Effect of prior corrosion on short crack behavior in 2024-T3 aluminum alloy

Two thicknesses of dogbone shaped 2024-T3 aluminum alloy specimens were notched and corroded prior to constant amplitude fatigue loading. The purpose of the subject research was to examine and characterize the effects of various levels of prior corrosion on the growth rate of short fatigue cracks. The specimens were notched and exposed to a corrosive environment per one of three defined protocols prior to experimentation. The notch was manually introduced at one edge of the test section of the specimen, which was later corroded to create a more natural site for crack origination. Fatigue crack nucleation was monitored and subsequent crack growth recorded, with results presented in the form of da/dN vs. ΔK curves.     

Effects of stress ratio on fatigue crack propagation properties of submicron-thick free-standing copper films

The dominant mechanics and mechanisms of fatigue crack propagation in ca. 500 nm thick free-standing copper films were evaluated at the submicron level using fatigue crack propagation experiments at three stress ratios, R = 0.1, 0.5 and 0.8. Fatigue cracking initiated at the notch root and propagated stably under cyclic loading. The fatigue crack propagation rate (da/dN) vs. stress intensity factor range (ΔK) relation was dependent on the stress ratio R;da/dN, increases with increasing R. Plots of da/dN vs. the maximum stress intensity factor (K_max) exhibited coincident features in the high-K_max region (K_max ? 4.5 MPa m^1/2) irrespective of R, indicating that K_max is the dominant factor in fatigue crack propagation. In this region, the fatigue crack propagated in tensile fracture mode irrespective of the R value. The region ahead of the fatigue crack tip is plastically stretched by tensile deformation, causing necking deformation in the thickness direction and consequent chisel-point fracture. In contrast, in the low-K_max region (K_max < 4.5 MPa m^1/2), the da/dN vs. K_max function assumes higher values with decreasing R; in this region, the fracture mechanism depends on R. At the higher R value (R = 0.8), the fatigue crack propagates in the tensile fracture mode similar to that in the high-K_max region. On the other hand, at the lower R values (R = 0.1 and 0.5), a characteristic mechanism of fatigue crack propagation appears: within several grains, intrusions/extrusions form ahead of the crack tip along the Σ3 twin boundaries, and the fatigue crack propagates preferentially through the intrusions/extrusions.     

淬火条件对砂铸A356合金疲劳裂纹扩展速率的影响

在相同固溶和时效条件下，选择3种不同温度的水对砂铸A356合金进行了淬火处理，并对这3种不同淬火态下的合金进行了拉伸及疲劳裂纹扩展性能研究。结果表明，随淬火介质温度的降低，淬火冷却速率提高，合金的强度增加，塑性下降；当应力比R较低时，淬火条件对合金门槛区的裂纹扩展有明显影响，降低淬火介质温度可以提高合金的疲劳裂纹扩展阻力。此外，不同淬火态合金的疲劳扩展均明显地表现出与应力比R的相关性，这种相关性可以用裂纹闭合来说明。     

Investigation of Fatigue Crack Propagation in Spot-Welded Joints Based on Fracture Mechanics Approach

In this paper, fatigue crack propagation life of resistance spot welds in tensile-shear specimens is investigated based on the calculation of stress intensity factors and J-integral using three-dimensional finite element method. For comparison, experimental works on 5083-O aluminum alloy spot-welded joints have been carried out to verify the numerical predictions of fatigue crack propagation of welded joints. A lot of analyses have been performed to obtain stress intensity factors and J-integral in tensile-shear specimens of spot-welded joints by using commercial software ANSYS. These gathered data have been formulated by using statistical software SPSS. The results of fatigue propagation life and predicted fatigue crack path revealed very good agreement with the experimental fatigue test data and photograph of cross-section of the fatigued spot-weld specimens.     

Rotary bending fatigue behavior of A356 –T6 aluminum alloys by vacuum pressurizing casting

Vacuum pressurizing casting technique, providing better mould filling and inter-dendritic feeding, can reduce the porosity greatly in cast aluminum alloys, and improve the fatigue properties. The rotary bending fatigue properties of A356-T6 alloys prepared by vacuum pressurizing casting were investigated. The S-N curve and limit strength 90 MPa under fatigue life of 107 cycles were obtained. The analyses on the fatigue fractography and microstructure of specimens showed that the fatigue fracture mainly occurs at the positions with casting defects in the subsurface, especially at porosities regions, which attributed to the crack propagation during the fatigue fracture process. Using the empirical crack propagation law of Pairs-Erdogon, the quantitative relationship among the initial crack size, fatigue life and applied stress was established. The fatigue life decreases with an increase in initial crack size. Two constants in the Pairs-Erdogon equation of aluminum alloy A356-T6 were calculated using the experimental data.     

含有第二相的高强铝合金疲劳模型

基于疲劳裂纹尖端的应力和应变以及高强铝合金中不同尺度第二相性态对其延性的影响，建立了高强铝合金中粗大第二相、中间尺度第二相以及细小时效强化相性态与其疲劳裂纹扩展速率之间的多元非线性关系模型。结果表明：对于2024铝合金的疲劳扩展速率，该模型的预测趋势与他人的实验研究结果吻合良好。同时借助于对该模型的理论分析，提出了在确保高强铝合金强度不降低的前提下降低其疲劳裂纹扩展速率的优化方案。     

Fatigue life prediction of aviation aluminium alloy based on quantitative pre-corrosion damage analysis

A new method of quantitative pre-corrosion damage of aviation aluminium (Al–Cu–Mg) alloy was proposed, which regarded corrosion pits as equivalent semi-elliptical surface cracks. An analytical model was formulated to describe the entire region of fatigue crack propagation (FCP). The relationship between the model parameters and the fatigue testing data obtained in the pre-corroded experiments, crack propagation experiments and S–N fatigue experiments was discussed. The equivalent crack sizes and the FCP equation were used to calculate the fatigue life through numerical integration based on MATLAB/GUI. The results confirm that the sigmoidal curve fitted by the FCP model expresses the whole change from Region I to Region III. In addition, the predicted curves indicate the actual trend of fatigue life and the conservative result of fatigue limit. Thus, the new analytical method can estimate the residual life of pre-corroded Al–Cu–Mg alloy, especially smooth specimens.     

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.     

Al-6Mg-0.8Zn-0.5Mn-0.2Zr-0.2Er合金高强耐损伤工艺与微观组织研究

以Al-6Mg-0.8Zn-0.5Mn-0.2Zr-0.2Er合金为基础,对该材料的冷轧态,温轧态,完全退火态进行拉伸测试和疲劳裂纹扩展速率测试。运用电子背散射衍射(EBSD),透射电镜(TEM),扫描电镜(SEM)对合金的原始组织、疲劳断口、裂纹扩展路径进行观察,研究微观组织对材料拉伸性能及疲劳裂纹扩展速率的影响。结果表明:温轧态屈服强度高,裂纹扩展抗力大,实现了高强高耐损伤性能的匹配。这主要是由于温轧态轧制过程中发生动态回复,位错缠结规整化,具有较多的亚晶界,该种组织模式对材料的屈服强度和疲劳裂纹扩展抗力均有提高。     

AZ91D+xNd压铸镁合金拉伸和疲劳断裂模式

压铸AZ91D镁合金中添加稀土Nd后,生成了新的稀土化合物Al11Nd3相,合金显微组织得到细化,力学性能得到提高,但是当Nd的添加量达到1.5%时,合金的力学性能又有所下降。AZ91D xNd合金拉伸断口具有准解理、撕裂棱及韧窝等韧性特征,但其断裂方式仍属于脆性断裂。含Nd的AZ91D合金疲劳裂纹萌生于试样的表面或亚表面下的孔隙或夹杂处,疲劳裂纹扩展区为平面状断面,含1.0%Nd合金的疲劳辉纹最为清晰,疲劳断口主要表现为脆性与韧性的混合断裂方式,局部存在准解理台阶与河流花样以及穿晶型和沿晶型二次裂纹。     

激光冲击TC17钛合金疲劳裂纹扩展试验

为研究激光冲击强化对钛合金试件疲劳性能的影响,在标准试件的裂纹扩展路径上设计了全强化和间隔强化两种不同的强化方案,研究激光冲击强化对试件疲劳寿命和裂纹稳定扩展时速率的影响规律,利用有限元数值模拟和X射线残余应力测试获得了试件的残余应力场分布状态,并对比分析了试件的断口形貌和微观组织特征。结果表明:相比于未强化试件,激光冲击强化后试件的平均疲劳寿命分别提高了2.14倍和1.90倍,两种不同的冲击强化方法分别降低钛合金试件的裂纹扩展速率24%和15%。间隔强化后试件表面产生-512 MPa的最大残余压应力,裂纹扩展的C′值为-7.3,m值为2.6,而强化间隔区引入最大值为82.4 MPa的残余拉应力,裂纹扩展速率急剧升高,C′值减小至-13.6,m值为8.0。当裂纹扩展到强化区时,扩展速率再次降低,激光冲击强化对TC17钛合金疲劳裂纹扩展有显著的抑制作用。     

Fatigue crack growth behavior of laser-annealed IN 718 alloy in hydrogen

The effect of hydrogen embrittlement on the fatigue crack growth of IN 718 plate and laser-annealed specimens in hydrogen containing environment were investigated. Although the differences in tensile strength and impact toughness between solution-annealed (S) and aged (A) IN 718 specimens were significant, the experimental results indicated that both specimens within the low ΔK regime exhibited a similar fatigue behavior. As the ΔK increased above 30 MPa , the solution-annealed specimen revealed a higher fatigue crack growth rate (FCGR) than the aged one. In general, the IN 718 alloy had a low sensitivity to hydrogen-enhanced fatigue crack growth, independent of hydrogen sources. Residual compressive stresses ahead of the crack tip were responsible for the improved resistance to fatigue crack growth in a laser-annealed specimen. For alloys with similar strength, IN 718 alloy trapped a huge amount of hydrogen in the matrix showing a less susceptibility to hydrogen-enhanced fatigue crack growth in comparison with the maraging steel. Additionally, fatigue-fractured appearance near crack initiation sites reveals quasi-cleavage fracture in embrittled specimens.     

Fatigue properties of rolled AZ31B magnesium alloy plate

Fatigue strength, crack initiation and propagation behavior of rolled AZ31B magnesium alloy plate were investigated. Axial tension-compression fatigue tests were carried out with cylindrical smooth specimens. Two types of specimens were machined with the loading axis parallel (L-specimen) and perpendicular (T-specimen) to rolling direction. Monotonic compressive 0.2% proof stress, tensile strength and tensile elongation were similar for both specimens. On the other hand, monotonic tensile 0.2% proof stress of the L-specimen was slightly higher than that of the T-specimen. Moreover, monotonic compressive 0.2% proof stresses were lower than tensile ones for both specimens. The fatigue strengths of 107 cycles of the L- and T-specimens were 95 and 85 MPa, respectively. Compared with the monotonic compressive 0.2% proof stresses, the fatigue strengths were higher for both specimens. In other words, the fatigue crack did not initiate and propagate even though deformation twins were formed in compressive stress under the cyclic tension-compression loading. The fatigue crack initiated at early stage of the fatigue life in low cycle regime regardless of specimen direction. The crack growth rate of the L-specimen was slightly lower than of the T-specimen. Consequently, the fatigue lives of the L-specimen were longer than those of the T-specimen in low cycle regime.     

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.     

拉-拉载荷下2195-T8铝锂合金在N2O4中的预腐蚀疲劳研究

液体导弹在长期加注贮存的状态下,弹体与贮箱结构常因腐蚀损伤从而导致疲劳裂纹的产生乃至断裂等问题。采用疲劳寿命测试、扫描电镜以及能谱分析等方法,研究了2195-T8铝锂合金在N₂O₄中预腐蚀180d后的疲劳裂纹萌生、扩展和断裂机制,并与未腐蚀试样进行对比。结果表明：2种环境下试样的疲劳极限为145、118MPa,循环应力降低比值约为18.62%;试样在预腐蚀的过程中,由于形成“闭塞区”,同时与富铜相粒子形成原电池,进一步加速腐蚀历程,形成多源裂纹萌生的特征,且更易从非金属夹杂区域起裂;受到晶粒间的位错、堆积等因素的影响,发现了垂直于疲劳辉纹、穿越大晶粒及途经小角度晶界的二次裂纹;2种环境中的疲劳瞬断区的断口形貌呈现出典型的沿晶韧窝和韧性断裂的特征。     

加Ti方式对ZL101A合金疲劳裂纹扩展性能的影响

在工业电解槽上用不同的方式生产出电解Al-Si-Ti合金和电解低钛铝基合金,并以这两种合金分别制备ZL101A合金试样,在MTS810型材料试验机上测量疲劳裂纹扩展速率。采用拟合试验数据代表点的新方法处理数据,得到Paris公式中两个重要参数和疲劳裂纹扩展门槛值。对比分析表明,电解低钛铝基合金制备的ZL101A合金具有较好的抗疲劳裂纹扩展性能。微观分析说明,产生差异的原因在于电解Al-Si-Ti合金中含铁量较高。     

High-cycle fatigue and fracture behaviours of SLM AlSi10Mg alloy

The high-cycle fatigue and fracture behaviours of the selective laser melting (SLM) AlSi10Mg alloy were investigated. Flat specimens were designed directly in the shape required for the fatigue tests under pulsating loading in tension (R=0, R is the dynamic factor). The fatigue–life (S–N) curves were modelled with a conditional Weibull's probability density function, where the real-valued genetic algorithm (GA) and the differential ant-stigmergy algorithm (DASA) were applied to estimating the needed Weibull's parameters. The fractography of the fatigue specimens showed that the fatigue cracks initiated around the surface defects produced by SLM and then propagated in an unstable manner. However, the presence of large SLM defects mainly influenced the crack initiation period and did not have a strong influence on the crack propagation. The obtained experimental results present a basis for further investigation of the fatigue behaviour of advanced materials and structures (e.g. cellular metamaterials) fabricated by additive manufacturing (AM). Especially, in the case of two-dimensional cellular structures, the cross-section of cellular struts is usually rectangular which corresponds to the specimen shape considered in this work.     

LF2铝合金搅拌摩擦焊接头的疲劳特性

对LF2铝合金搅拌摩擦焊接头的疲劳特性进行了研究，建立了焊接头的S-N曲线。疲劳试验结果表明，搅拌摩擦焊接头表现出良好的疲劳性能，疲劳寿命N=10^6次的疲劳强度值约为59～65MPa。搅拌摩擦焊接头具有细小的等轴晶粒和狭窄的热影响区，阻碍了滑移带的形成和裂纹的扩展，从而提高了接头的疲劳性能。疲劳断口分析显示，随着驻留滑移带的扩展逐渐萌生裂纹，在交变应力作用下最终导致失效。     

超声滚压强化对2D12铝合金疲劳性能的影响

通过对比分析2D12铝合金超声强化试样与抛光试样的疲劳性能,对表面硬化、残余应力和疲劳寿命进行了研究。残余压应力和梯度纳米晶结构对改善构件的疲劳性能起着至关重要的作用,可以有效减少疲劳裂纹的萌生和扩展。实验及分析预测结果表明,试样经超声强化后,轴向压应力提高了55%,显微硬度提高了20%。通过对表面强化规律的研究,为2D12铝合金的强化工艺和疲劳性能的影响提供了指导。     

Experimental Investigation and Finite Element Analysis on Fatigue Behavior of Aluminum Alloy 7050 Single-Lap Joints

The fatigue behavior of single-lap four-riveted aluminum alloy 7050 joints was investigated by using high-frequency fatigue test and scanning electron microscope (SEM). Stress distributions obtained by finite element (FE) analysis help explain the fatigue performance. The fatigue test results showed that the fatigue lives of the joints depend on cold expansion and applied cyclic loads. FE analysis and fractography indicated that the improved fatigue lives can be attributed to the reduction in maximum stress and evolution of fatigue damage at the critical location. The beneficial effects of strengthening techniques result in tearing ridges or lamellar structure on fracture surface, decrease in fatigue striations spacing, delay of fatigue crack initiation, crack deflection in fatigue crack propagation and plasticity-induced crack closure.