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.     

7075 铝合金强化固溶T76处理后的拉伸与剥落腐蚀性能

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%.     

7050-T7451铝合金搅拌摩擦焊接头组织和性能与疲劳断裂

文中主要对7050-T7451铝合金搅拌摩擦焊焊接接头组织性能和疲劳断裂进行研究,对焊件进行金相组织、硬度、疲劳试验,并根据试验结果进行分析。试验结果表明,焊核区和热力影响区组织有明显的分界,整个接头表面和截面的不同区域的组织有明显的不同,焊核区经历高温热循环,并且受到强烈的搅拌作用,发生了显著的动态再结晶,组织均匀细小,没有明显的方向性。热力影响区组织在搅拌摩擦焊接过程中主要受到热循环作用的影响,同时一定程度上受到了机械外力的作用,产生了较小的塑性变形,但储能不够,最终未出现动态再结晶。热影响受到热循环的作用,组织比母材要粗大,但没有发生明显塑性变形,仍具有母材纤维组织的特点。硬度试验的结果表明,母材区和焊核区的硬度比较大,而热影响区的硬度偏低,热力影响区的硬度在它们之间。通过对疲劳试验分析,应力水平为200 MPa时,试样在前进侧热影响区发生断裂,断口的表面较为粗糙。应力水平为250 MPa时,试样在焊核区发生断裂,断口表面较为平整。应力水平为300 MPa时,试样在母材处发生断裂,断口表面十分平整。创新点： 通过搅拌摩擦焊工艺形成的7050-T7451铝合金焊接接头,成形良好,技术优势突出,适用于航天航空等多个重要领域。     

温度与保温时间对2519A铝合金高温力学性能的影响

利用高温拉伸力学性能测试、扫描电镜与透射电镜等分析手段对2519A铝合金在不同温度与保温时间下的高温力学性能进行研究。结果表明：合金在保温10 min后进行拉伸,从室温至400℃,随着温度的升高,抗拉强度从471 MPa下降至55.5 MPa,屈服强度从440.3 MPa降至50.3 MPa,延伸率由11.6%提高至21.3%。300℃时,随保温时间的延长,合金的抗拉强度先由171.6 MPa下降至151.4 MPa,屈服强度由139.4 MPa降至130.5 MPa,1 h后基本上稳定不变。高温条件下,该合金力学性能的下降主要是由于析出相的粗化与转变引起的。     

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.     

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。     

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.     

固溶温度对7075铝合金组织及高周疲劳性能的影响

通过对7075铝合金进行不同温度（450、465、480和495 ℃)的固溶处理,研究了固溶温度对该合金的硬度、室温拉伸性能及高周疲劳性能的影响,并用光学显微镜和扫描电镜对合金显微组织及疲劳断口进行观察。结果表明,随着固溶温度的升高,合金组织发生不同程度的静态再结晶和晶粒长大,合金硬度和拉伸强度均先升高后降低,480 ℃固溶处理后达到最高;疲劳极限随着固溶温度的升高先降低后升高,495 ℃固溶处理后达到最高。疲劳裂纹主要起源于粗大残留相处,扩展过程中产生的二次裂纹可降低裂纹扩展的驱动力,进而降低合金的裂纹扩展速率,提高合金疲劳性能。     

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。     

6082-T6铝合金搅拌摩擦焊组织演变与力学性能

通过透射电子显微镜、扫描电子显微镜、拉伸试验机和显微硬度计对6082-T6铝合金搅拌摩擦焊接头焊缝区组织演变和力学性能进行分层研究. 结果表明,在焊核区上层,材料发生塑性变形,晶格畸变能增加,为降低能量,大量的位错集聚成亚结构边界发生动态回复. 同时在焊接热循环的作用下发生动态再结晶,导致焊缝区上层晶粒细小. 在焊核区下层,主要受到搅拌针搅拌作用,轴肩产热通过扩散过程传递到下层的热量减少,发生动态回复和动态再结晶程度低于焊缝上层,晶粒粗大. 前进侧和后退侧热影响区均出现棒状β′沉淀相. 对应焊缝上、下两层硬度都呈“W”形分布,焊缝上层硬度高于焊缝下层硬度,最小值出现在前进侧. 沿着焊缝长度方向上层和下层的抗拉强度分别为205,186 MPa,呈降低趋势,为韧性断裂.     

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.     

6063铝合金双道次热变形微观组织演变

采用Gleeble-1500热模拟试验机对6063铝合金进行双道次热轧试验,分析了合金在变形温度为300~500 ℃,应变速率为0.001~0.1 s^-1,道次间停留时间10~90 s时的流变应力和微观组织。结果表明:随着道次间停留时间增长,第二道次屈服应力减小;温度与道次间停留时间对合金的静态软化率有较大的影响。低温大应变速率短道次间停留时间下试样的强化相较多,其形貌为长条状与圆形;高温低应变速率长道次间停留时间下试样的强化相数量有所减少,其形貌以圆形为主。通过能谱分析可知,试样中的强化相以AlFeSi为主,长条状强化相为6 μm左右,圆形强化相尺寸约2 μm。     

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.     

轧制态6082-T6铝合金的热压缩力学行为及微观组织分析

采用热模拟试验机对轧制态6082-T6铝合金进行热压缩试验,分析了合金在变形温度100~400 ℃,应变速率0.01 s^-1条件下的流变应力,对不同温度热变形的微观组织进行了表征。结果表明,轧制态6082铝合金的力学性能受变形温度和轧制方向的影响。变形过程中应力呈现负的温度敏感性,即随着变形温度升高,应力不断下降。合金表现出明显的力学性能各向异性,压缩强度在与轧制方向呈0°和90°较高,45°方向强度较低。经过热压缩变形后,与轧向呈不同方向的6082-T6铝合金的晶粒组织均沿着剪切力方向发生扭曲,同时,变形温度对晶粒组织的演变影响不大。随着变形温度的升高,合金基体内的位错密度明显下降,析出相发生粗化。