7075-T651铝合金薄壁管件多轴低周疲劳行为及寿命预测

针对航空铝合金多轴疲劳失效问题,对7075-T651铝合金薄壁管件进行不同加载条件下的拉扭复合疲劳实验。结果表明:随等效应力幅的降低,多轴疲劳寿命增加;等效应力恒定时,寿命随应力幅比的升高而增加;拉扭相位差对寿命影响较小。高应力幅下材料在轴向和扭向以软化为主,低应力幅下硬化和软化交替出现。宏观断口平台区随应力幅比的增加而逐渐减小,微观断口呈现管壁外侧的多裂纹源特征,扩展区可以观察到疲劳条带和二次裂纹,瞬断区出现混合型韧窝。提出基于Basquin准则的改进模型,得到较好的寿命预测效果,寿命预测值均位于两倍分散带内。     

无铅焊料Sn-3.8Ag-0.7Cu的低周疲劳行为

测量了Sn-3.8Ag-0.7Cu无铅焊料试样的循环滞后回线、循环应力响应曲线、循环应力-应变和应变寿命关系,研究了焊料在总应变幅控制下的低周疲劳行为结果表明:该焊料合金在总应变幅较高(1%)时发生连续的循环软化,而在总应变幅较低(≤0.4%)时则表现为循环稳定.线性回归分析表明,该焊料的低周疲劳寿命满足Coffin-Manson经验关系式,由此给出了焊料在室温下的低周疲劳参数.采用扫描电镜观测和分析了焊料在疲劳前后的组织特征.     

菱形加载路径下35CrMoA钢的微动疲劳行为EI北大核心CSCD

采用MTS809拉扭复合疲劳试验机、扫描电镜(SEM)研究了接触应力为150MPa时35CrMoA合金钢在菱形加载路径下微动疲劳性能。结果表明:随着等效应力幅值的增加,材料的软化、硬化效果更加明显;剪应力-剪应变滞后回线的面积增大;裂纹萌生源区的面积减小,瞬断区面积与总断面面积的比例增加,瞬断区的撕裂也越严重。微动磨损使表面塑性枯竭,从而形成疲劳裂纹源。     

500MPa级针状铁素体钢的低周疲劳行为

采用光滑圆柱疲劳试样,通过对500MPa级针状铁素体钢进行轴向总应变控制模式的室温低周疲劳实验,研究了实验钢的循环应力-应变行为、应变-寿命特性及循环应力响应。结果表明:当总应变幅为临界应变幅时(Δεt/2=0.35%),循环一开始就进入饱和状态,应力幅值保持不变;当总应变幅低于临界应变幅时(0.2%≤Δεt/2<0.35%),实验钢表现出循环软化特性;当总应变幅高于临界应变幅时(0.35%<Δεt/2≤0.6%),实验钢先表现出循环硬化,达到循环饱和后又表现出循环软化特性。疲劳断口的SEM分析表明,疲劳裂纹通常萌生于试样一侧的表面,具有多源性,且裂纹的扩展符合Laird的塑性钝化机制。     

60Si_2Mn钢的低周拉扭复合微动疲劳特性

测量60Si_2Mn钢在拉扭复合载荷作用下的低周微动疲劳特性,研究了不同轴向循环拉伸应力幅值对微动疲劳寿命、循环软化特性以及摩擦磨损表面和断口形貌的影响.结果表明,随着循环拉伸应力幅值的提高,60Si_2Mn钢的微动疲劳寿命降低幅度不同,发生循环软化的时期不断提前,完成循环软化的疲劳周期也不断缩短。同时,微动摩擦副产生的氧化物磨屑对微动磨损性能有重要影响,在疲劳前期加剧摩擦磨损,在疲劳后期减轻摩擦磨损。微动疲劳裂纹源形成于试样发生微动摩擦磨损的表面,并出现疲劳台阶。在扭矩产生的切向剪切应力作用下,疲劳裂纹沿着与轴向45°角的方向扩展,最终在断口上留下显著的舌状凸起,拉应力的幅值越大舌状凸起越明显。     

ZTC4（Ti-6Al-4V）铸造钛合金的室温低周疲劳行为

研究了ZTC4钛合金应变控制的室温低周疲劳行为,对循环应力-应变和应变疲劳寿命数据进行了分析,通过双对数线性回归处理,得出了Manson-Coffin处理模型的疲劳参数。结果表明：ZTC4钛合金总应变幅在0.6%～0.8%时,材料存在轻度循环软化的现象;总应变幅为0.4%～0.5%时,循环初期表现出循环硬化的现象,而后循环软化。合金的疲劳裂纹萌生于试样表面,裂纹扩展区存在明显的疲劳条带,合金疲劳断口呈现韧性断裂特征。     

10CrNiMo结构钢低周疲劳过程中的应变滞后特性

在6级轴向逐级增加的系列恒应变幅(0.3%~1.0%)控制下,室温空气中,采用光滑圆形横截面试样,研究了10CrNiMo结构钢在低周疲劳作用下的应力-总应变及应力-塑性应变的滞后回线特性。结果表明:在小应变幅(0.3%~0.4%)控制下,虽然弹性应变占绝对优势,但塑性应变并不为零,且逐级增长;而在大应变幅(0.6%~1.0%)控制下,塑性应变增长较快,并逐渐占主导地位。无论应变幅大小,只须几个循环,材料便进入稳定状态,而初始循环与失稳循环却表现出不稳定的特征。     

镍基高温合金GH4169的热机械疲劳行为

在不同温度区间、不同条件下进行GH4169合金的热机械疲劳实验测试其热机械疲劳数据,研究了这种合金的热机械疲劳行为。结果表明：GH4169合金在热机械条件下的迟滞回线具有明显的拉压不对称性;同相位时材料承受压应力,反相位时承受拉应力。拉应力,是影响疲劳寿命的主要因素。应变幅较高时GH4169合金出现平均应力松弛,在高温半周为先循环软化后循环稳定,在低温半周始终趋于循环稳定。     

拉-压及拉-扭载荷下6063合金的疲劳行为

对6063锻造铝合金进行了不同应力幅值下拉-压及拉-扭复合疲劳试验,并用透射电子显微镜观察了疲劳失效试样的位错结构。结果表明:在循环加载过程中,循环硬化占据主要地位,循环硬化的速率和程度对应力幅值和加载路径有依赖性;相同应力幅值下,试样在拉-扭复合加载下失效比拉-压失效形成更为复杂的位错结构,且位错密度更高;位错之间及位错与析出相的交互作用是材料发生循环硬化的主要原因,循环硬化程度越高,疲劳寿命越短。     

800MPa级低合金高强度钢的循环软硬化特性

在不同应变级别控制下,研究了800MPa级低合金高强度钢10CrNiSMoV轴向加载低周循环软硬化特性,研究结果表明：应变加载级别不同,材料表现出不同的循环软硬化特性,当应变幅在0．4％～1．0％范围变化时,材料表现出循环软化的特性,且应变幅越大,循环软化速率越高;当应变幅在0．30％-0．40％范围变化时,材料表现出先硬化,再趋于循环饱和,再轻微循环软化直至断裂的特性。采用透射电镜观察了不同应变级别下试样断口的位错形态,用位错理论解释了产生上述现象的原因。     

Evaluating a strain energy fatigue method using cyclic plasticity models

For the development of constitutive equations that describe the behaviour of materials under cyclic plastic strains, different kinds of formulations can be adopted. Recently, an energy‐based fatigue damage parameter has been developed to present energy‐fatigue life curves using a calculation of the total strain energy. In this study, the damage criterion is examined by calculation of the plastic strain energy from stress–strain hysteresis loops in the cyclic plasticity models under condition of multi‐axial fatigue. These cyclic plasticity models are the Garud multi‐surface model and the Chaboche nonlinear kinematic hardening model. The models are briefly explained and the general features of their computational procedure are presented. Then, the hysteresis loops of these models will be obtained and the fatigue lives are predicted and compared to experimental data by the ratio of predicted life to experimental life. Consequently, a weighting factor on shear plastic work is presented to decrease the life factors.     

Influence of loading direction on the anisotropic fatigue properties of rolled magnesium alloy

The influence of loading direction on the fatigue behavior of rolled AZ31 alloy was investigated by conducting fully reversed stress-controlled fatigue tests along the rolling direction and normal to the rolling plane. Alternating twinning and detwinning behavior during initial cycling was found to cause asymmetric hysteresis loops, resulting in a compressive strain in the rolling direction and a tensile strain normal to the rolling plane. A transition in the dominant deformation mechanism from twinning–detwinning to slip occurs at around five cycles under both conditions due to cyclic hardening, thus making their loops symmetric. The lower twinning stress in tension along the normal direction leads to an increase in fatigue damage by plastic strain, resulting in a lower fatigue resistance than along the rolling direction.     

Torsional fatigue with axial constant stress of oligo‐crystalline 316L stainless steel thin wire

A series of symmetric torsional fatigue with axial constant stress tests, a kind of multiaxial fatigue test, was conducted on oligo‐crystalline 316L stainless steel thin wire, which was less than 3.5 grains across diameter of 200 μm. The material presents significant cyclic hardening under symmetric torsion cycling, and hardening is more obvious with the increasing shear strain amplitude. However, symmetric torsional cycle with constant axial stresses tests characterize rapid initial hardening and then gradually softening until fatigue failure. The axial stress has a great effect on torsional fatigue life. Fractography observation shows a mixed failure mode combined torsional fatigue with tensile strain because of axial tensile stress. A newly proposed model with axial stress damage parameter is used to predict the torsional fatigue life with constant axial stress of small scale thin wire.     

Effect of back-stress on cyclic stress-strain behaviour of a quenched and tempered low alloy steel

Low cycle fatigue was considered in relation to back-stress hardening. Cyclic stress-strain behaviours under controlling strain and stress conditions were investigated for a quenched and tempered low alloy steel which contained cementite particles. The cyclic stress-strain states obtained by the two prescribed tests were uniquely described using a parameter which reflected the cumulative reversible plastic work associated with the back-stress hardening. It was suggested that the effect of back-stress hardening on cyclic deformation should appear directly on the cyclic stress-strain curves defined as the loci of the tips of stable hysteresis loops. The initial slopes of the cyclic stress-strain curves for several steels were demonstrated to coincide with the theoretical work-hardening rates calculated on the basis of back-stress hardening due to the included carbide particles. Finally, the Manson-Coffin law was explained from the view that the surface damage would progress in parallel with the structure change in the bulk according to the persistency of slips resulting from the reversible back-stress hardening.     

Assessment of fatigue response of thermally aged reduced activation ferritic-martensitic steel based on finite element analysis

Abstract

In the present investigation, effect of thermal ageing on low cycle fatigue (LCF) behaviour of Reduced Activation Ferritic Martensitic steel has been assessed by finite element analysis. The steel was thermally aged at 873 K for 3000 hour. Low cycle fatigue tests were carried out on both the as-received and thermally aged material at strain rate of 3×10^?3 s^?1 at 823 K, over strain amplitudes in the range of ± 0.25 to ± 0.8%. Continuous cyclic softening till final failure, except for initial few cycles especially at relatively lower strain amplitudes, was observed in both the material conditions. Thermal ageing resulted in marginally higher cyclic stress response accompanied by lower fatigue life. The differences in fatigue responses have been attributed to the coarsening of precipitates on thermal ageing. Finite element analysis has been carried out considering combined isotropic and kinematic hardening as material model to estimate the effect of thermal ageing on the response of material under LCF loading. Thermal ageing was found to decrease both the isotropic and kinematic hardening with appreciable effect on isotropic hardening. The predicted cyclic stress response and hysteresis loops were found to be in good agreement with the experimental data. The LCF life of the steel has been estimated based on the hysteresis energy approach.     

Damage Monitoring of Unidirectional C/SiC Ceramic-Matrix Composite under Cyclic Fatigue Loading using A Hysteresis Loss Energy-Based Damage Parameter at Room and Elevated Temperatures

The damage evolution of unidirectional C/SiC ceramic-matrix composite (CMC) under cyclic fatigue loading has been investigated using a hysteresis loss energy-based damage parameter at room and elevated temperatures. The experimental fatigue hysteresis modulus and fatigue hysteresis loss energy versus cycle number have been analyzed. By comparing the experimental fatigue hysteresis loss energy with theoretical computational values, the interface shear stress corresponding to different cycle number and peak stress has been estimated. The experimental evolution of fatigue hysteresis loss energy and fatigue hysteresis loss energy-based damage parameter versus cycle number has been predicted for unidirectional C/SiC composite at room and elevated temperatures. The predicted results of interface shear stress degradation, stress–strain hysteresis loops corresponding to different number of applied cycles, fatigue hysteresis loss energy and fatigue hysteresis loss energy-based damage parameter as a functions of cycle number agreed with experimental data. It was found that the fatigue hysteresis energy-based parameter can be used to monitor the fatigue damage evolution and predict the fatigue life of fiber-reinforced CMCs.     

Cyclic shear deformation and fatigue of extruded Mg-Gd-Y magnesium alloy

Deformation and fatigue of extruded Mg-8.0 Gd-3.0 Y-0.5 Zr(GW83, wt%) magnesium(Mg) alloy were experimentally investigated under cyclic torsion using tubular specimen fabricated along the extrusion direction. The controlled shear strain amplitudes ranged from 0.606% to 4.157%. Twinning and detwinning of extension twins are observed to take place during cyclic torsion and the shear stress-shear strain hysteresis loops display a perfectly symmetric shape at all tested strain amplitudes. Marginal cyclic softening is observed when the shear strain amplitude is higher than 1.732%. The strain-life fatigue curve shows two kink points, corresponding to the shear strain amplitude of 1.040% and 1.732%, respectively.When the shear strain amplitude is higher than the upper kink point, early fatigue crack is found to initiate on the maximum shear plane. When the strain amplitude is lower than the lower kink point,fatigue cracking is parallel to the maximum tensile plane. At an identical equivalent strain amplitude,the fatigue life under pure shear is much higher than that under tension-compression. The fatigue life of extruded GW83 alloy is much higher than that of extruded AZ31 B alloy at the same plastic strain energy density.     

Influence of loading path on fatigue crack growth under multiaxial loading condition

In this study, the specimens made of carbon steel S45 with an initial surface straight edge notch were subjected to combined cyclic axial‐torsion loading at room temperature. The fatigue life, surface crack extension direction and crack length were experimentally investigated. The effects of loading path, stress amplitude ratio and phase angle on the crack growth behaviour were also discussed. The results showed that, under the combination of cyclic axial and torsion loading, the tension stress amplitude had more effect on the initial crack growth path than the latter. The shear stress amplitude contributed mainly to the latter crack extension. The crack extension path was mainly determined by the stress amplitudes and the ratio of the normal stress to the shear stress, and almost independent of the mean stresses. The increase of the tension stress amplitude and shear stress amplitude would both accelerate the crack growth rate.     

Fatigue Hysteresis of Carbon Fiber-Reinforced Ceramic-Matrix Composites at Room and Elevated Temperatures

When the fiber-reinforced ceramic-matrix composites (CMCs) are first loading to fatigue peak stress, matrix multicracking and fiber/matrix interface debonding occur. Under fatigue loading, the stress–strain hysteresis loops appear as fiber slipping relative to matrix in the interface debonded region upon unloading/reloading. Due to interface wear at room temperature or interface oxidation at elevated temperature, the interface shear stress degredes with increase of the number of applied cycles, leading to the evolution of the shape, location and area of stress–strain hysteresis loops. The evolution characteristics of fatigue hysteresis loss energy in different types of fiber-reinforced CMCs, i.e., unidirectional, cross-ply, 2D and 2.5D woven, have been investigated. The relationships between the fatigue hysteresis loss energy, stress–strain hysteresis loops, interface frictional slip, interface shear stress and interface radial thermal residual stress, matrix stochastic cracking and fatigue peak stress of fiber-reinforced CMCs have been established.