Preparation of micro-arc oxidation coatings on magnesium alloy and its thermal shock resistance property

In the NaAlO2-Na2SiO3 compound system, the ceramic coatings were prepared on magnesium alloy by micro-arc oxidation. The morphology, phase composition, and thermal shock resistance of the ceramic coatings were studied by scanning electron microscope, X-ray diffraction and thermal shock tests, respectively. The results showed that the ceramic coating contains MgO, MgAl2O4, as well as a little amount of MgESiO4. The thickness of the ceramic coatings increases with the current density increasing, when the current density is 12 A·dm^-2, the thermal shock resistance of the produced ceramic coating is the best. The hardness of the ceramic coating is up to 10 GPa or so.

Thermal Shock Resistances of FeMnCr/Cr_3C_2 Coatings Deposited by Arc Spraying

Arc spraying with the cored wires was applied to deposit FeMnCr/Cr3C2 coatings on low carbon steel substrates, namely FM1, FM2 and FM3. Thermal shock resistances of the coatings were investigated to assess the influence of Cr3C2 content on thermal shock resistance. Characteristics of the coatings under thermal cycling test were studied by optical microscopy, field emission scanning electron microscope （FE-SEM） and energy dispersion spectrum （EDS）, X-ray diffraction （XRD）. The experimental results show that hardness of the coatings increases, bonding strength decreases slightly with increase of the Cr3C2 content of the coatings. As a result, FM2 coating possesses the best thermal shock resistance, attributing to its better thermal expansion matches and wettability than those of FM3 coating, less oxide rate than that of FM1 coating restraining from cracks formation and propagation in coatings.

Diagnosis of Electron,Vibrational and Rotational Temperatures in an Ar/N2 Shock Plasma Jet Produced by a Low Pressure DC Cascade Arc Discharge

In this paper, a low pressure Ar/N2 shock plasma jet with clearly multicycle al- ternating zones produced by a DC cascade arc discharge has been investigated by an emission spectral method combined with Abel inversion analysis. Plasma emission intensity, electron, vi- brational and rotational temperatures of the shock plasma have been measured in the expansion and compression zones. The results indicate that the ranges of the measured electron temperature, vibrational temperature and rotational temperature are 1.1 eV to 1.6 eV, 0.2 eV to 0.7 eV and 0.19 eV to 0.22 eV, respectively, and it is found for the first time that the vibrational and rota- tional temperatures increase while the electron temperature decreases in the compression zones. The electron temperature departs from the vibrational and the rotational temperatures due to non-equilibrium plasma effects. Electrons and heavy particles could not completely exchange energy via collisions in the shock plasma jet under the low pressure of 620 Pa or so.

铝合金电弧增材与激光冲击强化复合制造组织与性能

对电弧增材铝合金试样进行激光冲击强化,观察激光冲击强化对电弧增材铝合金材料的现象,分析了激光冲击强化对电弧增材铝合金微观组织和力学性能的影响。激光冲击强化后,未影响区域的微观结构与电弧增材试样的结构相似,由细长的柱状晶区和位于柱状晶区之间的细小等轴晶区组成;受影响区中杂乱分布着的中等大小的等轴晶及较长的柱状晶。激光冲击改变了材料微观结构,出现了中等大小的等轴晶,减少了气孔。激光冲击强化后,增材铝合金表面均产生了残余压应力场,在合理的工艺参数下,可以获得最大残余压应力约为−124 MPa。在不同试验参数下,冲击能量、冲击次数和搭接率的提高都能增加铝合金的显微硬度和影响深度,证明激光冲击强化技术显著提高了电弧增材铝合金试样表面性能,在改善力学性能方面有重要作用。

2219铝合金TIG焊缝激光冲击强化与腐蚀性能研究

目的 改善2219铝合金钨极氩弧焊焊缝的耐腐蚀性能。方法 采用激光冲击技术对焊缝进行强化处理,比较分析处理前后的表面残余应力、物相组成和元素状态,通过静态浸泡失重法和电化学试验测量腐蚀速率的变化。结果 经过激光冲击强化处理后,2219铝合金焊缝部位的元素状态没有改变,但焊缝区域的残余拉应力变为残余压应力。2219铝合金钨极氩弧焊接区域的自腐蚀电位明显下降,相比未经激光冲击处理的试件,焊核区和焊接过渡区的平均腐蚀电流分别减小了14%和12.7%,腐蚀速率分别减小了16.9%和12.9%。结论 激光冲击强化可以有效提升2219铝合金钨极氩弧焊焊缝区域的耐腐蚀性能,可以为提升特种装备安全性和轻量化提供技术参考。

电弧熔覆和激光喷丸对轨道交通用Al-Zn-Mg合金疲劳扩展和腐蚀性能的影响

为了提高再制造修复铝合金的服役性能特别是疲劳性能和抗腐蚀性能,以轨道交通用具有代表性的Al-Zn-Mg合金板材为研究对象,在研究合金疲劳行为的基础上模拟实际服役条件对合金造成的损伤。通过不同的电弧熔覆工艺和激光冲击强化技术对产生裂纹的样品合金进行修复,综合比较了修复前后合金的服役性能差异。研究发现,与传统电弧熔覆相比,结合激光冲击强化的电弧熔覆能显著提高合金的疲劳抗力和耐蚀性,电弧熔覆结合激光冲击强化的样品在低应力因子强度范围内展现出更低的疲劳裂纹扩展速率,并在高应力因子强度范围仍维持较低的扩展速率,显著提升了疲劳寿命,同时也降低了晶间腐蚀深度,增强了合金的抗腐蚀性能。该研究结果可为轨道交通用铝合金结构件的服役寿命延长和腐蚀控制提供理论依据和科学指导。

Experimental Investigation on Airfoil Shock Control by Plasma Aerodynamic Actuation

An experimental investigation on airfoil （NACA64-215） shock control is performed by plasma aerodynamic actuation in a supersonic tunnel （Ma -= 2）. The results of schlieren and pressure measurement show that when plasma aerodynamic actuation is applied, the position moves forward and the intensity of shock at the head of the airfoil weakens. With the increase in actuating voltage, the total pressure measured at the head of the airfoil increases, which means that the shock intensity decreases and the control effect increases. The best actuation effect is caused by upwind-direction actuation with a magnetic field, and then downwind-direction actuation with a magnetic field, while the control effect of aerodynamic actuation without a magnetic field is the most inconspicuous. The mean intensity of the normal shock at the head of the airfoil is relatively decreased by 16.33%, and the normal shock intensity is relatively reduced by 27.5% when 1000 V actuating voltage and upwind-direction actuation are applied with a magnetic field. This paper theoretically analyzes the Joule heating effect generated by DC discharge and the Lorentz force effect caused by the magnetic field. The discharge characteristics are compared for all kinds of actuation conditions to reveal the mechanism of shock control by plasma aerodynamic actuation.

Study of Variation Patterns of Shock Wave Control by Different Plasma Aerodynamic Actuations

Demonstrative experiments on the variation patterns of the position, angle, and intensity of shock wave are presented. Different means of aerodynamic actuation, such as variations of the distance between discharge channels, the number of discharge channels, the DC discharge voltage, the angle of ramp, and the application of magnetic field, in a supersonic flow of M = 2.2 are employed. Results of both the schlieren and pressure test indicated that when the plasma aerodynamic actuation is applied, the starting point of the shock wave was shifted 1 mm to 8 mm upstream on average, the shock wave angle was reduced 470 to 8% on average, and the shock wave intensity was decreased by 8% to 26%. The local plasma aerodynamic actuation could generate an extrusive plasma layer with high temperature and pressure. This plasma layer caused an upstream-shift of the separating point of the boundary layer. which changed the structure of the original shock wave. Moreover, in a simulation study, the plasma aerodynamic actuation was simplified as a thermal source term added to the Navier-Stokes equations, after all, the results obtained showed consistency with the experimental results.

大电流弧爆激波的改进等离子炬聚束性能研究

具有高温高压特性的大电流弧爆激波,在材料加工与军工领域有着巨大的应用前景。为实现定向热冲击,需要对弧爆激波聚束,通过改进等离子炬,设计了一种聚束原型机。采用等效电弧爆炸的方法,利用Autodyn-2D和高精度多物质求解器Euler-2D对9组设计方案进行数值模拟,分析了原型机的聚束管、管仰角和电极距离等对弧爆激波聚束性能的影响规律。研究结果表明:等离子炬通过加装聚束管改进后,能将弧爆激波射流速度与压强峰值分别提升300%、500%;管仰角γ对出口出处射流速度有很大的影响;弧倾角λ为45°时,聚束波的速度和能量最大;电极距离主要影响弧爆激波速度和压强的变化率。

TC4钛合金表面激光冲击强化-微弧氧化涂层的组织和性能

通过激光冲击强化(LSP)在TC4钛合金表面制备细晶粒过渡层,再采用微弧氧化(MAO)制备LSP-MAO复合涂层,研究TC4钛合金表面MAO涂层及LSP-MAO复合涂层的显微组织、相结构、显微硬度和耐磨性。结果表明:激光冲击强化处理后,TC4钛合金衍射峰变宽,表层晶粒明显细化。与MAO涂层相比,LSP-MAO复合涂层表面的孔径更小,表面更加平整,显微硬度和强化层深度有所增加,其中激光冲击2次时显微硬度最高,达到636.3 HV0.025(距离表面30μm处),其强化层最大深度达到390μm。LSP-MAO涂层的耐磨性均优于MAO涂层,其中激光冲击强化2次时LSP-MAO复合涂层耐磨性最好。

基于坐标变换的强间断问题伪弧长算法

针对爆炸冲击波数值模拟中经常要面临的强间断奇异性问题,在一维或多维空间中引入弧长参数,通过添加一个约束方程,致使原网格自适应移动变形而能够在强间断区域分布较多的网格点,以此提高大梯度物理量捕捉的分辨率。针对非均匀变形物理空间中格式构造困难的问题,提出了坐标变换,将物理空间中的控制方程映射至均匀正交的弧长计算空间。基于MUSCL格式编写了伪弧长算法相应的一维、二维程序,并对其开展人为解方法验证。将伪弧长算法(PALM)的数值结果同有限体积法进行比较,经过误差分析,验证了伪弧长算法在间断附近具有较高的分辨率。

冲击性负荷对“双高”电网暂态电压影响的研究

随着可再生能源发电规模的不断扩大,电力系统呈现出了高比例新能源、高比例电力电子装置的“双高”特性。随着大量冲击性负荷的接入,电网电压波动、谐波等问题愈加明显,加之电力系统“双高”特性,这些因素会给“双高”电网电能质量带来很大隐患。对此,建立了以并网型光伏发电系统为主的“双高”电网,以交流电弧炉为典型冲击性负荷,分析电弧炉三相短路对“双高”电网造成的电压暂降问题。仿真结果表明,电弧炉三相短路时,0.02 s内,无功冲击是正常运行时的5倍,短路电流是正常运行时的5.24倍,35 kV并网点相电压有效值下降了29.19%,引起了明显的电压暂降。

超声冲击对电弧增材制造铝合金应力影响的有限元分析

采用有限元分析方法对附加超声冲击下电弧增材制造2219铝合金的过程进行数值模拟,并研究了其应力场变化以及工件变形情况的变化.结果表明,附加超声冲击能使多层多道沉积过程中沉积件边缘处以及基板中靠近沉积件的区域的应力集中程度下降.多层多道沉积过程中附加超声冲击能有效降低沉积件内部的应力.在附加超声冲击后道间交界处的应力范围由156.1~211.6 MPa下降至138.8~181.9 MPa,表面平均残余应力下降22.3%.附加超声冲击下,多层多道电弧增材构件最大变形量由0.61 mm下降至0.53 mm,平均变形量由0.33 mm下降至0.27 mm.试验实际测量所得的与有限元计算的多层多道沉积件上表面的应力分布规律相近,证明模拟结果的可靠.创新点:(1)建立了多层多道电弧增材有限元模型,并合理地简化超声冲击载荷.(2)利用超声冲击可显著降低电弧增材制造残余应力和变形.

TC4合金微弧氧化涂层的组织结构与高温氧化行为研究

为了提高TC4合金的高温抗氧化性能,采用微弧氧化方法在NaAlO_(2)+Na_(3)PO_(4)电解液体系中,于钛合金表面制备抗氧化陶瓷涂层。通过XRD、SEM、EDS等方法,表征涂层的相组成和微观结构,用纳米压痕仪测试涂层硬度与弹性模量,并研究了微弧氧化涂层的抗高温氧化及抗热震性能。结果表明:微弧氧化涂层表面多孔,涂层以Al_(2)TiO_(5)和金红石型TiO_(2)相为主。微弧氧化涂层的纳米硬度为(7.8±0.6)GPa,显著高于TC4合金[(4.0±0.2)GPa]。微弧氧化涂层在700℃循环氧化80 h后,单位面积增重仅0.73 mg/cm^(2),远小于TC4合金的增重(20 mg/cm^(2)),表现出良好的高温抗氧化性能。经700℃热冲击25次后,涂层未出现剥落现象,展现出良好的抗热震性能。由此可见,微弧氧化涂层能有效阻止氧的扩散,显著降低了钛合金基体的氧化速率,改善了钛合金的抗高温氧化性能。

爆炸冲击波作用下灭弧防雷间隙熄灭工频电弧的机理及应用

为提高输电线路的防雷性能,从灭弧防雷间隙和绝缘子配合时的伏秒特性出发,对爆炸波冲击作用下灭弧装置的灭弧机理进行了研究。基于电弧黑盒模型对暂态电弧进行建模,得出故障电流切除时电弧的电压、电流、电压变化率、电流变化率波形,并进行了试验验证。结果表明:5 k A故障短路电流在第1次过零点时被切断,在爆炸冲击波作用下电弧在5 ms内经拉伸到变形到断裂直至熄灭,且未出现重燃;仿真结果与试验结果一致。基于该原理的灭弧装置现场试运行良好,验证了灭弧间隙的实用性。

轴流压气机超音叶片新设计技术研究

介绍了一种轴流压气机超音叶片新设计技术 ,即叶型中弧线用任意多段圆弧生成 ,前缘用椭圆弧连接。该方法可以灵活控制叶型中弧线的曲率分布 ,有效控制扩散因子 ,提高气流抗分离的能力。椭圆形的前缘可减弱超音气流在前缘进口区的加速程度 ,降低进口弓形波的强度 ;叶型入口段理想的曲率分布可以合理组织进口激波结构和位置 ,大幅降低激波损失。

基于等离子体气动激励的斜劈诱导激波控制

基于弧光等离子体气动激励,采用不同的放电通道间距、放电通道数、放电直流输入电压、斜劈劈角、有无磁场作用等激励条件,实验研究了在超音速来流条件下(马赫数为2.2)斜激波位置、角度、强度的变化规律。结果表明:施加等离子体气动激励后,激波的起始位置平均前移1～8 mm,激波角平均减小4%～8%,激波强度平均减弱8%～26%。这主要是由于等离子体气动激励产生高温高压的表面等离子体层,使边界层分离点逆气流前移,改变了原有激波系结构,使原有的激波位置前移,激波角减小;同时由于局部的高温导致当地音速增大,使得当地马赫数减小,上述两个原因均可导致激波强度减弱。

底面起爆的圆弧钝感炸药爆轰传播规律的数值模拟研究

用爆轰冲击波动力学的广义几何光学模型ＧＧＯ２Ｄ编码计算了底面起爆的圆弧钝感炸药的爆轰波传播过程，以及同一圆心角上不同半径的爆轰走时，计算结果与实验符合得很好。

水中大电流脉冲放电激波影响因素分析

利用液电脉冲放电产生强有力的激波在碎石、液电清砂等领域获得广泛应用。基于液电脉冲激波实验平台,采用高速摄像机拍摄针–针电极放电形成的电弧膨胀过程,研究了水中放电电弧发展的随机性以及激波强度与电弧膨胀速度的对应关系。放电电弧的击穿路径不规则,激波强度主要取决于传递到电弧通道的功率与能量。电弧长度增加,电流峰值降低,但注入电弧通道的功率与能量增大,电能向机械能的总转换效率提高,激波强度增强。

基于多物理场耦合的高压SF_6断路器混沌电弧模型

以高压SF6断路器电弧数学模型为基础,利用二维傅里叶级数的收敛性质,将模型中的涡量变量、温度变量作为混沌特征量,根据边界条件进行二维傅里叶级数展开,得到了描述高压SF6断路器电弧的混沌特性方程,得到反映混沌特征的Lyapunov指数图、时间历程图,以此表征高压SF6断路器电弧存在混沌特性。为进一步反映高压SF6断路器灭弧室内电场、磁场、气流场间的耦合作用,引入麦克斯韦电磁方程和电流密度方程,对SF6断路器电弧的不稳定性进行分析,得到SF6断路器电弧三阶常系数非线性微分方程。通过改变方程中的SF6断路器电弧参数值,系统呈现出混沌行为。