Effect of laser shock processing on residual stress and fatigue behavior of 6061-T651 aluminum alloy

Laser shock processing is a very new technique and an emerging modem process that generates compressive stresses much deeper into the surfaces of metals or alloys. A brief parametric study of the effect of laser parameters on fatigue behavior and residual stress state generated in 6061-T651 alloy specimens was summarized. Residual stress of 6061-T651 alloy was analyzed both before and after laser processing with multishocks. The material remains in compressive residual stress of approximate 1 mm in depth which is approximately 10 times deeper than that can be achieved with the conventional technique, and the maximal compressive residual stress at the surface of the sample is about -350MPa. Near the surface, yield strength and hardness are found to be increased by the laser shock. The ratio of fatigue crack initiation life for the laser-shocked to unshocked specimens is found to be 4.9 for specimens. The results clearly show that LSP is an effective surface treatment technique for improving the fatigue performance of aluminum alloys.     

高温变形中2B25-T3511铝合金组织及性能

通过高温拉伸、TEM和SEM等手段对2B25-T3511铝合金高温力学性能及组织变化进行研究。结果表明,随拉伸温度升高,合金强度逐渐下降,其中抗拉强度随温度升高而降低的趋势较屈服强度显著;伸长率先升高-降低-略有升高-降低的"M"状变化趋势。在175℃以下,晶粒内基本没有新析出相,合金基体随拉伸温度升高而不断发生软化是强度降低的主要因素,合金基体与相粒子之间的界面弱化以及175℃以上时晶内细小片针状析出相的析出是合金塑性呈现"M"状变化的原因。随温度升高,断口形貌也由沿晶断裂为主逐渐过渡到以高温滑移特征以及基体/沉淀相界面的滑脱为主的韧窝形貌。     

An investigation of the reduction in tensile strength and fatigue life of pre-corroded 7075-T6 aluminum alloy

In aging aircraft, the synergetic interaction between corrosion and fatigue has been shown to reduce the life expectancy of aluminum alloys. The objective of this study was to quantify the effects of corrosion, in terms of mass loss per unit area, on the static strength and fatigue life of 7075-T6 aluminum alloy. This was an experimental study in which test specimens were corroded in a laboratory environment. The corrosion process was accelerated by use of a corrosion cell. Test specimens were cut from flat sheets of aluminum and covered with masking material to restrict corrosion to a confined area. After testing, the fatigue life, ultimate tensile strength (UTS), and hardness of the specimens were observed to drop significantly with small amounts of corrosion. After the initial decrease, the UTS was observed to decrease linearly with increasing corrosion levels. The fatigue life of the specimens decreased in an inverse exponential fashion as mass loss per unit area increased. The hardness values of the corroded surfaces were also observed to drop. The topology of the pits and the related subsurface damage produced areas of high stress concentration resulting in the immediate reduction of UTS and fatigue life of the specimens. Subsurface corrosion damage was responsible for the reduction in hardness.     

铝合金搅拌摩擦点焊疲劳性能研究

研究了2mm厚的6082-T6铝合金搅拌摩擦点焊接头的疲劳性能。在最优的焊接工艺参数和良好的焊接接头的基础上,完成了点焊接头的疲劳实验,观察分析点焊接头薄弱环节的微观组织和疲劳断口的形貌,并测试接头显微硬度,得到了在一定范围内预测疲劳寿命的表达式。结果表明:疲劳裂纹在上下板间的接头根部起裂,在热影响区和热力影响区的交界处扩展直至断裂;微量元素形成的强化相在很大程度上影响点焊接头的疲劳性能;点焊接头的疲劳寿命随着应力强度因子的变小呈增大趋势。     

Microstructure evolution of Al-Zn-Mg-Cu-Zr alloy during hot deformation

Compression tests of the Al-Zn-Mg-Cu-Zr(7055) alloy were performed at various strains and temperatures from 300 to 450°C under a constant strain rate between 10⁻² s⁻¹ and 1 s⁻¹. Microstructures during hot deformation were studied by transmission electron microscopy (TEM). Dislocation density, dislocation cells and subgrains of the deformed samples were investigated in detail and compared to make a better understanding of the microstructure evolution. The results showed that stress-strain curves under the experimental conditions belonged to the type of dynamic recovery. When the alloy deformed at various strains and 300°C, the microstructure underwent a process of disordered dislocations to cell structure, subgrain structure and subgrain coarsening. With the temperature increasing, subgrains grew and dislocation density in the interior decreased at a strain rate of 1 s⁻¹. At the temperature of 350°C, the average diameter of subgrains decreased, sub-boundaries broadened and dislocation density in the interior decreased when the strain rate was increased. The deformed samples of 7055 alloy had smaller subgrains than that of 7005 alloy at the same compression condition because of high alloy content.     

A356铸造铝合金的疲劳裂纹萌生及短裂纹扩展研究

研究了A356-T6铸造铝合金的缺口疲劳裂纹萌生与早期扩展行为及机制.结果表明,热等静压试样的疲劳抗力优于非热等静压试样.对于钝缺口试样,疲劳裂纹萌生于缺口根部附近的多个平面,最终哪个裂纹源扩展成主裂纹取决于局部微观组织.对于缺口几何形状不同的热等静压和非热等静压疲劳试样,在疲劳过程中,不管是在高应力状态下,还是在低应力状态下,都出现了铝基体的循环塑性变形和共晶硅粒子断裂导致疲劳裂纹萌生.对于非热等静压试样,铸造缩孔在构件的疲劳过程中起着重要作用,但即使缺口根部存在较大尺度的铸造缩孔,导致了疲劳裂纹萌生,但也同时观察到疲劳裂纹从共晶硅粒子、金属间化合物、铝基体的滑移带和铁基金属间化合物等处萌生.对于脆性的A356铸造铝合金可采用修正的断裂力学参量ΔKn、局部应力范围Δσ或局部应变幅Δε/2作为控制参量来表征疲劳裂纹萌生行为,而缺口有效应力强度因子范围ΔKneff和ΔJs参量可用来表征缺口场中短裂纹扩展行为.     

A7075搅拌摩擦焊疲劳裂纹扩展速率试验分析

对航空用铝合金A7075-T651的搅拌摩擦焊接头的母材、焊核区和热影响区的疲劳裂纹扩展速率（da／dN）进行了试验研究。疲劳裂纹扩展试验采用CT（紧凑拉伸）试样,在810 Material Test System试验机上进行。用递增多项式法求得疲劳裂纹扩展速率（da／dN）和（△K）,并分别将母材、焊核区和热影响区同一组试样的（da／dN）和（△K）数据点合在一起进行了整体回归分析。试验中得到了以Paris公式表达的铝合金A7075-T651母材、焊核区、热影响区da／dN与△K的关系式。结果表明,热影响区疲劳裂纹扩展速率高于母材和焊核区,是该合金搅拌摩擦焊接头最薄弱的区域。     

2519铝合金热变形组织演化

采用Gleeble-1500热模拟实验机研究2519铝合金高温变形组织演化行为。利用光学显微镜（OM）及透射电子显微镜（TEM）分析合金在不同压缩条件下的组织形貌特征。结果表明,2519铝合金在变形温度为300-450℃、应变速率为0．01～1s^-1条件下,仅发生动态回复;而在变形温度为350-450℃,变形速率为10s^-1的条件下变形时,发生动态再结晶,动态再结晶机制为连续动态再结晶和几何动态再结晶。     

6005A铝合金焊接接头预腐蚀对其疲劳性能的影响

6005A铝合金广泛用于高速列车的生产。通过对4 mm厚6005A铝合金焊接接头进行预腐蚀试验及疲劳性能测试,研究不同预腐蚀等级下6005A铝合金焊接接头的疲劳寿命及预腐蚀对焊接接头疲劳强度的影响。结果表明,6005A铝合金焊接接头经预腐蚀后,腐蚀最严重的为熔合线,其次为母材,焊缝腐蚀程度最轻;与未腐蚀试样相比,预腐蚀试样的疲劳极限有一定降低;预腐蚀后焊接接头断裂均在熔合线;断口疲劳源区可发现类解理河流、台阶花样及擦伤痕迹,疲劳扩展区发现明显疲劳条带。     

Tensile and fatigue properties of aluminum alloy sheet 6022

Tensile and fatigue tests were performed on aluminum alloy 6022 T4E29 and T6 sheet specimens in ambient air. The tensile and fatigue properties were compared with other commercial aluminum alloys. The results showed that 6022 alloy has high fatigue strength and good ductility with moderate tensile strength.     

CuW80铜钨合金疲劳损伤过程的研究

借助扫描电镜研究了CuW80铜钨合金电触头材料在循环载荷作用下微观组织的变化过程,用系统分析的方法定义CuW80铜钨合金疲劳损伤参数,并对其三点弯曲疲劳损伤过程进行了定量跟踪分析.试验结果表明,CuW80铜钨合金疲劳的损伤过程可以分为三个阶段,具有双线性损伤过程的特征,分别对应于疲劳裂纹萌生阶段(EF)和扩展过程(FH)两个线性阶段,且分别占疲劳总寿命的60%和33%;在循环载荷作用下CuW80铜钨合金的疲劳裂纹主要萌生于铜钨合金铜相的晶体内,而非发生于铜、钨界面,并且疲劳裂纹在铜相晶体内不断扩展直至断裂.     

High cycle fatigue and fracture behavior of 2124-T851 aluminum alloy

The high cycle fatigue properties and fracture behavior of 2124-T851 aluminum alloy were investigated roundly, including the fatigue crack growth rate, fracture toughness and fatigue S--N curve. Furthermore, the fatigue crack growth rate was analyzed by fitting the curves. And the microstructure of the alloy was studied using by optical microscopy, transmission electron microscopy and X-ray diffractometry, scanning electron microscop1/2 The results show that the fatigue strength and the fracture toughness of 2124-T851 thick plate are 243 MPa and 29.6 MPa.m at room temperature and R=0. 1, respectively. At high cycle fatigue condition, the characteristics of fatigue facture were observed obviously. And the higher the stress amplitude, the wider the space between the fatigue striations, the faster the rate of fatigue crack developing and going into the intermittent fracture area and the greater the ratio between the intermittent fracture area and the whole fracture area.     

Fatigue and corrosion fatigue behavior of an AA6063-T6 aluminum alloy coated with a WC-10Co-4Cr alloy deposited by HVOF thermal spraying

The present investigation has been conducted in order to study the fatigue and corrosion fatigue behavior of an AA6063-T6 aluminum alloy substrate coated with a WC-10Co-4Cr deposited by HVOF thermal spraying. It has been determined that the deposition of such a coating on the aluminum substrate gives rise to significant gains in fatigue life in comparison with the uncoated substrate, when testing is carried out both in air and in a 3 wt.% NaCl solution. It has been shown that during testing in air, the fatigue gain ranges between ~ 540 and 4300%, depending on the maximum alternating stress applied to the material. Larger fatigue gains are associated with low alternating stresses. Also, when fatigue testing is conducted in the NaCl solution, the gain in fatigue resistance varies between ~ 620 and 1460%. Fatigue cracks have been observed to initiate at the coating surface and then grow towards the substrate after propagating through the entire coating thickness. Crack growth along the coating has been observed to occur mainly along the regions formed by the agglomeration of W and W-Co-Cr-rich particles, flanking the tougher Co-Cr-rich areas. Although in the present work residual stresses were not measured, it is believed that the gain in fatigue life of the coating-substrate system is due to the presence of compressive residual stresses within the coating which hinder fatigue crack propagation. The deposition of the coating does not give rise to significant changes in the static mechanical properties and hardness of the aluminum alloy substrate. It has been observed that the WC-10Co-4Cr coating displays a significant indentation size effect and has a mean hardness of ~ 9.4 GPa.     

5A90Al-Li合金超塑性变形过程中的显微组织及微观织构演变

通过采用电子背散射衍射技术研究具有扁平状组织的5A90 Al-Li合金板材在变形条件475℃、8×10^-4S^-1时的显微组织演变。结果表明,在进行超塑性变形前,其显微组织表现为扁平状组织,具有大量的小角度晶界,且初始板材具有明显的黄铜织构{110}（112）。在变形过程中发生了晶粒的长大、晶粒形貌的改变、晶粒取向差的增大以及织构的弱化,而且大角度晶界的含量在流动应力到达最大值后开始逐渐增加。同时,对不同阶段的相关变形机制进行了讨论。超塑性变形初始阶段的主要变形机制为位错运动,随着变形的进行而开始发生动态再结晶,晶粒旋转作为晶界滑移的主要协调机制。在超塑性拉伸的最后大应变阶段,晶界滑移是主要的变形机制。     

7075-T651铝合金摩擦塞补焊接头的组织与性能

以2219-T87铝合金为塞棒材料,采用摩擦塞补焊工艺对8 mm厚7075-T651铝合金进行焊接,并对不同工艺参数下接头的成形、微观组织、力学性能等进行观察和测试.结果表明,采用优化的工艺参数可以获得无缺陷的接头,塞棒和母材摩擦界面形成了等轴晶.根据组织形貌可以把摩擦塞补焊接头分成再结晶区、热力影响区、塞棒热力影响区、热影响区、塞棒热影响区和母材6个区,热力影响区组织发生了变形和长大以及沉淀相的溶解和粗化,局部发生了软化,尤其是塞棒热力影响区硬度值最低,在90 ~ 95 HV左右,拉伸试验时无缺陷的接头断裂位置在塞棒区,断裂模式为韧性特征. 摩擦塞补焊接头抗拉强度最高可达343 MPa,断后伸长率最高达7.0%,分别达到母材的63.8%和77.8%.     

A6N01铝合金焊接接头疲劳损伤和断口形貌分析

采用高频疲劳试验机对A6N01铝合金MIG焊接试样进行低周拉伸疲劳试验,研究了A6N01铝合金焊接接头疲劳过程中表面形貌变化和疲劳断裂后的断口形貌。结果表明:随着循环应力的加载,在试样产生裂纹之前,晶界处位错塞积严重,产生永久滑移带,裂纹源萌生于永久滑移带。气孔、夹杂等缺陷处应力集中较大,也容易称为裂纹源。在裂纹扩展过程中,主裂纹对次裂纹的扩展具有屏蔽作用。裂纹在相邻的不同位向的晶粒中扩展时,裂纹扩展方向发生变化。A6N01铝合金焊接接头疲劳断口有较多浅显的韧窝,说明A6N01铝合金焊接接头具有良好塑性。     

Effect of electromagnetic bulging on fatigue behavior of 5052 aluminum alloy

The effect of electromagnetic bulging on the fatigue behavior of the 5052 aluminum alloy was investigated through tensile–tensile fatigue testing. The intriguing finding is that the bulged specimens exhibited enhanced fatigue strength as depicted by maximum stress vs the number of cycles until failure (S–N) curves, by comparison with these original aluminum alloys. Although the fatigue process of the original and budged alloys follows the same mechanism with three distinct steps, namely, crack initiation at a corner of the tested samples, stable crack propagation with typical fatigue striations and finally catastrophic fracture with dimple fractographic features. The typical crack propagation rate vs stress intensity factor range (da/dN–ΔK) curves derived from the spacing of striations reveal a lower crack propagation rate in the bulged specimens. The enhancement of fatigue strength in electromagnetically bulged aluminum alloy is further rationalized in-depth on the basis of strain hardening and dislocation shielding effect.     

The fatigue response and fracture behavior of a spray atomized and deposited aluminum-silicon alloy

In this article the results of a recent study designed to improve our understanding of the cyclic fatigue and fracture characteristics of a spray atomized and deposited hypereutectic aluminum-silicon alloy are presented. Specimens of the alloy were cyclically deformed to failure at ambient temperature under fully reversed total strain amplitude controlled tension-compression loading. The alloy exhibited low cyclic plasticity and fatigue life under total strain amplitude controlled deformation. Cyclic stress amplitude controlled high-cycle fatigue characteristics were established at an elevated temperature (150 °C). The cyclic stress response, high-cycle fatigue life and fracture characteristics of the alloy are compared with a conventional ingot metallurgy processed counterpart and discussed in light of intrinsic microstructural features, nature and magnitude of stress, and ductility of the material.     

2524-T34合金疲劳裂纹的萌生和扩展行为

通过四点弯曲疲劳试验研究2524-T34板材的疲劳性能,借助金相和扫描电镜观察疲劳裂纹的萌生和扩展行为。结果表明:2524合金具有良好的疲劳性能,疲劳强度达到屈服强度的80%以上;疲劳裂纹主要在第二相粒子以及第二相粒子/基体界面萌生,裂纹扩展过程中的偏转与晶界的阻碍有关;相邻晶粒内两个有利滑移面之间的位向差是控制裂纹通过晶界扩展的重要因素。     

焊接气孔缺陷对A7N01铝合金焊接接头腐蚀疲劳性能的影响

在不同环境湿度条件下制备了不同焊缝气孔率的A7N01铝合金焊接接头,并通过条件腐蚀疲劳强度和断口微观形貌研究气孔缺陷对焊接接头腐蚀疲劳性能的影响。结果表明,当焊接环境的湿度由常湿增至70%时,焊缝的平均气孔率由0.07%增大为0.16%,接头的条件腐蚀疲劳强度由110 MPa降为100 MPa,焊接气孔缺陷对A7N01铝合金焊接接头的腐蚀疲劳性能有明显影响。焊缝中的气孔会造成严重的缺口效应,引起应力集中,导致裂纹在气孔处优先萌生,并在应力和腐蚀介质的共同作用下形成沿晶与脆性疲劳条带的混合断裂形貌。