LY12CZ铝合金单轴腐蚀疲劳寿命评估的损伤模型

基于损伤力学基本理论,建立了LY12CZ铝合金试件的腐蚀疲劳寿命预测模型,并利用LY12CZ铝合金进行腐蚀疲劳的验证性试验。结果表明,利用损伤力学基本理论建立的模型所得到的预腐蚀LY12CZ铝合金试件腐蚀的疲劳寿命预测结果与腐蚀疲劳试验结果吻合程度良好,尤其对于应力水平较高的低周疲劳结果预测更为准确。这说明基于损伤力学的铝合金预腐蚀疲劳寿命预测模型合理有效,对LY12CZ铝合金构件的损伤容限评估具有参考价值。     

孔挤压与超载复合强化对LY12CZ铝合金疲劳裂纹起始寿命的影响

研究了孔挤压与超载复合强化对LY12CZ铝合金疲劳裂纹起始寿命的影响。实验结果与分析表明,孔挤压与超载复合强化对LY12CZ铝合金的疲劳裂纹起始寿命及裂纹萌生、扩展特性的影响和孔挤压单一强化效果相同。此外还给出了复合强化后LY12CZ铝合金疲劳裂纹起始寿命的定量表达式,以及变幅载荷下LY12CZ铝合金孔挤压件疲劳裂纹起始寿命的估算新方法。     

LY12CZ铝合金拉扭复合载荷下疲劳损伤律实验研究

对LY12CZ铝合金薄壁圆管试样进行多种路径下按高—低和低—高顺序作用的两级变幅载荷下的疲劳损伤累积实验。分析两级变幅循环载荷下各种路径的疲劳累积损伤规律,以及第一级载荷作用循环次数对试件总的疲劳寿命的影响。实验结果表明,在多轴拉扭复合加载的情况下,累积损伤规律呈现出非线性,且损伤程度受第一级载荷作用循环次数影响。     

直流脉冲电流对4043铝合金拉伸硬化的影响

低成本消除加工硬化,愈合损伤对轧制材料具有重要意义。本文将4043铝合金在介于其名义屈服强度和强度极限之间的某一应力下进行拉伸,造成拉伸硬化和损伤后,用直流脉冲电流处理。结果表明:随着脉冲处理时间的增加,试件延伸率增加,名义屈服强度和强度极限减小;0.5 s脉冲处理试样的力学性能十分接近未损伤试样的性能;光学显微照片显示同一位置上的损伤得到部分愈合。试样拉伸造成一定损伤后,其电阻值有明显增加;脉冲电流处理后电阻减小,但没有恢复到拉伸前的电阻值。经过不同时间的脉冲处理后,其电阻值十分接近,但是力学性能差异较大,表明电阻值对材料的力学性能不十分敏感,不能完全依赖电阻值判定材料的力学性能。     

疲劳损伤及中间退火修复的40Cr试件的微观结构分析

利用透射电子显微镜对原始态、疲劳损伤态以及疲劳损伤后经中间退火修复的40Cr钢的微观结构进行研究。结果表明，经高温回火的40Cr钢的原始试样由于合金元素铬的存在使其回火稳定性较高，组织基本上保留了原板条马氏体的形貌。沿板条界或在板条中分布着粒状碳化物M7C3和M23C6，另外在较宽的板条中还有细长的杆状M3C碳化物存在，疲劳损伤态的试样的组织中位错组态与原始态的不同，部分区域位错缠结成位错墙结构，还有一些区域观察到位错胞结构，而且损伤后M23C6碳化物的形貌变大，杆状M3C碳化物的数量增加，杆的长度减小，经过中间退火修复后，碳化物周围的位错缠结减少，而且位错胞的壁厚减小，位错密度降低，在整个组织中只发现了大块圆球状的M23C6碳化物均匀分布，从微观亚结构分析这三种状态的试样的组织存在一定的差异，因而表现为其力学性能和疲劳总寿命都有所不同。     

短裂纹密度场细观统计分析

通过LY12铝合金棒材位移控制下的疲劳试验获得了含裂纹的计算机层析成像(CT)检测样本。采用微焦点CT对疲劳试样进行了扫描与重建,获得了密度场图像库,并提取了试样内部的三维裂纹形态。结果表明裂纹以体的形式存在。对裂纹区域内外平均灰度、沿裂纹扩展轨迹密度变化、沿裂纹体两侧走向密度分布等进行了密度场的细观统计分析。细观统计结果表明,裂纹区域和邻近区域的密度要低于正常区域的密度,材料内部的疲劳损伤呈现不均匀性。     

基于初始不连续状态预测LY12铝合金缺口结构件的疲劳寿命

对LY12铝合金缺口试样进行了疲劳试验,并根据此试验数据建立了计算初始不连续状态(IDS)的力学模型,得到了LY12铝合金的IDS值,用IDS值对含缺口结构件疲劳寿命进行了预测.结果表明:LY12铝合金的IDS值符合三参数威布尔分布;预测的疲劳寿命与试验结果吻合良好,从而为把基于断裂力学中裂纹扩展的损伤容限方法向传统疲劳研究领域延伸提供了依据.     

LY12CZ铝合金的双重处理表面摩擦学改性研究

本采用双重处理表面改性技术对LY12CZ铝合金进行了摩擦学表面改性处理,即首先对LY12CZ铝合金进行硫酸的阳极氧化处理,然后在其表面再沉积一层润滑薄膜,实验结果表明,双重处理可有效地降低铝合金在真空环境中的摩擦并用明显提高耐磨寿命,特别是采用低摩擦系数的MoS2-Au基复合薄膜,可在较高载荷下达到较长的耐磨寿命,对双重处理铝合金的摩擦失效机理也作了初步探讨。     

疲劳损伤钢件修复的最佳时机

为了研究影响疲劳损伤中间退火修复效果的诸因素 ,找出最佳修复时机的变化规律 ,在恒应变± 0 .5 %和± 0 .8%控制下 ,对 40Cr调质钢进行疲劳循环加载 ,求得存活率为 90 %时的寿命Nf。将试样疲劳加载到少于Nf 的不同周次后 ,再进行中间退火修复。发现中间退火可以延长损伤件的疲劳寿命。本次试验条件下能使疲劳寿命提高到原始试样的二倍。修复效果与损伤周次和承受的循环应变大小有关。用高灵敏度电阻仪和TEM对疲劳损伤过程与修复后材料的微观结构进行测试和观察。发现中间退火不能使损伤的材料恢复到原始材料状态。疲劳加载对材料的微观变化有两个相反的影响 ,疲劳损伤导致形成微观裂纹 ,但疲劳加载在材料中累积的应变能在中间退火过程中 ,作为附加驱动力 ,促使材料更加均匀、稳定 ,从而减少了形成微裂纹的条件。当循环应变增加 ,获得最佳修复效果的损伤周次减少。     

残余热应力对复合材料双面胶接含裂纹铝合金板修复结构疲劳寿命的影响

为研究残余热应力对复合材料双面胶接修复损伤金属结构疲劳寿命的影响,利用T300/E51复合材料补片对含中心裂纹的LY12CZ铝合金板进行双面胶接修复,研究了修复结构的疲劳寿命,并通过断口分析反推出了疲劳裂纹的扩展情况;利用Abaqus软件建立了考虑残余热应力的修复结构的三维有限元模型,分别计算了应力强度因子随裂纹长度的变化关系,并利用二次多项式拟合得到了应力强度因子幅值与裂纹长度的关系式;最后,利用Pairs公式材料常数修正法,对修复结构的疲劳寿命进行了预测。结果表明:在相同的疲劳载荷条件下,裂纹板修复结构的疲劳寿命约为未修复裂纹板的23倍;残余热应力会增加裂纹尖端的应力强度因子;有限元模拟的裂纹板修复结构的疲劳寿命与试验结果吻合较好,相对误差为3.7%。     

基才激光加工技术的飞机钛合金构件损伤快速修复新工艺

飞机钛合金构件损伤的快速修复是飞机修理工作中的难题,目前国内对此项工艺的研究甚少。本文研究了基于激光加工技术飞机钛合金构件损伤的快速修复新工艺,设计出了相应的激光修复系统,得出了修复工艺过程和主要工艺参数。应用该修复工艺可满足质量及使用要求。     

无缝线路磨损钢轨激光熔覆自动修复方式的研究

由于列车的高速化和重载化,钢轨磨损问题越来越严重,采用修复质量高、修复速度快的激光熔覆技术可以对其进行在线快速修复。为此,采用三维扫描仪首先对磨损钢轨进行扫描,然后将扫描点云数据进行三维重构、路径规划及数据格式转换,最后利用优化的数据驱动机器手臂和激光熔覆装置对磨损钢轨进行自动修复。修复工艺结果表明,对5 mm的磨耗层进行7层修复,利用修复道与道之间和层与层之间的回火作用,修复层的组织马氏体含量少,硬度为330~360 HV;经过600℃回火处理10 min后,加入钒元素的铁基合金粉末激光熔覆修复后钢轨母材、热影响区、修复层硬度均在300~340 HV,组织为回火索氏体;修复钢轨的耐磨性约为钢轨母材的87%,达到修复目的。     

电流大小对TC4钛合金高温压缩力学行为的影响分析

为了研究电流大小对TC4钛合金高温压缩力学行为的影响,利用Gleeble-1500D动态热-力学模拟机,以电流作为加热源,分别以不同的升温速度将晶粒尺寸为8μm、16μm和20μm的TC4小圆柱体试样加热至700℃进行恒温压缩。结果表明：升温阶段的电流大小对应力影响大,大电流有利于塑性变形。电流降低了恒温变形阶段材料的动态再结晶温度,促进动态再结晶软化,降低变形抗力,有利于塑性变形,电流越大效果越明显。     

Prediction of creep failure in aeroengine materials under multi-axial stress states

The creep and creep rupture behaviour of two, significantly different, aeroengine materials, namely a nickel-base superalloy at 700°C and a high temperature titanium alloy at 650°C, were studied. Experimental creep tests were conducted on uniaxial specimens and axisymmetric notched bars under constant tensile loads conditions. From the uniaxial creep test results, a creep continuum damage model was established for each of the materials. The skeletal point stress approach was used to obtain the approximate creep rupture stress criterion in the multi-axial generalization of the creep continuum damage models. This approximation was cross-checked using axisymmetric Finite Element (FE) analyses in a trial and error procedure. Multi-axial creep continuum damage models were then used in further FE creep analyses to predict the creep rupture times in specimens subjected to different tensile loads. The FE predictions of the rupture times in these notched specimens were found to be in good agreement with the experimental results for the nickel-base superalloy (Waspaloy) at 700°C and the titanium alloy (IMI834) at 650°C.     

电火花修复涡轮导向叶片试验研究

研究了电火花修复K418涡轮导向叶片,为涡轮导向叶片的修复提供了理论依据.通过观察试样金相组织及测量显微硬度,并对所得试验数据进行分析,得出结论:修复后试样的金相组织较修复前均匀,晶粒明显细化;修复后试样硬度值一般提高30～50 HV,可以推断试样的耐磨性将会得到改善;最优工艺参数为电压65V,功率B2,频率C1,最大影响因素为电压;修复中还存在气孔、裂纹等缺陷,可以通过进一步试验,比如对试样进行预热、缓冷、改变材料成分等加以避免.     

Damage and failure characterization of 7075 aluminum alloy hot stamping

7000 series high strength aluminum alloys are increasingly used in manufacturing automobile body parts to meet the more stringent demands for automobile lightweight. Hot stamping of 7000 series high strength aluminum alloys is a complex thermal-mechanical coupling process and precise simulation is needed to predict material fracture. To obtain damage model of 7075 aluminum alloy in hot stamping, five different stress triaxiality specimens were designed. The fracture strain, critical strain and average stress triaxiality of different specimens were obtained by the hybrid finite element simulation and experiment (FE-EXP) method. GISSMO model of 7075 aluminum alloy at 400 °C was established. Compared with the experimental results of U-shaped part hot stamping under different lubrication conditions, the calibrated GISSMO model was demonstrated to predict the damage behavior of 7075 aluminum alloy during high temperature deformation accurately.

     

Use of EBSD to study electropulsing induced reverse phase transformations in a Zn-Al alloy (ZA22)

Multi‐phase identification and phase transformations in electropulsing treated Zn–Al based alloy wire specimens were studied using electron back‐scattered diffraction, back‐scattered scanning electron microscopy and X‐ray diffraction techniques. By using electron back‐scattered diffraction, two phases: η′_S and η′_T with a small difference of about 1% in lattice parameters (c₀/a₀) were identified, based on the determined lattice parameters of the phases, and the reverse eutectoid phase transformations: η′_T+?′_T+α′_T→η′_S and ?+α→T′+η were successfully detected. Electron back‐scattered diffraction appeared to be an effective technique for studying complex electropulsing induced phase transformations.     

钛合金表面氧化膜原位修复新工艺研究

研究了钛合金表面氧化膜损伤原位修复设备及工艺,通过表面形貌观察、磨损试验、耐腐蚀试验、X衍射成分分析,考察了修复的效果。结果表明,用原位修复设备及相关工艺能方便地修复氧化膜,修复后的氧化膜具有良好的耐磨性和耐腐蚀性。     

Fabrication of two-layered Al-B4C composites by conventional hot pressing uuder nitrogen atmosphere and their characterization

In this study, we describe the conventional hot pressing (CHP) of layered Al-B₄C composites and their characterization. The matrix alloy A1-5 wt.%Cu was prepared from elemental powder mixtures. The metal and B₄C powders were mixed to produce either Al-Cu-10vol.%B₄C or Al-Cu-30vol.%B₄C combinations. Then, these powder mixtures were stacked as layers in the hot pressing die to form a two-layered composite. Hot pressing was carried out under nitrogen atmosphere to produce 30×40×5 mm specimens. Microstructural features and age hardening characteristics of composites were determined by specimens cut longitudinally. The flexural strength of both layered composites and their monolithic counterparts were investigated via three point bending tests. In the case of layered specimens of both 10vol.%B₄C and 30vol.%B₄C containing layers were loaded for three-point test. The results show that a homogeneous distribution of B₄C particles in the matrix alloy which is free of pores, can be obtained by CHP method. The ageing behavior of the composites was found to be influenced by the reinforced materials, i.e. higher hardness values were reached in 8 hrs for the composites than that for the matrix alloy. Flexural strength test showed that two-layered composites exhibited improved damage tolerance depending on layer arrangement. Microstructural investigation of the fracture surfaces of the bending specimens was performed by means of scanning electron microscope (SEM). While layer with lower reinforcement content exhibited large plastic deformation under loading, the other with higher reinforcement content exhibited less plastic deformation.