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。     

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...     

室温大气环境下不同时效态2A12合金的疲劳行为

在拉-压疲劳试验机上对室温大气环境下欠时效态、峰时效态、过时效态和自然时效态2A12合金的疲劳行为进行研究,并采用扫描电镜(SEM)分析室温大气环境下不同时效态对疲劳断口形貌的影响.结果表明:在室温大气环境下,四种时效态2A12合金的疲劳断裂循环次数均随着循环应力的减小而明显增加.循环应力水平越低,疲劳寿命提高越明显;各时效态的疲劳断口均为穿晶断口.断口中均出现疲劳条纹、台阶和韧窝,并在较低循环应力下,疲劳条纹出现的区域较多;欠时效态和峰时效态断口上还可观察到轮胎花样.自然时效态表现出最好的疲劳裂纹扩展阻力,其次是欠时效态、峰时效态,过时效态的疲劳裂纹扩展阻力最低.对室温大气环境下各时效态2A12合金疲劳行为进行了讨论.     

真空环境下欠时效态2A12合金的疲劳行为

在低温真空拉-压疲劳试验机上对欠时效态2A12合金的疲劳行为进行了研究,并采用扫描电镜(SEM)分析了真空环境对疲劳断口形貌的影响.结果表明,真空环境使疲劳寿命提高,疲劳曲线右移.在低循环应力时,真空环境中的疲劳断裂次数可比室温大气环境中的多一个数量级.真空和室温大气环境下的疲劳断口均为穿晶断口.在室温大气疲劳断口上可观察到轮胎花样与疲劳条纹.疲劳条纹在低循环应力时出现疲劳条纹的区域增多,真空环境下极少出现轮胎花样与疲劳条纹.文中对真空环境影响欠时效态2A12合金疲劳行为的原因进行了讨论.     

真空环境下欠时效态2A12合金的疲劳行为

在低温真空拉-压疲劳试验机上对欠时效态2A12合金的疲劳行为进行了研究,并采用扫描电镜(SEM)分析了真空环境对疲劳断口形貌的影响.结果表明,真空环境使疲劳寿命提高,疲劳曲线右移.在低循环应力时,真空环境中的疲劳断裂次数可比室温大气环境中的多一个数量级.真空和室温大气环境下的疲劳断口均为穿晶断口.在室温大气疲劳断口上可观察到轮胎花样与疲劳条纹.疲劳条纹在低循环应力时出现疲劳条纹的区域增多,真空环境下极少出现轮胎花样与疲劳条纹.文中对真空环境影响欠时效态2A12合金疲劳行为的原因进行了讨论.     

真空环境下峰时效态2A12合金的疲劳行为

在低温真空拉-压疲劳试验机上对峰时效态2A12合金的疲劳行为进行了研究,并采用扫描电镜(SEM)分析了真空对疲劳断口形貌的影响.结果表明,真空使疲劳寿命提高,疲劳曲线右移.在低循环应力时,真空环境中的疲劳断裂次数可比室温大气环境中的多2至3倍.真空和室温大气环境下的疲劳断口均为穿晶断口.在室温大气疲劳断口上可观察到轮胎花样与疲劳条纹.在低循环应力时出现疲劳条纹的区域增多.真空环境下极少出现轮胎花样与疲劳条纹.对真空影响峰时效态2A12合金疲劳行为的原因进行了讨论.     

欠时效态3J21合金低温拉伸性能

在万能拉伸机上对欠时效态3J21合金室温及低温条件下的拉伸性能进行研究,并采用金相显微镜、X射线衍射仪对冷轧状态和欠时效态的金相组织及物相进行分析,采用TEM观察两种状态的组织和结构,验证了X射线衍射结果.对欠时效态3J21合金不同温度下拉伸断口附近形变显微组织进行分析,采用扫描电镜(SEM)对拉伸断口进行观察.结果表明:欠时效态3J21合金的室温断口为韧窝断口,而低温断口呈现混合断裂特征.随着温度降低,脆性断裂的特征更为明显,低温拉伸断口附近显微组织中可发现孪晶数量随温度的降低而增加;欠时效态3J21合金的抗拉强度和屈服强度随温度的降低而明显提高,其中抗拉强度提高的幅度较大,而延伸率略有下降.对室温和低温对欠时效态3J21合金拉伸性能的影响进行了讨论.     

片层厚度对损伤容限型TC21合金裂纹扩展速率的影响

分别采用α β锻造和β锻造方式制备了TC21合金φ90mm棒材,研究了两种加工方式下同规格棒材的裂纹扩展速率,分析了粗细两种片层结构对裂纹扩展速率的影响.结果表明:β锻造获得了细片层组织结构,具有较低的疲劳裂纹扩展速率;α β锻造得到粗片层组织结构,裂纹扩展速率较快.疲劳裂纹扩展速率随着组织片层厚度的增加而加快.在疲劳裂纹稳态扩展区,裂纹以条带循环机制向前扩展,同时能看到许多疲劳条纹.     

真空环境下过时效态2A12合金的疲劳行为

在真空拉-压疲劳试验机上对过时效态2A12合金的疲劳行为进行了研究,并利用扫描电镜分析了真空对疲劳断口形貌的影响.结果表明:真空环境中疲劳寿命明显提高;在低循环应力下,真空环境中的疲劳断裂循环次数比室温大气环境中高近3倍;室温大气和真空环境下的疲劳断口均为穿晶断口,断口中均出现疲劳条纹、台阶和韧窝,且在低循环应力下,疲劳条纹出现的区域较多,但真空环境下疲劳断口中的台阶高度较低,疲劳条纹与韧窝较细小.     

挤压SiCw／LD2复合材料的疲劳裂纹扩展

本文测量了挤压19％(Vol)SiCw/LD2复合材料疲劳裂纹扩展的门槛值ΔK_(th)和扩展速率da/dN。并在扫描电镜下观察了疲劳断口形貌。结果表明,复合材料在门槛值附近和中速扩展区的疲劳裂纹扩展抗力高于基体材料LD2合金。复合材料纵向试样于170℃时效后的疲劳裂纹扩展抗力高于150℃时效,疲劳裂纹扩展扩展过程包括不在一个面内的微裂纹长大和联接这些微裂纹的(Ⅰ+Ⅱ)复合型裂纹的扩展。与裂纹相垂直的晶须有效地阻碍了微裂纹的长大。     

Microstructural characterization of two lithium-containing aluminium alloys

The microstructures of two lithium-containing aluminium alloys have been investigated. The two alloys were an Al-Li-Mn alloy, heat treated to provide an under-aged, peak-aged and an over-aged condition, and a commercial Al-Cu-Li alloy, 2020, heat treated and aged to contain ordered precipitate structures. It was observed that both materials were recrystallized with fairly large grains. The Al-Li-Mn material had a high volume fraction of Al₆Mn dispersoids and the Al-Cu-Li alloy had a substantial volume fraction of coarse intermetallic particles and intermediate size disperoids. The major strengthening precipitates were identified from brightfield and dark-field images and selected-area diffraction patterns taken in the transmission electron microscope. Precipitate-free zones were found to be present in both the Al-Li-Mn and Al-Cu-Li alloys. The results of this study suggest that the peak-aged Al-Cu-Li alloy and the under-aged and peak-aged Al-Li-Mn alloys enhance deformation to occur primarily by planar slip, and the larger particle size and interparticle spacing of the over-aged Al-Li-Mn promotes a combination of planar slip and Orowan looping.     

Influence of Ageing Heat Treatment on the High Cycle Fatigue of an 8090 Al-Li Alloy

Fatigue lives for the smooth and notched specimens of 8090 Al-Li alloy jn the different ageing conditions have been studied. For the smooth samples of 8090 alloy the artificial ageing results in an increase in fatigue life in comparison with natural ageing. On the contrary, the notched specimens of 8090 alloy in the naturally aged condition show higher fatigue life than in the peak-aged. The exposure to either the peak-aged or naturally aged leads to superior fatigue properties of Al-Li alloy to the traditional high strength aluminum alloys of 7075 and 2024, especially in the latter aged condition. In all ageing conditions, i,e. naturally, under-, peak- and over-aged, the peak-aged 8090 alloy displays the highest fatigue life and the over-aged material has a minimum value at the same stress amplitude. The difference in fatigue life is mainly attributable to the size and distribution of strengthening precipitates as well as the wide of precipitate free zones (PFZ's) along grain boundaries.     

国产与进口5083-H116铝合金微观组织及疲劳裂纹扩展速率研究

研究了国产与进口5083-H116态铝合金轧制薄板材（厚度3 mm）的微观组织及其疲劳裂纹扩展行为。结果表明,国产与进口5083铝合金化学成分均满足相应标准要求。国产与进口5083铝合金显微组织均存在较多的粗大第二相,但后者的数量更多;相对于国产合金,进口合金晶粒尺寸更加细小、分布更加均匀。沿板材横、纵向,国产合金的抗拉强度和屈服强度皆高于进口合金,而延伸率相反。进口合金的疲劳裂纹扩展速率低于国产合金,在ΔK=15 MPa·m^1/2时,其裂纹扩展速率降低了32%以上。疲劳断口皆呈3个典型区域：裂纹萌生区均出现疲劳辉纹,相对于进口合金,国产合金较平坦且存在分层现象;稳态扩展区皆有明显疲劳辉纹,辉纹间距分别为0.405 5μm和0.282 3μm;瞬断区内,进口合金具有数量更多、尺寸更小的韧窝。     

Study of fatigue behaviour of 7475 aluminium alloy

Fatigue properties of a thermomechanically treated 7475 aluminium alloy have been studied in the present investigation. The alloy exhibited superior fatigue life compared to conventional structural aluminium alloys and comparable stage II crack growth rate. It was also noticed that the fatigue crack initiated from a surface grain and the crack extension was dominated by ductile striations. Analysis also revealed that this alloy possessed fracture toughness and tensile properties superior to that noticed with other structural aluminium alloys. Therefore the use of this alloy can safely reduce the overall weight of the aircraft.     

2A12铝合金的多轴加载疲劳行为

采用SDN100/1000电液伺服拉扭复合疲劳试验机对2A12铝合金进行多关键参数的多轴疲劳性能研究,通过对断口的微观分析探究疲劳失效机理。结果表明:等效应力加载条件下,随拉扭相位差的增加疲劳寿命降低,0°相位差下断面裂纹源区能观察到轮胎状、鱼骨状以及钟乳石状的特殊形貌,裂纹扩展区存在二次裂纹和模糊的疲劳条带;分别改变拉、扭平均应力,多轴疲劳寿命均降低,裂纹源区能看到白色絮状的氧化物,瞬断区存在二次裂纹和剪切型韧窝;不同加载波形条件下,正弦波对应最长的多轴疲劳寿命,三角波次之,方波时最短且体现出最大的结构耗能。低-高两级加载条件下,材料产生"锻炼效应"。     

Effect of heat treatment on the behavior of an AA7055 aluminum alloy during ballistic impact

Effect of heat treatment on mechanical properties and ballistic resistance of AA 7055 aluminum alloy plates has been studied. Large differences in the static mechanical properties are observed in the plates subjected to three different heat treatment schedules namely under-aging, peak aging and over-aging. The peak-aged plate shows the maximum strength and hardness followed by the under-aged and over-aged plates. The ballistic resistance of these heat treated plates of thicknesses 5 and 10 mm are evaluated by impacting deformable projectiles at a velocity of 820 ± 10 m/s and at a normal angle of attack, by using a thick backing technique. The under-aged and peak-aged materials exhibit similar ballistic penetration resistances which are superior to the over-aged material. Metallographic examination of the impacted plates shows formation of adiabatic shear band (ASB) induced cracks and few transformed ASBs. Peak-aged 7055 aluminum alloy plate shows much improved ballistic properties compared to commercially available 7017 aluminum alloy plate in terms of the depth of penetration.     

Effect of heat treatment on strain–controlled fatigue behavior of cast Mg–Nd–Zn–Zr alloy

The influence of heat treatment on the strain-controlled fatigue behavior of cast NZ30?K alloy was investigated. Compared with the as-cast and solutionized (T4) alloys, the peak-aged (T6) and over-aged (T7) counterparts have a higher cyclic stress and a lower plastic strain value due to the precipitation strengthening. The as-cast and T4-treated alloys have a higher fatigue strength/yield strength ratio than the aged alloys, which is mainly attributed to their higher cyclic hardening. Under stress-controlled loading, the aged alloys show lower hysteresis energies than the as-cast and T4-treated counterparts, leading to longer fatigue lifetimes. For the T4-treated alloy, the cyclic hardening and fatigue failure are controlled by the dislocations-slip and twinning, while for both the as-cast and T6-treated counterparts, they are controlled by the dislocation-slip. For the T7-treated alloy, cyclic deformation and failure behavior are mainly dependent on dislocations-slip and grain boundary sliding.