河流花样,裂纹扩展区存在大量二次裂纹,瞬断区疲劳裂纹呈韧性断裂特征。在疲劳裂纹扩展过程中,裂纹的扩展能力因大角度晶界的铁素体和高强度贝氏体的相互作用而受到限制,同时在晶界处形成的二次裂纹同样可减缓扩展速率,达到提高疲劳寿命的效果。     

RuT400蠕墨铸铁热疲劳性能研究

采用光学显微镜(OM)、扫描电镜(SEM)、能谱分析(EDS)及热疲劳试验等对比分析了RuT400蠕墨铸铁在不同循环温度区间的热疲劳性能,研究了裂纹萌生及扩展的规律,并分析了不同开裂现象的成因。结果表明:在450～25℃及650～25℃热疲劳循环温度下,疲劳裂纹长度随着循环周次的增加呈线性增长,且温度越高,增长越快。在420～25℃循环温度下,仅形成了表面裂纹,裂纹没有贯穿材料基体,其原因是该温度尚不足以引起晶界滑动。当循环上限温度超过450℃时,晶界滑动促进了裂纹的形成。热疲劳条件下石墨和铁素体相界首先开裂,随后向铁素体区扩展,多个脱粘微裂纹形成主裂纹。     

挤压AZ31镁合金压压疲劳行为

研究了挤压AZ31镁合金的压-压疲劳行为,并与拉-拉疲劳行为对比,了解孪生对疲劳行为的影响。结果表明,循环压缩滞后环为非对称的S形的曲线,而循环拉伸滞后环比较对称。循环压缩导致了平均应力显著下降。循环应变硬化存在于循环压缩和循环拉伸两种情况下,但循环压缩表现出较强的循环应变硬化中观察到,该行为可归因于压缩阶段易于孪生,孪晶界起到晶界强化效果。与循环拉伸相比,循环压缩样品的塑性应变幅度更大。循环压缩样品具有较大的疲劳裂纹稳定扩展区面积,表明其具有较为优异的疲劳寿命。断裂表面的残余孪晶在两种情况中均会出现。     

TWIP钢的低周疲劳断裂机制

通过采用扫描电镜及透射电镜等手段,观察并研究了TWIP钢在低周单轴循环对称拉压载荷下的疲劳断裂后的显微组织。结果表明:TWIP钢矩形试样的疲劳裂纹一般萌生于角部,从表面萌生时可能表现为多个疲劳源。在低周疲劳变形过程中,TWIP钢不但产生了形变孪晶,还产生了大量的微条带,其实质为细微孪晶片层和驻留滑移带。疲劳裂纹主要萌生于微条带对晶界和孪晶界的撞击引发的孔洞。孔洞串连接起来成为裂纹,夹杂物促进了裂纹扩展。随着裂纹的扩展,试样的承载面积不断减小,最终发生快速的韧性断裂。     

TiAl基合金弯曲疲劳的断裂机制

通过对弯曲疲劳断裂宏观试验结果以及相应的卸载表面观察和断口观察分析研究,发现在疲劳加载的过程中,首先在缺口根部产生裂纹,裂纹在应力循环的作用下不断扩展,直至疲劳裂纹的长度达到与疲劳外加力所匹配的临界裂纹长度时,突然发生整体解理断裂.在一定应力下的疲劳弯曲加载试验中,随着循环次数的增加,产生的裂纹变长,即产生的损伤严重,疲劳区域变宽,其断裂机制是疲劳区各裂纹单向扩展,解理区起裂源分散扩展直至断裂.对于循环次数较小的材料,其断裂机制是具有发散扩展路径的起裂源直接产生于缺口根部,然后分散扩展直至断裂,在其扩展的路径上并不因疲劳区与解理区而有任何的不同.     

应力水平对线弧增材制造TA15钛合金疲劳行为的影响

以原位轧制线弧增材制造TA15合金为研究对象,研究了退火态TA15合金的疲劳性能与疲劳断裂失效行为。结果表明,退火态TA15合金的轧向和纵向组织均以α/β片层交叠形成的网篮组织为主,局部存在等轴晶粒分布。通过对S-N曲线进行拟合,TA15钛合金疲劳极限为311 MPa。试样断口包含疲劳裂纹源区、疲劳裂纹扩展区和瞬断区。裂纹均从表面萌生,同时裂纹扩展区存在大量的疲劳辉纹和二次裂纹,瞬断区由等轴状的韧窝构成,呈现典型的准解理断裂特征。在低循环应力下,裂纹主要穿过或沿着α/β片层组织进行扩展,裂纹扩展路径较长;在高循环应力下,裂纹开始沿着原始β晶界扩展,二次裂纹扩展路径较短但数量较多。疲劳裂纹容易沿着组织中相对薄弱的位置进行扩展,并且二次裂纹周围有裂纹分支生成。     

冷却条件对Cr24Ni16Nb2钢热疲劳性能的影响

采用自约束热疲劳试验方法、金相显微镜和扫描电镜,研究了冷却条件对Cr24Ni16Nb2钢热疲劳性能的影响。结果表明:空冷试样由于晶粒较为均匀,从而随循环次数增加,裂纹长度增加最慢;自然冷却试样由于明显存在柱状晶,使得裂纹更易扩展;水冷试样与空冷试样的扩展规律基本相同。热疲劳裂纹的扩展沿晶界进行,晶界的氧化促进了扩展进程。循环90次后(如180次)试样边缘出现的齿轮状裂纹及裂纹前沿不断加宽,使中心部位的应力得到松弛,从而减慢了裂纹扩展速率。     

预应变对工业纯钛TA2疲劳裂纹尖端应变场的影响

钛制承压设备在制造和服役过程中会产生塑性变形,影响其抗疲劳性能。为了研究预应变对工业纯钛TA2疲劳裂纹扩展行为的影响,本文对原始材料、预应变量为10%、20%和30%的材料进行疲劳裂纹扩展试验,结合数字图像相关(Digital image correlation, DIC)技术获取裂纹尖端应变场,研究预应变对裂纹尖端应变场的影响。结果表明：随着预应变量的增加,稳态疲劳裂纹扩展阶段的扩展速率减小,裂纹张开位移减小,裂纹张开载荷增大,裂纹尖端塑性区、塑性变形量以及循环塑性应变累积量均减小。因此预应变抑制了裂纹尖端的塑性变形及循环塑性累积,致使裂纹闭合效应愈加明显,从而抑制了裂纹的扩展。研究结果对钛制承压设备的安全评定具有参考意义。     

7050铝合金FSW接头微区低周疲劳裂纹扩展行为

对5 mm厚铝合金7050搅拌摩擦焊接头微区进行了低周疲劳裂纹扩展试验,研究了焊核区、前进侧及后退侧热力影响区的疲劳裂纹扩展行为. 结果表明,焊核区的疲劳裂纹扩展速率最快,前进侧热力影响区次之,后退侧热力影响区最慢. 焊核区疲劳裂纹呈沿晶与穿晶混合方式扩展,热力影响区的裂纹主要以穿晶方式进行扩展. 裂纹偏转或裂纹产生分支是热力影响区疲劳裂纹扩展速率降低的原因. 疲劳裂纹扩展初期,焊核区断口有疲劳辉纹出现;热力影响区断口并没有找到疲劳辉纹,而是出现了轮胎压痕花样. 疲劳裂纹稳态扩展期,焊核区和热力影响区断口均有疲劳辉纹.     

EFFECT OF GRAIN BOUNDARY ON FATIGUE BEHAVIOUR OF Al BICRYSTALS

The effect of grain boundaries on cyclic deformation and fatigue crack growth in aluminumbicrystals has been studied.The effect of a grain boundary is restricted in a narrow area,termed as grain boundary affecting zone(GBAZ),where the incompatible plastic straintreats internal stress which conversely promotes inhomogeneous slip in the area and grainboundary cracking.As an extended stage I crack initiated from a notch approaches the grainboundary under a constant cyclic stress,the crack front branches splits into several pieces,meanwhile,the growth rate of the crack reduces to a minimum value at the center of theGBAZ.Such microstructure-sensitive growth of extended stage I cracks is mainly attributedto the grain boundary-induced crack tip sheilding.     

CYCLIC DEFORMATION OF COARSE GRAINED POLYCRYSTALLINE PURE Ai——Ⅰ.SLIP CHARACTERISTICS

Comparing with ordinary ploycrystalline materials sized to μm grade,the slip morphology ofthe coarse grained polycrystalline pure Al is characterized by:(1)several slip domains occurin a grain,and in same domain,several slip systems operate at same time or one after anotherintensely,a beautiful and neat slip pattern is forming on the specimen surface;(2)for highΣ-value coincident and random grain boundaries,the grain boundary affecting zone(GBAZ),bout 50—120μm wide,is favourable site to form intergranular crack at early fa-tigue life easily,and migration or slide of the boundaries were often observed.While lowΣ-value near-coincident grain boundaries show a higher degree of slip continuity and straincompatibility than high Σ-value ones.Intergranular crack is not easily nucleated at lowΣ-value near-coincident boundaries;and(3)due to suppression of grain boundary slip attriple grain boundary node,the high Σ-value and random grain boundary among the threeboundaries of tricrystal crack easily during cyclic deformation.     

EBSD Analysis of Fatigue Crack Growth of 2124 Aluminum Alloy for Aviation

运用电子背散射衍射(EBSD)分析技术对2124-T851铝合金板材的疲劳裂纹扩展进行了分析研究。结果表明,疲劳裂纹扩展以穿晶为主,随晶粒取向的不同而呈现一定的择优性。当裂纹扩展到晶界时,由于相邻晶粒间存在的取向差,裂纹会偏离其正常扩展路径而发生偏转,而晶内的裂纹偏转则更多是因为粗大第二相粒子在循环应力作用下协调变形能力差引起的。裂纹扩展过程中发生裂纹分叉与特定的晶体学方向有关,是由于裂纹尖端多个等效{111}<110>滑移系的同时开动造成的。     

CRACK GROWTH BEHAVIOR AND FRACTURE FEATURE OF GH2132 UNDER CREEP-FATIGUE CONDITIONS

1.IntroductionSuperalloysareirreplaceableinengines[llandenginesundergostaticandcyclicloading[2].Thereforeitisimportanttostudycrackgrowthbehaviorofsuperalloysundercreepfatigueconditions.Itisnoticedthattheeffectofcyclicloadingoncrackgrowthisconsiderablel3'4],butdifferentatalowstresslevelfromthatatahighoneIS'6].Itisfoundthattheyieldstrengthofmaterialsisanimportantparameterinstudyingfatiguepropertiesl7,8]andcrackgrowthic,lo].Soitisofmuchimportancetocorrelatecrackgrowthbehaviorandfracturefeaturew…     

A crystallographic mechanism for fatigue crack propagation through grain boundaries

A crystallographic model is proposed which takes into account both crack-plane twist and tilt effects on crack retardation at grain boundaries. The twist and tilt angles of the crack-plane deflection at a grain boundary are the key factors that control the path and growth rate of a short crack. Because of crack-plane twist, the area between the traces on the grain-boundary plane of the crack planes across the boundary has to be fractured in order for the crack to propagate through the boundary. This presents significant resistance to crack growth. As the area to be fractured increases with the extent of crack growth beneath the surface of observation, the grain boundary could still resist crack growth after the crack tip has passed the grain boundary on the surface, until the crack propagates through the whole boundary below the surface. A grain boundary with a large twist component could cause a short crack to arrest or branch. Studies of short fatigue crack growth in an Al–Li 8090 alloy plate provide evidence that supports the model.     

铜双晶体中晶界及组元晶体的疲劳寿命

本文对具有单,双滑移取向组元晶体的近生趣晶界铜双晶体进行拉－拉循环变形,得出铜双晶体中晶界及组元晶体的Ｓ－Ｎ曲线,比较了铜双晶体晶界及组元晶体疲劳寿命的差别,发现在相同的应力幅下晶界的疲劳寿命明显低于组元晶体的疲劳寿命。     

7050铝合金晶界偏析与应力腐蚀,腐蚀疲劳行为的研究

研究了不同时效状态的７０５０铝合金晶界偏析与应力腐蚀开裂及湿空气环境下疲劳裂纹扩展的关系，并采用修正的化学方法计算了晶界偏析对断裂应力的影响。结果表明：随着时效程度的增加，晶界上Ｍｇ偏析浓度减小，捕获Ｈ的能力减弱，晶界断裂应力的百分数随之下降，因而合金的抗应力腐蚀和腐蚀疲劳性能提高。     

CRACK GROWTH, FRACTURE FEATURE AND RUPTURE LIFEDURING CYCLIC CREEP OF SUPERALLOY GH2132

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IN SITU OBSERVATION OF FATIGUE CRACK GROWTH IN CENTRIFUGAL SPRAY DEPOSITION (CSD) Ti 48Al 2Mn 2Nb ALLOY

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