氩气感应耦合等离子体速度与温度数值模拟

为了获得用于研究再入飞行器热防护系统的感应耦合等离子体风洞流场数据,基于流场、电磁场和化学场的多场耦合建立了非平衡态感应耦合等离子体数值模型。利用该模型对不同入口质量流率和不同工作压力下的感应耦合等离子体进行了数值模拟,得到了相应工作参数下感应耦合等离子体温度与速度的分布特性。计算结果表明:等离子体中心线上的速度随着入口质量流率的增大而增大,而随着工作压力的增大而减小;同时,等离子体中心线上的温度随着入口质量流率的增大而减小,而随着压力的增大先减小后增大。这些结果可为感应耦合等离子体风洞优化设计及其工业应用提供理论指导。     

非平衡感应耦合等离子体流场与电磁场作用机理的数值模拟

以航天领域中研究再入飞行器热防护系统的感应耦合等离子体(inductively coupled plasma, ICP)风洞为研究对象,通过流场-电磁场-化学场-热力场-湍流场多场耦合求解研究ICP风洞流场与电磁场的分布特性及其相互作用机理.数值模拟中,基于热化学非平衡等离子体磁流体动力学模型准确模拟了空气ICP的高频放电、焦耳加热、能量转化、粒子内能交换等过程,通过多物理场耦合计算模拟得到了100 kW级ICP风洞内空气等离子体的电子温度、粒子数密度、洛伦兹力、焦耳加热率、速度、压强、电场强度的分布规律.研究结果表明:在感应线圈区靠近等离子体炬壁附近,等离子体流动处于热力学非平衡状态;洛伦兹力对感应线圈区空气粒子的动量传递和电子热运动起着控制作用.     

临近声速气流条件下电子束空气等离子体特性

为了研究高速动态气流中的电子束等离子体特性,建立了一个由蒙特卡罗模型、多组分等离子体模型与计算流体力学模型组成的多阶段耦合数值模型,在临近声速气流条件下,对1.33×104 Pa空气电子束等离子体特性进行了研究。结果表明,电子束能量沉积具有极强的空间不均性,电子束激发下的风洞流场呈现不同的性质,亚声速流场下游边界区密度减小,而在超声速流场中可诱发弱激波;相比于静止气体,在动态气流中等离子体密度下降,且存在额外的输运行为,使其向气流下游输运,但在临近声速条件下,气流速度大小对气流下游等离子体分布的影响不大;电子束入射角对等离子体空间分布和大小均有影响。     

液氢贮箱零蒸发数值模拟与分析

采用CFD技术,对处于微重力下的零蒸发(ZBO)液氢贮箱内采用喷嘴棒强迫混合的流场进行稳态数值模拟,建立了二维轴对称模型,预测了在不同几何参数下贮箱内温度场及速度场分布情况。研究表明,喷嘴棒伸入贮箱长度、入口直径等因素均会对系统内温度场产生影响。贮箱内平均温度和最大温度随喷嘴棒长度和入口直径的增大而减小,而喷口直径对贮箱内温度场影响不明显。由上述可以看出,通过增大入口直径、选择合适的喷嘴棒伸入长度,可以改善系统性能。     

感应耦合等离子体的1维流体力学模拟

 采用双极扩散近似的流体力学模型，通过数值模拟方法研究了射频感应耦合等离子体(ICP)中等离子体密度和电子温度等物理量的空间分布，其中射频源的功率沉积由动力学理论给出。分析了不同的射频线圈的驱动电流和放电气压对等离子体密度和电子温度空间分布的影响。在低气压下，等离子体密度基本上保持空间均匀分布。随着放电压强的增加，等离子体密度的分布呈现出明显的空间不均匀性。当线圈电流增大时，等离子体密度和电子温度都随着增大。     

一种耦合外部电路的脉冲感应推力器磁流体力学数值仿真模型

为了深入研究脉冲感应推力器的工作原理,预测其推进性能,建立了一种耦合外部电路的磁流体力学模型,实现了对加速通道内等离子体二维流场结构演化过程及驱动电路放电过程的同步耦合求解.模拟计算所得美国MK-1推力器加速通道内的等离子体瞬态参数分布及推力器比冲、效率等性能参数均与实验数据一致;计算结果成功复现了推力器的工作物理图景.借助这一新模型,实现了对电路-等离子体双向耦合作用的定量分析,分析结果表明:耦合等离子体导致驱动电路等效电阻增大,电感减小;激励线圈与等离子体之间的互感随等离子体整体远离线圈表面而逐渐减小.     

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将等离子体作为磁流体,考虑其流体属性和电磁属性,介绍了利用FLUENT软件包并将其进行二次开发,解算电磁场方程、质量连续性方程、动量守恒方程、以及能量守恒方程的数值模拟方法,得到了以磁矢势为表达形式的电磁场分布、温度分布和速度分布.数值模拟了粉末球化所用的感应耦合等离子体炬电磁场分布、温度分布、速度分布.分析了温度分布、速度分布产生的物理原因,为感应耦合等离子体炬球化粉末颗粒提供理论性指导.     

直流电压等离子体点火器点火特性研究

使用自行设计的等离子体点火装置,对极间电流随进口氩气压力的变化规律以及不同进口氩气压力和工作电流条件下等离子体点火器出口射流特性进行了实验研究。利用四通道CCD光谱仪测量了点火器出口处的发射光谱特征,并计算了等离子体的电子温度。结果表明,极间电流随进口氩气压力的增大而逐渐减小,等离子体点火器的射流长度随进口氩气流量的增大先增大后减小,随工作电流的增大而增大,等离子体点火器的工作电流随进口氩气流量的增大而减小,随电源输出电流增大而增大,等离子体射流的电子温度随氩气流量的增大而降低,随工作电流的增大而升高。所得结果对等离子体点火系统在航空发动机的实际应用具有一定的指导意义和参考价值。     

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为了提高等离子体废物处理效率,根据磁流体动力学理论,利用计算流体力学软件FLUENT,采用磁矢量势的方法对直流双阳极非转移型电弧等离子体炬进行了二维轴对称数值模拟。计算中采用了SIMPLE算法。数值模拟得到了等离子体的温度、速度等分布。结果表明,等离子体的温度随着轴向距离的增加而减小,随弧电流增加而增加;其速度随着轴向距离的增加而先增大后减小,随弧电流增加而增加;等离子体炬出口处的温度和速度随着径向距离的增加而减小。这些结果与实验结果基本相符。     

超音速等离子体炬的数值模拟

介绍了描述大气压下超音速等离子体炬内等离子体特性的磁流体力学模型，在二维近似下，对会聚-扩展型喷口等离子体炬进行了数值模拟，获得了等离子体炬内等离子体速度、温度、压力以及马赫数的分布.结果表明超音速等离子体炬内的流场特性可以分为亚音速、跨音速和超音速三个明显的区域. 关键词： 等离子体炬 磁流体力学 数值模拟     

Ar介质感应耦合等离子加热器能量转化与流动特性

对感应耦合等离子(inductively coupled plasma,ICP)加热器内能量转化过程与分布规律、 流动特性的研究和认识能够为高频等离子加热器的设计提供理论指导,同时能够为加热器向大功率、多介质、广适用方向的发展提供支撑.基于二维轴对称、层流流动和局部热力学平衡等假设条件,利用COMSOL对百千瓦级Ar介...     

Numerical simulation and experimental validation of multiphysics field coupling mechanisms for a high power ICP wind tunnel

We take the established inductively coupled plasma(ICP) wind tunnel as a research object to investigate the thermal protection system of re-entry vehicles. A 1.2-MW high power ICP wind tunnel is studied through numerical simulation and experimental validation. The distribution characteristics and interaction mechanism of the flow field and electromagnetic field of the ICP wind tunnel are investigated using the multi-field coupling method of flow, electromagnetic, chemical, and thermodynamic field. The accuracy of the numerical simulation is validated by comparing the experimental results with the simulation results. Thereafter, the wind tunnel pressure, air velocity, electron density, Joule heating rate, Lorentz force, and electric field intensity obtained using the simulation are analyzed and discussed. The results indicate that for the 1.2-MW ICP wind tunnel, the maximum values of temperature, pressure, electron number density, and other parameters are observed during coil heating. The influence of the radial Lorentz force on the momentum transfer is stronger than that of the axial Lorentz force. The electron number density at the central axis and the amplitude and position of the Joule heating rate are affected by the radial Lorentz force. Moreover, the plasma in the wind tunnel is constantly in the subsonic flow state, and a strong eddy flow is easily generated at the inlet of the wind tunnel.     

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对感应耦合氩气热等离子体的速度分布特性以及各操作参数对等离子体速度分布的影响进行了细致的研究。研究结果表明,与直流电弧热等离子体相比,感应耦合热等离子体速度小,弧流集中,速度峰值出现在等离子体炬下游,在线圈段上游出现明显的回流现象。此外,送气流量、感应电流等操作参数对等离子体速度分布有明显影响。研究结果可为等离子体球化粉末颗粒及其他应用提供理论指导。     

基于COMSOL 的感应耦合等离子体炬多物理场研究

为了优化锂微粉等离子体球化的工艺,对感应耦合等离子体炬进行二维建模,将电磁场计算域扩展到等离子体放电区域之外的空气区域,利用COMSOL 软件进行多物理场模拟。得到了等离子体的电磁场、温度和速度分布,并对分布形成的物理机制进行分析。模拟发现等离子体区域线圈段存在上下两组对称的回流涡,线圈段中部靠近约束管处等离子体速度分布杂乱,有激烈的径向打壁现象,乱流预计会对约束管壁相应位置造成一条环状的破裂效果。基于模拟结果,提出在采用感应耦合等离子体球化锂微粉的工艺工程中,可以将注粉口下移,绕开上回流涡。     

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In order to optimize the process of plasma spheroidization of the lithium micro-powder, a 2-D model of inductively coupled thermal plasma torch is presented. The calculating domain of the electromagnetic field is extended to the air region outside the plasma discharge region and multi-physics coupling calculation was performed by using COMSOL software. The plasma electromagnetic field, temperature and velocity distributions are obtained. The physical mechanism of distributions is analyzed. The simulation found that there are two sets of symmetrical reflux vortices in the coil section of the plasma region. The velocity distribution which locates in the center of coil section and closes to the wall of confinement tube is in disorder. The plasma particles hit the wall along the radial direction. Disorderly flow may cause a rupture area along the circular tube wall. Based on the simulation results, it is proposed that in the process of inductively coupled plasma spheroidization, powder injection port can be moved down to avoid the upper reflux vortex.     

Numerical simulation of the thermal non-equilibrium flow-field characteristics of a hypersonic Apollo-like vehicle

In order to investigate the relationship between the flow-field parameters outside the vehicle and the altitude, this paper takes the Atmospheric Reentry Demonstrator (ARD) with an angle of attack of -20° as the research object and adopts a two-temperature model coupled with the shear-stress transport k-ω turbulence model to focus on the variation of flow-field parameters including flow-field pressure, Mach number and temperature with the reentry altitude. It is found that the flow-field high-pressure region and low-Mach region both appear in the shock layer near the head of the ARD, while the maximum pressure of the surface appears on the windward side of the ARD's head with a toroidal distribution, and the numerical magnitude is inversely proportional to the radius of the torus. With fluid through the shoulder of the ARD flow expansion plays a dominant role, the airflow velocity increases, the Mach number of the windward side of the rear cone increases and the flow-field pressure and surface pressure rapidly decrease. When the fluid passes through the shock layer, the translational-rotation temperature will increase before the vibration-electron temperature, there is a thermal non-equilibrium effect and the two temperatures will rapidly decrease again when approaching the surface of the ARD due to the existence of temperature gradient. At the same time, both the windward side of the shoulder and the back cover of the ARD suffer from a large thermal load and require thermal protection.     

保护气对切割弧特性影响的模拟研究

通过比较两种不同结构切割炬所产生的等离子体流场,发现保护气对等离子体的温度和速度分布影响很小.垂直保护气在切割炬喷口形成阻碍作用,造成切割炬内的压强有所升高,但是增加不大.两种结构保护气对切割弧的影响只是在炬喷口外的激波附近.加入保护气后激波的强度会减弱.相对于没有保护气的情况,保护气增加冷却作用,弧电压会略有升高.当改变保护气的成分时,发现弧柱区的氧气含量不受影响,所以保护气成分的改变不会影响到弧电压.计算发现轴线处氧气和周围气体的混合很少,在喷口下游10mm处,氧气的摩尔分数仍在90%以上. 关键词： 等离子体切割弧 保护气 数值模拟     

Gas flow characteristics of argon inductively coupled plasma and advections of plasma species under incompressible and compressible flows

In this work, incompressible and compressible flows of background gas are characterized in argon inductively coupled plasma by using a fluid model, and the respective influence of the two flows on the plasma properties is specified. In the incompressible flow, only the velocity variable is calculated, while in the compressible flow, both the velocity and density variables are calculated. The compressible flow is more realistic; nevertheless, a comparison of the two types of flow is convenient for people to investigate the respective role of velocity and density variables. The peripheral symmetric profile of metastable density near the chamber sidewall is broken in the incompressible flow. At the compressible flow, the electron density increases and the electron temperature decreases. Meanwhile, the metastable density peak shifts to the dielectric window from the discharge center, besides for the peripheral density profile distortion, similar to the incompressible flow.The velocity profile at incompressible flow is not altered when changing the inlet velocity, whereas clear peak shift of velocity profile from the inlet to the outlet at compressible flow is observed as increasing the gas flow rate. The shift of velocity peak is more obvious at low pressures for it is easy to compress the rarefied gas. The velocity profile variations at compressible flow show people the concrete residing processes of background molecule and plasma species in the chamber at different flow rates. Of more significance is it implied that in the usual linear method that people use to calculate the residence time, one important parameter in the gas flow dynamics, needs to be rectified. The spatial profile of pressure simulated exhibits obvious spatial gradient. This is helpful for experimentalists to understand their gas pressure measurements that are always taken at the chamber outlet. At the end, the work specification and limitations are listed.     

Comparative measurements on thermal plasma jet characteristics inatmospheric and low pressure plasma sprayings

The ion and electron temperatures and plasma flow velocities are measured and compared between atmospheric and low pressure plasma spraying systems. The measurements of ion temperature for two systems are carried out by an optical emission spectroscopy which uses the relative emissivities of isolated Ar I emission lines. The electron density and temperature are measured by a Langmuir probe rotating across the plasma jets. The ion saturation currents collected by a Mach probe at two orientations, perpendicular and parallel to the plasma jet, determine the flow velocity. The spatial distributions of electron density, plasma flow velocity, and the associated shock activity in thermal plasma jets are discussed in conjunction with their direct dependency upon the ambient pressures as well as the torch powers. Measurements on temperatures and velocity profiles of thermal plasma jets reveal the general features of the LPPS jet characteristics, i.e., higher velocity flow with lower temperature, longer heating zone of expanded flame, and more extended accelerating zone compared with those of the APS jets. The shock activity clearly exists in the form of standing shock waves in the plasma jet of LPPS in view of flow compression and abrupt velocity drop which are appeared in the results of measurements on the variations of electron density and flow velocity along the plasma jet. In the center of the plasma jet of APS, the electron density is high enough to reach the LTE criterion, and the difference between ion and electron temperatures becomes insignificant as the torch input power increases