Mg-11Gd-2Y-1.5Ag-0.5Zr合金的高温蠕变行为

本工作研究了Mg-11Gd-2Y-1.5Ag-0.5Zr合金在225～275℃/110～150 MPa条件下的高温蠕变行为和组织演变.结果表明:合金在225℃/110～150 MPa蠕变状态下,蠕变应力指数n=3.4,蠕变机制为位错滑移机制;在250℃/110～150 MPa蠕变状态下,蠕变应力指数n=4.7,蠕变机制为位错滑移机制;在275℃/110～130 MPa蠕变状态下,蠕变应力指数n=5.8,蠕变机制为位错滑移机制;在275℃/130～150 MPa蠕变状态下,蠕变应力指数n=10.5,幂律蠕变定律失效,蠕变机制较为复杂.根据蠕变激活能Q值对蠕变机制的分析结果与蠕变激活能n值分析结论基本一致.合金在同一温度下,晶粒尺寸随着应力的增大而增大;在同一应力下,晶粒尺寸随着温度的升高而减小.在本研究中,110～150 MPa的高应力范围内,合金在250℃以下有着良好的抗蠕变性能.     

基于Eshelby等效夹杂理论的沥青混合料有效粘弹性质分析

利用Eshelby 等效夹杂理论研究了沥青混合料的单轴压缩蠕变行为。通过时间域内的Laplace 变换将问题线性化, 得到了沥青混合料的蠕变本构关系。开展了不同温度、应力水平条件下沥青砂的单轴压缩蠕变实验, 根据数据拟合了沥青砂四参量流变模型的模型参数。在此基础上, 预测了沥青混合料在不同温度、应力水平下的蠕变曲线, 分析了温度、应力水平对沥青混合料蠕变行为的影响。结果表明:在相同的应力水平下, 沥青混合料的应变和应变率都随温度的升高而增大, 并且在沥青软化点附近发生明显突变;在相同的温度下, 沥青混合料的应变和应变率都随加载应力的增加而增大。     

AZ91D室温环境棘轮及其低周疲劳行为

通过AZ91D室温环境应力控制下的低周疲劳试验,对铸造镁合金棘轮及其低周疲劳行为进行了研究,讨论了室温环境下材料的应力循环特性、棘轮行为、塑性应变范围、全应变范围等疲劳参量随载荷水平和加载历史的变化规律,同时基于平均应力修正对材料的应力-寿命曲线进行了讨论。研究结果表明:AZ91D在室温环境下的应力循环呈循环硬化,材料的棘轮行为和塑性应变范围、全应变范围等疲劳参量依赖于载荷水平和加载历史,另外考虑平均应力修正后的应力-寿命曲线预测效果有明显改观。     

Ti-6Al-3Nb-2Zr-1Mo合金室温压缩蠕变行为及位错类型研究

研究Ti-6Al-3Nb-2Zr-1Mo合金在不同外加应力下的室温压缩蠕变行为,拟合了蠕变曲线,计算出蠕变发生第二阶段的临界值,并对不同应力水平压缩后的合金显微组织进行TEM观察,研究其位错滑移类型.结果表明:室温条件下,Ti-6Al-3Nb-2Zr-1Mo合金压缩蠕变-时间曲线符合时间强化指数模型,该合金发生蠕变第二...     

加载路径对5A06铝合金力学性能和微观组织的影响

目的 通过力学性能测试和微观组织表征等手段研究预加载方向和双向加载对5A06铝合金组织性能的影响。方法 分别沿轧制方向(RD)和垂直于轧制方向(TD)施加预变形,然后沿RD进行拉伸试验,对比研究预加载方向对合金力学性能的影响。通过双向拉伸试验研究合金在双向加载时力学性能的变化情况;采用透射电镜观察预加载和双向加载条件下典型试样内的位错组态,分析加载路径对位错组态的影响。结果 预加载使5A06铝合金的屈服强度提高,伸长率下降。与RD预加载相比,TD预加载对屈服强度和伸长率的影响更小,TD预加载试样的抗拉强度更高。不同预加载方向下试样的位错组态不同:预加载与二次加载方向一致会使位错沿单一方向塞积;预加载与二次加载方向垂直时会出现平行位错列交错缠结现象。双向加载时,不同加载比例下合金的应力–应变关系不同,加载比例越接近等比例双向拉伸情况,加工硬化系数越大,在等比例双轴拉伸时达到最大。在应力状态从单拉状态变化到等双拉状态的过程中,不同阶段屈服点间隔不同,在等比例双轴拉伸时达到最大,在单向拉伸时最小。对于不同加载比例的试样,其位错密度随中心区应变量的增大而增大。结论 预加载方向会显著影响5A06铝合金的力学性能和位错组态。不同比例的双向加载会影响5A06铝合金的应力–应变关系。     

基于纳米压入法Ti-13Mo-8Cr-6Sn-5Nb钛合金的应变率敏感性研究

采用纳米压入法对钛合金室温应变率敏感性进行研究。通过控制加载阶段不同应变率达到最大压入深度,基于连续刚度测量原理,研究硬度及弹性模量的应变率敏感性,并观察压入应变率对于保载阶段材料蠕变位移的影响。结果表明,钛合金硬度表现出应变率敏感性,弹性模量对应变率不敏感。压痕保载阶段主要为位错运动主导的蠕变形式,蠕变应力指数随加载应变率增大而降低。     

基于纳米压痕测试的超细晶Si_2N_2O-Si_3N_4陶瓷室温蠕变特性

目的陶瓷材料由于其固有硬脆性,难以利用传统单轴拉伸与压缩实验测试其蠕变性能,而纳米压痕测试技术对试样形状尺寸没有特殊要求,因此利用纳米压痕测试技术研究Si2N2O-Si3N4超细晶陶瓷的室温蠕变性能。方法针对1600,1650,1700℃条件下烧结制备的Si2N2O-Si3N4超细晶陶瓷,采用纳米压痕技术测试材料在最大载荷分别为5000,6000和7000μN条件下的载荷-位移曲线,并通过拟合计算获得了3种材料室温蠕变应力指数。结果 3种材料均呈现明显的加载效应。结论研究表明,在相同载荷下,压入深度和蠕变位移都随着材料烧结温度的升高而增大,且相同材料的蠕变应力指数,随着保压载荷的增大而减小。对比分析发现,在1600℃条件下烧结制备的Si2N2O-Si3N4超细晶陶瓷,晶粒细小均匀,晶界数多,室温下表现出较强的蠕变性能。     

应力对FeCrMoCu合金阻尼性能的影响

用动态力学分析仪(DMA)的三点弯和双悬臂方法测量FeCrMoCu合金的阻尼性能,通过ABAQUS有限元模拟分析测量过程中试样的应力分布,研究了应力对FeCrMoCu合金阻尼行为的影响。结果表明:测量阻尼时预载荷使样品产生应力集中,使样品的磁畴壁发生移动从而降低了合金的阻尼性能。应力越大磁畴的可动性越低,对合金阻尼性能的影响也越大。应力的加载方式也对FeCrMoCu合金阻尼性能有较大的影响,预载荷使双悬臂模式下样品上下表面都受到压应力,因此需要较大的应力才能使样品的磁畴结构达到饱和。其结果是对应的应变振幅εmax较大,测得的最大阻尼性能Q-m1ax偏低。而三点弯测试时,由于上下表面分别受到压应力和拉应力,应力的叠加使合金磁畴达到饱和的应变振幅εmax较小,测得的Q-m1ax较大。     

GH2901镍基合金蠕变及疲劳的实验和数值研究

以GH2901高温合金为研究对象,通过实验测定了其在500℃下,730 MPa和850 MPa的恒定单轴拉伸力作用下的蠕变应变与时间的关系曲线。然后基于该曲线采用组合时间强化蠕变本构方程对其进行函数拟合,并获得相应的蠕变本构方程。通过该方程采用蠕变有限元计算和疲劳寿命的计算,获得了该合金的应变规律及使用寿命情况。分析结果表明:该合金在500℃,730 MPa恒定应力作用10h,蠕变应变值为0.002553~0.010767,总应变值为0.0027544~0.012411。该数据表明,率无关应变值(弹性应变加率无关塑性应变)相对于蠕变应变值(率相关塑性应变)来说非常微小,约为其1/10。     

1Cr18Ni9不锈钢高温单轴时相关棘轮行为研究

在室温、250℃、500℃和650℃四种温度下对1Cr18Ni9不锈钢材料的单轴应变循环特性及其时相关棘轮行为进行了实验研究,以讨论不同加载速率、加载波形和峰值应力保持时间对材料棘轮行为的影响。实验结果表明:在室温下,材料呈现出弱的循环软化特性和渐进型棘轮变形行为,并对加载速率和峰值应力保持时间具有强烈依赖性;在250℃、650℃下,因材料的循环硬化加快而使其棘轮行为较快趋于安定,但棘轮变形大小仍一定程度依赖于加载速率和保持时间;在500℃温度下则由于动态应变时效的影响没有明显的棘轮行为发生。研究得到一些有助于后续建立时相关本构模型的结论。     

Strain Accumulation in Ti-6Al-4V during Fatigue at High Mean Stress

The effect of mean stress and frequency on the high cycle fatigue behavior of Ti-6Al-4V has been investigated. It has been shown that a transition in the fatigue behavior occurs at a stress ratio of approximately 0.7. Above this value, the material exhibits measurable strain accumulation and necking. Since Ti-6Al-4V is susceptible to room temperature creep, an empirical model was developed using static creep data in an attempt to predict the cyclic behavior of the material. The model was unable to account for the large amounts of strain seen experimentally. In addition, closer examination of the data revealed that the deformation was more closely related to the number of cycles than to time.     

Effects of intermittent loading time and stress ratio on dwell fatigue behavior of titanium alloy Ti-6Al-4V ELI used in deep-sea submersibles

Different components of deep-sea submersibles,such as the pressure hull,are usually subjected to inter-mittent loading,dwell loading,and unloading during service.Therefore,for the design and reliability assessment of structural parts under dwell fatigue loading,understanding the effects of intermittent loading time on dwell fatigue behavior of the alloys is essential.In this study,the effects of the inter-mittent loading time and stress ratio on dwell fatigue behavior of the titanium alloy Ti-6Al-4V ELI were investigated.Results suggest that the dwell fatigue failure modes of Ti-6Al-4V ELI can be classified into three types,i.e.,fatigue failure mode,ductile failure mode,and mixed failure mode.The intermittent loading time does not affect the dwell fatigue behavior,whereas the stress ratio significantly affects the dwell fatigue life and dwell fatigue mechanism.The dwell fatigue life increases with an increase in the stress ratio for the same maximum stress,and specimens with a negative stress ratio tend to undergo ductile failure.The mechanism of dwell fatigue of titanium alloys is attribute to an increase in the plastic strain caused by the part of the dwell loading,thereby resulting in an increase in the actual stress of the specimens during the subsequent loading cycles and aiding the growth of the formed crack or damage,along with the local plastic strain or damage induced by the part of the fatigue load promoting the cumu-lative plastic strain during the dwell fatigue process.The interaction between dwell loading and fatigue loading accelerates specimen failure,in contrast to the case for individual creep or fatigue loading alone.The dwell fatigue life and cumulative maximum strain during the first loading cycle could be correlated by a linear relationship on the log-log scale.This relationship can be used to evaluate the dwell fatigue life of Ti alloys with the maximum stress dwell.     

Thermo-mechanical sheet metal forming of aero engine components in Ti-6Al-4V – PART 1: Material characterisation

Ti-6Al-4V is one of the most frequently used titanium alloy in aerospace applications such as for load carrying engine structures, due to their high strength to weight ratio in combination with favourable creep resistance at moderate operating temperatures. In the virtual development process of designing suitable thermo-mechanical forming processes for titanium sheet metal components in aero engine applications numerical finite element (FE) simulations are desirable to perform. The benefit is related to the ability of securing forming concepts with respect to shape deviation, thinning and strain localisation. The reliability of the numerical simulations depends on both models and methods used as well as on the accuracy and applicability of the material input data. The material model and related property data need to be consistent with the conditions of the material in the studied thermo-mechanical forming process. In the present work a set of material tests are performed on Ti-6Al-4V at temperatures ranging from room temperature up to 560°C. The purpose is to study the mechanical properties of the specific batch of alloy but foremost to identify necessary material model requirements and generate experimental reference data for model calibration in order to perform FE-analyses of sheet metal forming at elevated temperatures in Ti-6Al-4V.     

神经网络预测搅拌摩擦加工TC4超塑性行为

目的 研究搅拌摩擦加工工艺改性的Ti–6Al–4V双相钛合金的超塑性变形行为。方法 对360 r/min、30 mm/min工艺条件下搅拌摩擦加工处理的TC4钛合金在不同的变形条件下进行超塑性拉伸实验,在实验数据的基础上构建以变形温度、应变速率和晶粒尺寸为输入参数且以峰值应力为输出参数的3–16–1结构的BP人工神经网络模型。应用所构建的BP人工神经网络模型对不同变形条件的Ti–6Al–4V钛合金的超塑性行为进行预测。结果 BP人工神经网络预测的精准度较高,实验应力值与预测应力值吻合度较高,相关系数R=0.991 3,相对误差为1.91%~12.48%,平均相对误差为5.92%。结论 该模型预测的准确性较高,能够客观真实地描述Ti–6Al–4V合金的超塑性变形行为。     

TI-6Al-4V合金置氢-除氢组织与力学性能

为研究除氢处理对置氢钛合金组织与性能的影响,对Ti-6Al-4V合金在不同参数条件下进行了置氢与除氢处理,采用光学显微镜分析了置氢-除氢处理过程中Ti-6Al-4V合金微观组织的演化规律,通过室温拉伸试验研究了置氢-除氢处理后Ti-6Al-4V合金的力学性能,探讨了Ti-6Al-4V合金置氢-除氢组织与力学性能之间的相...     

增材制造Ti-6Al-4V合金组织调控研究现状

增材制造技术可实现复杂钛合金零件的快速成形,制造的Ti-6Al-4V合金具有较高的强度以及优异的高温性能,被广泛应用于航空、医疗等各大领域。综述了金属增材制造的典型工艺,分析了Ti-6Al-4V合金的相变特征,总结了选区激光熔化制造Ti-6Al-4V的力学性能和组织调控方法,着重分析了热处理温度、冷却速率、变质处理以及超声冲击等对合金组织的影响;展望了增材制造Ti-6Al-4V合金的主要发展方向。     

Effect of Triple Annealing Treatment on Stress Relaxation of Ti-6Al-4V Alloy

The effect of triple annealing on stress relaxation of Ti-6Al-4V alloy as well as the microstructure after stress relaxation werestudied. The results showed that triple annealing treatment enhanced the resistance of stress relaxation performance, andwhen the temperature was rising, this effect became notable. The stress relaxation deformation mechanism is of dislocationcreep at 400℃ and recovery creep at 600℃.     

Creep Behavior of As-Cast Ti-48Al-2Cr Intermetallic Alloy for Aerospace and Automotive Applications

The creep properties of as-cast Ti-48Al-2Cr (at%) alloy which had been strengthen with addition of 2 at% Cr were investigated. Tensile creep experiments were performed in air at temperatures from 600-800°C and initial stresses ranging from 150 to 180 MPa. Stress exponent and activation energy were both measured. Data indicates that the alloy exhibits steady state creep behavior and the steady state creep rate is found to depend on the applied load and temperature. The measured power law stress exponent for steady state creep rate is found to be close to 3 and the apparent activation energy for creep is calculated to be 15.7 kJ/mol. The creep resistance of the present alloy was also compared with binary Ti-48Al (at%) to evaluate the effect of Cr addition on creep resistance of TiAl. It is concluded that addition of 2 at% of Cr does not have significant effect on the creep resistance of TiAl.     

颗粒增强Ti基复合材料的特性

本文研究了采用粉末冶金工艺制备的碳化钛颗粒(TiCp)增强 Ti-Al-V 复合材料的显微组织、弹性模量、高温强度、蠕变行为及断裂特征。研究结果表明,选用合适的不连续增强相及 Ti合金基体可以获得增强相与基体结合良好、具有高比强、高比模、良好高温性能的不连续增强 Ti基复合材料。这些 Ti 基复合材料具有各向同性,可用于复杂应力状态,可通过热压、热挤压等一般热加工工艺加工成型。