An Investigation into the Effect of Normal Load Frequency on Fretting Fatigue Behavior of Al7075-T6

Most previous studies on fretting fatigue have been accomplished under constant normal loading and less attention has been paid to cyclic normal loading. An innovative test apparatus was specially designed and manufactured for fretting fatigue tests under cyclic loading in this work and the fretting fatigue behavior of Al7075-T6 was investigated at different normal load frequencies. A finite element model was developed to study the effect of normal load frequency on the contact stress distribution. It was found that the cyclic normal load has a more damaging effect on fretting fatigue life compared to constant normal load, particularly at lower frequencies. The results showed that at the normal load frequency of f = 1 Hz, fatigue life decreased by 52% in the high cycle fatigue regime and 28% in the low cycle fatigue regime. The experimental results also indicated that at the normal load frequency of 80 Hz, the fretting fatigue life converged to its corresponding life under constant normal load condition. The fracture surface and the fretting area of the specimens were examined using both optical and scanning electron microscopy (SEM). The experimental observations showed that the dominant partial slip condition with a wider slip region compared to constant normal loading, severe delamination, and higher oxidation rate due to the normal load release at each cycle, are the most important reasons for significant reductions in fretting fatigue life, under cyclic normal loading, especially for low normal load frequencies.     

Numerical Investigation into the Effect of Contact Geometry on Fretting Fatigue Crack Propagation Lifetime

Fretting fatigue is a phenomenon in which two contact surfaces undergo a small relative oscillatory motion due to cyclic loading. There is a need to analyze the effects of contact geometry on crack propagation under fretting fatigue conditions. In this investigation, a finite element modeling method was used to study the effects of different contact geometries along with crack–contact interaction on crack propagation lifetime. Different contacts geometries—that is, cylindrical on flat and flat on flat—along with different contact span widths were analyzed. In addition, the effects of different contact spans on stress distribution at the contact interface were investigated. The computed crack propagation life was compared with experimental results. It was found that the crack initiated near the contact trailing edge for all contact geometries, which agreed with experimental observations. In terms of crack propagation for different contact spans, the fretting fatigue life for a two-based cylindrical pad was shorter than that for a two-based flat pad. By increasing the contact span width for both flat and cylindrical pads, the crack propagation lifetime increased. A comparison between the experimental and numerical results demonstrated a difference of about 18% in crack propagation lifetime.     

Fretting Fatigue Life Estimation of Al 7075-T6 Using Plain Fatigue Test

Fretting fatigue occurs in many engineering applications. Fretting fatigue life is estimated by experiment, which is tedious and requires special equipment and instrumentation. In this study, we attempt to introduce a method for estimation of fretting fatigue life from plain fatigue (normal fatigue without fretting) experiments. The method employs the critical distance theory for estimation of fretting fatigue life of Al7075-T6 under rotary bending loading. The approach uses the Fatemi-Socie parameter (FSP) as a multiaxial criterion to account for the stress multiaxiality on focus path. A comparison between the predictions of the new approach with the experimental results shows that the approach is quite accurate for low stress or high cycle fatigue regimes but for high stresses it is slightly conservative. This method considers only elastic behavior for materials and two characteristic diagrams that are obtained simply by testing two simple notched specimens under plain fatigue conditions. The method is therefore an applicable approach that can be used in the context of finite fretting fatigue life estimation with no need for fretting fatigue tests.     

微动疲劳寿命的估算方法研究

着重分析了零构件由于微动磨损而造成的疲劳失效机制 ,说明了在这种微动疲劳模式下疲劳寿命的组成情况 ,用门槛值应力公式估算了当磨蚀坑根部萌生扩展性裂纹时蚀坑的临界深度尺寸 ,并分析了微动裂纹尖端的应力强度因子 ,得出了计算微动裂纹萌生尺寸的表达式 ,最后用上述方法计算了螺纹联接件的微动磨损寿命与裂纹萌生尺寸 ,用局部应力应变法计算了微动裂纹的萌生寿命 ,所得到的估测寿命与试验值相符 ,由此可见 ,该微动疲劳寿命的估测方法是合理的、有效的     

Fretting fatigue behavior of Al7075-T6 at sub-zero temperature

In some fretting fatigue applications, such as aero industry, the temperature may drop well below −50 °C Fretting fatigue behavior of aluminum alloy Al7075-T6 is investigated at temperatures of 24, 0, −25 and −50 °C in this work. The results show that (i) normal fatigue life increases considerably at sub-zero temperatures up to around 85% for low working stresses and reduces to about 40% for higher working stresses; (ii) fretting fatigue life at sub-zero temperatures rises significantly up to around 220% for low working stresses and reduces to about 50% for higher working stresses; (iii) ultimate strength of material changes from −15% to 15% under the fretting fatigue test conditions; and finally (iv) some parameters such as mechanical properties and fatigue behavior of material at low temperatures, contact load relaxation, crack closure, oxidation and some unknown sources can be thought to be responsible for fretting fatigue behavior of Al7075-T6 at sub-zero temperatures.     

Fretting Wear Behavior of Laser Peened Ti-6Al-4V

This work deals with the influence of laser peening on the fretting wear behavior of Ti-6Al-4V. Laser peening was carried out on Ti-6Al-4V. The laser-peened surface was characterized by transmission electron microscopy. Surface roughness, nanoindentation hardness, residual stress, and tensile properties of the material in both laser-peened and unpeened conditions were determined. Fretting wear tests were conducted at different normal loads using a ball-on-flat contact geometry. Laser peening resulted in the formation of nanocrystallites on the surface and near-surface regions, increased hardness, and compressive residual stress. Laser peening did not affect the tensile properties and surface roughness significantly. There was no considerable difference between the values of the tangential force coefficient of laser-peened and unpeened samples. The fretting scar size, wear volume, and wear rate of laser-peened specimens were lower than those of unpeened samples. This may be attributed to an increase in surface hardness due to strain hardening and grain refinement at the surface and near-surface regions, higher compressive residual stress, and higher resistance to plastic deformation of laser-peened samples.     

On the application of a micromechanical small fatigue crack growth model to predict fretting fatigue life in AA7075-T6 under spherical contact

This work presents a method for assessing the fretting fatigue life by estimating the fatigue crack growth rate from the regime of microcracks to the final failure, which is achieved using a two-threshold small fatigue crack growth model. The propagation thresholds are associated with the interaction of the "monotonic plastic zone" and the "cyclic plastic zone" with the microstructure of the material. The predicted fatigue life and the estimated non-propagating cracks agree very well with the experimental fretting fatigue tests with spherical contact in 7075-T6 aluminium alloy.     

喷丸强化对新型7055-T7751铝合金疲劳性能的影响

对7055-T7751新型铝合金表面进行了陶瓷丸喷丸强化处理,采用X射线衍射仪、表面轮廓仪、扫描电子显微镜、显微硬度计等研究了喷丸强度、喷丸覆盖率等工艺参数对铝合金表面残余应力场、表面粗糙度、表面损伤及表面加工硬化和疲劳性能的影响。结果表明:优化工艺参数下的喷丸强化能够显著提高该铝合金的疲劳性能,并不是喷丸强度或喷丸覆盖率越高强化效果越好,而是存在合理的喷丸强化参数范围,在优化条件下铝合金可以获得良好的综合表面完整性,疲劳断裂抗力最高;确定的优喷丸参数为喷丸强度0.15mm,覆盖率100%,以此参数强化处理的7055-T7751铝合金的疲劳寿命是基材的2.7倍。     

Effect of Cold Rolling on the Fretting Wear Behavior and Mechanism in Inconel 600 Alloy

The fretting test was carried out using an SRV IV fretting test rig in order to investigate the fretting wear behavior and mechanism in Inconel 600 alloy at room temperature. The materials were rolled to different reductions before the test. The effect of cold rolling on the friction coefficient and wear volume was subsequently investigated. The surface and cross-sectional morphologies of the wear scar were studied by scanning electron microscopy (SEM), laser scanning confocal microscopy (LSCM), and electron back-scattering diffraction (EBSD). The results indicated that the cold rolling had a different effect on wear behavior in different slip regimes. In the stick regime, cold rolling strongly decreased the wear volume, although it did not affect the friction coefficient. The 25% rolled specimen had the minimum wear volume. The mechanisms of as-received and 50% rolled specimens were delamination and oxidation wear, whereas for the 25% rolled specimen, cracking was the main wear mechanism. In the gross slip regime, cold rolling had little effect on the friction coefficient or wear volume. The fretting wear process gave rise to a decrease in the Σ3 grain boundary, an increase in local misorientation, and a change in the crystal orientation.     

焊后涂装工艺对6063-T6铝合金MIG焊T型接头组织和性能的影响

采用金属熔化极惰性气体保护(MIG)焊制备6063-T6铝合金T型接头,之后对T型接头进行涂装,研究了焊后涂装工艺对接头组织与性能的影响。结果表明:涂装工艺对接头各区域晶粒形态和尺寸没有影响,涂装后热影响区中针状β″相析出量明显增加;焊后涂装可以显著提高接头的力学性能,抗拉强度较涂装前的提高了13%,热影响区的显微硬度较涂装前的提高了18.8%;涂装完成前,接头最薄弱区域为热影响区,而涂装完成后,最薄弱区域为焊缝处;涂装后镁、硅原子在热影响区富集形成溶质原子富集区(GP区),同时针状β″相析出量的增加干扰位错运动,导致热影响区的硬度大幅提高,而使焊缝处成为接头的最薄弱区域。     

Investigation on the Fretting Wear Behavior and Mechanisms of Alloy 690TT during the Transformation from Mixed Regime to Partial Slip Regime Induced by Elevated Temperature

Fretting wear of Alloy 690TT can occur in the steam generator of a nuclear power plant, in which the interfacial conditions are changed as the temperature varies. In this study, the gradual transformation from the mixed fretting regime (MFR) to the partial slip regime (PSR) occurred with an increase in test temperature. Correspondingly, there was a competition in wear modes due to the formation of a nanostructured tribologically transformed structure (TTS), presence of delamination cracking, nucleation of fatigue cracks, and oxidation. Delamination within the TTS dominated first. As the area of TTS and the plastic deformation region was reduced, fatigue cracks began to initiate. Oxidation was accelerated by an increase in the test temperature, and that effect resulted in reduced wear volume of Alloy 690TT in the MFR.     

Ti-6Al-4V燕尾榫结构微动疲劳裂纹萌生及扩展行为研究

针对Ti-6Al-4V钛合金燕尾榫连接结构在不同载荷下的微动疲劳现象,采用榫形微动疲劳试验进行研究,并对裂纹萌生扩展、微动磨损及断口进行分析。结果表明,微动疲劳使构件疲劳寿命显著降低约70%;疲劳载荷对微动裂纹扩展的影响比对裂纹萌生的影响更大;微动疲劳裂纹起始于接触面边缘,与接触表面约成45°角,裂纹扩展到60~150μm后转向与接触表面垂直;微动疲劳断口形貌表面在微动磨损区具有多个裂纹源点,但只有一个主裂纹形成。     

不锈钢外板对5A06铝合金板材液压胀形行为的影响

薄壁曲面铝合金零件整体液压成形时,易发生起皱和破裂缺陷,探讨通过施加外层板能抑制缺陷发生的机理。采用5A06铝合金内层板材和1Cr18Ni9Ti不锈钢外层板材,对双层板液压胀形行为进行研究。通过塑性理论分析板材液压胀形屈服半径,讨论经向摩擦力及法向压力对板材应力大小的影响;利用数值模拟给出内层板的应力、应变分布;通过双层板液压胀形试验,对比单层板和双层板条件下,铝合金内层板极限胀形高度、极限应变,分析双层板的变形协调性。结果表明:通过施加不锈钢外层板,减小了5A06铝合金内层板顶部位置面内的双向拉应力,减小了内层板变形区应力、应变梯度,使胀形变形更加均匀,胀形高度提高32%,顶部极限应变提高51.7%,极限应变显著提高。