边界层效应影响等离子体气动激励诱导激波机理

 针对小型暂冲式超声速风洞进行的诱导激波实验结果,提出等离子体气动激励诱导激波的机理不仅取决于放电时产生的焦耳热效应,放电区域的边界层厚度也起到了决定性的作用的推论。为进一步验证此思想,在高超声速激波风洞进行了等离子体气动激励诱导激波的实验研究。结果表明,在边界层很薄的情况下,等离子体气动激励能够诱导出斜激波。分别阐述了两种实验条件下诱导激波的机理,证实了边界层效应在等离子体与激波相互作用中起到了决定性作用。     

等离子体气动激励对气膜冷却特性的影响

采用大涡模拟方法研究了锯齿电极等离子体激励器气动激励对圆形孔和扇形孔平板气膜冷却效率和气动损失的影响。结果表明:锯齿电极激励器气动激励产生的动量注入效应促使边界层流体加速而提高了冷却气流向下游的延伸能力;锯齿电极激励器气动激励诱导的反肾形涡对削弱了肾形涡对的强度与尺度,减少了下游冷、热流体间的掺混,使得扇形孔的中心线和展向平均气膜冷却效率相对于圆形孔最大提高了130%和300%,肾形涡对控制区内的掺混总压损失显著减小;锯齿电极激励器气动激励导致气膜孔内的流动损失略有增大而使其成为影响总压损失的重要因素;锯齿电极激励器气动激励导致圆形孔的熵增升高了26%,但使得扇形孔的熵增减小了41%。     

等离子体气动激励器布局对放电特性与加速效果的影响

在常规大气环境下,对常规、半圆和锯齿三种不同布局的等离子体气动激励器的放电特性与加速效果进行了实验研究,对不同激励参数下的频率与放电电压和频率与放电电流以及等离子体气动激励器诱导的边界层速度进行了测量。实验结果表明：当等离子气动激励器基本设计参数相同时,布局形式的改变使得放电电压和放电电流参数值发生变化,但其谐振频率保持不变,诱导气流速度则相应的发生改变;实验中还发现,半圆、锯齿等离子体气动激励器放电时离子流对绝缘材料有很强的破坏作用。     

介质阻挡放电等离子体对近壁区流场的控制的实验研究

采用粒子图像测速仪对介质阻挡放电等离子体在静止流场中诱导出的速度场、等离子体激励对平板附面层的改变进行了研究.实验结果表明,等离子体激励作用主要集中在近壁面附近;激励电压与诱导速度近似为线性关系,激励频率对诱导速度的影响不大.将等离子体流动控制原理初步归纳为撞击效应和热效应,并通过数值模拟的方法研究了热效应对等离子体激励诱导速度场的影响.数值模拟结果表明,在无来流的情况下等离子体热效应对流场的影响比较明显,使局部水平方向速度大小提高近30%.简要介绍了提高等离子体激励强度的方法. 关键词： 介质阻挡放电等离子体 流动控制 边界层     

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。     

介质阻挡放电等离子体流动控制实验研究

通过平板实验和压气机叶栅实验研究了介质阻挡放电等离子体所产生的电动力对外流流动和内流流动边界层的加速作用.平板实验中采用LDV测量了介质阻挡放电等离子体在静止流场中诱导出的速度场,并研究了激励电压和频率对诱导速度大小的影响;在不同来流速度情况下,测量了等离子体激励对速度剖面的改变.通过低负荷和高负荷压气机叶栅实验,利用三孔探针研究了等离子体激励对栅后总压、速度以及流动分离的影响.实验中发现,流速低于20 m/s时,加电产生等离子体后,可显著改善栅后总压和速度分布;流速接近50 m/s时,等离子体仍会明显改变总压和速度的最小值;在低速下等离子体激励抑制流动分离是有效的.     

多相等离子体气动激励流动特性

 等离子体激励器电极组相位不同便产生多相等离子体气动激励,建立了粒子图像测速仪流场参数测试系统,利用粒子图像测速仪技术,研究了非对称布局等离子体气动激励诱导空气流动特性,分析了多相等离子体气动激励对诱导空气流动速度的影响。结果表明：粒子图像测速仪流场测试系统能够准确地反映等离子体气动激励诱导空气流动的流场空间结构,等离子体气动激励诱导空气流动是平行于激励器的近壁面射流,多相等离子体气动激励能够增大等离子体气动激励诱导气流速度,或者使等离子体气动激励影响流场区域增大。粒子图像测速仪系统是深入研究等离子体气动激励的流场结构最佳的方式之一。     

介质阻挡放电等离子体与激波相互作用实验研究

 主要针对介质阻挡放电等离子体改变激波系结构展开了实验研究。验证了介质阻挡放电等离子体气动激励能够对边界层施加影响,顺气流放电时能减小激波强度,逆气流放电时能增大激波强度。逆气流放电时,3组电极放电与4组电极放电比较,3组电极放电时压比更高。由于在该实验中放电区域比边界层小得多,介质阻挡放电产生的体积力远小于高速来流条件下的气动力,因此对激波的作用效果十分微弱。     

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基于介质阻挡放电等离子体的体积力气动激励机理,仿真研究了等离子体增升减阻技术对沿螺旋桨桨径方向均匀分布的10个叶素气动特性的改善效果.采用叶素理论,对比分析了等离子体对螺旋桨整体气动性能的提高效果.主要结论有:桨尖和桨叶根部的叶素容易发生气动分离现象,其中根部叶素处于负攻角的工况中;采用介质阻挡放电等离子体流动控制技术可以完全抑制流动分离不太严重的桨叶中部区域的叶素气动分离,对桨尖处翼型的严重气动分离不能完全抑制但也有改善作用,但对处于负攻角工况的叶素作用不大;等离子体增升减阻技术确实可以提高螺旋桨的气动性能,对本文所研究的情况,螺旋桨的拉力和效率分别提高了28.27％和 12.3％.     

等离子体激励翼型分离流动控制数值模拟

文章利用CFD软件FLUENT中的自定义函数接口, 将等离子体对中性气体的激励作用模型化为体积力引入Navier-Stokes方程, 研究了等离子体气动激励诱导的平板射流, 以及介质阻挡放电(dielectric barrier discharge, DBD)等离子体激励对NACA0015翼型大迎角分离流的控制作用.计算分析表明, 多对电极等离子体激励器可以有效控制NACA0015翼型大迎角分离流动.      

等离子体气动激励机理数值研究

基于介质阻挡与准直流电弧放电的物理过程, 分析了它们的气动激励机理, 建立了各自的气动激励模型, 并分别研究了它们对低速和超声速流动的激励效果. 结果显示: 介质挡板放电等离子体气动激励机理是改变了连续流体中的三种力, 即由牛顿内摩擦引起的剪切应力、由电动力学引起的体积力及由压力突变引起的冲击力, 其中基于电动力学的体积力效应占主导地位; 临近空间环境中体积力的作用效果更强, 诱导速度更大; 超声速来流下准直流电弧放电气动激励机理主要是等离子体的热阻塞效应, 本文所建立的爆炸丝传热模型可以用于仿真其控制激波的过程; 热电弧对于超声速来流而言就像一个具有一定斜坡角度的虚拟突起, 可用于高超声速飞行器前体激波的控制.     

Experimental investigation of nanosecond discharge plasma aerodynamic actuation

In this paper we report on an experimental study of the characteristics of nanosecond pulsed discharge plasma aerodynamic actuation. The N 2 (C 3 Π u ) rotational and vibrational temperatures are around 430 K and 0.24 eV, respectively. The emission intensity ratio between the first negative system and the second positive system of N 2 , as a rough indicator of the temporally and spatially averaged electron energy, has a minor dependence on applied voltage amplitude. The induced flow direction is not parallel, but vertical to the dielectric layer surface, as shown by measurements of body force, velocity, and vorticity. Nanosecond discharge plasma aerodynamic actuation is effective in airfoil flow separation control at freestream speeds up to 100 m/s.     

Aerodynamic actuation characteristics of radio-frequency discharge plasma and control of supersonic flow

In this paper, aerodynamic actuation characteristics of radio-frequency(RF) discharge plasma are studied and a method is proposed for shock wave control based on RF discharge. Under the static condition, a RF diffuse glow discharge can be observed; under the supersonic inflow, the plasma is blown downstream but remains continuous and stable.Time-resolved schlieren is used for flow field visualization. It is found that RF discharge not only leads to continuous energy deposition on the electrode surface but also induces a compression wave. Under the supersonic inflow condition, a weak oblique shock wave is induced by discharge. Experimental results of the shock wave control indicate that the applied actuation can disperse the bottom structure of the ramp-induced oblique shock wave, which is also observed in the extracted shock wave structure after image processing. More importantly, this control effect can be maintained steadily due to the continuous high-frequency(MHz) discharge. Finally, correlations for schlieren images and numerical simulations are employed to further explore the flow control mechanism. It is observed that the vortex in the boundary layer increases after the application of actuation, meaning that the boundary layer in the downstream of the actuation position is thickened. This is equivalent to covering a layer of low-density smooth wall around the compression corner and on the ramp surface, thereby weakening the compressibility at the compression corner. Our results demonstrate the ability of RF plasma aerodynamic actuation to control the supersonic airflow.     

The characteristics of surface arc plasma and its control effect on supersonic flow

The characteristic of surface arc plasma included millisecond and microsecond actuation in supersonic flow is investigated both experimentally and numerically. In the experiment, the discharge characteristic of surface arc plasma in quiescent air and supersonic flow is recorded. The stable oblique shock could be observed with millisecond actuation. And the unstable compressive wave could be also observed with microsecond actuation. In the numerical investigation, plasma actuation is defined as a source term with input power density from discharge V–I characteristic, which is expected to better describe the influence of heating process. The numerical results are coincident with experimental results. In order to confirm the capability of surface arc plasma actuation to control supersonic flow, experimental investigations on control shock induced by ramp and separation of boundary layer induced by impinging shock are performed. All the results demonstrate the control effect of surface arc plasma actuation onto supersonic flow.     

Dynamic evolution of vortex structures induced by tri-electrode plasma actuator

Plasma flow control is a new type of active flow control approach based on plasma pneumatic actuation.Dielectric barrier discharge(DBD) actuators have become a focus of international aerodynamic research.However,the practical applications of typical DBDs are largely restricted due to their limited discharge area and low relative-induced velocity.The further improvement of performance will be beneficial for engineering applications.In this paper,high-speed schlieren and high-speed particle image velocimetry(PIV) are employed to study the flow field induced by three kinds of plasma actuations in a static atmosphere,and the differences in induced flow field structure among typical DBD,extended DBD(EX-DBD),and tri-electrode sliding discharge(TED) are compared.The analyzing of the dynamic evolution of the maximum horizontal velocity over time,the velocity profile at a fixed horizontal position,and the momentum and body force in a control volume reveals that the induced velocity peak value and profile velocity height of EX-DBD are higher than those of the other two types of actuation,suggesting that EX-DBD actuation has the strongest temporal aerodynamic effect among the three types of actuations.The TED actuation not only can enlarge the plasma extension but also has the longest duration in the entire pulsed period and the greatest influence on the height and width of the airflow near the wall surface.Thus,the TED actuation has the ability to continuously influencing a larger three-dimensional space above the surface of the nlasma actuator.     

Effect of convection and heat conduction on the laser gain in a nonequilibrium recombinational hydrogen wall plasma

The effect of a conducting body with a large heat capacity on the thermal state of a hydrogen plasma in the boundary surface layer is analyzed. It is shown that, under certain conditions, the energy accumulated in the plasma within the boundary layer can be efficiently transferred to the conducting body; this leads to plasma overcooling. The mathematical model of plasma incorporates mechanisms for convective heat exchange and heat conduction. The possibility is analyzed of the existence of nonequilibrium recombination states with inverse population in the overcooled wall plasma. It is shown that the maximum gain (a few tenths of cm^?1) on hydrogen nuclei is achieved at the 3-2 transition for the following initial parameters: the plasma pressure is 1–3 atm, the plasma temperature is 0.5 eV, the tungsten surface temperature is 300 K, and the body radius is 0.5–1.0 m.     

Endogenous magnetic reconnection and associated high energy plasma processes

An endogenous reconnection process involves a driving factor that lays inside the layer where a drastic change of magnetic field topology occurs. A process of this kind is shown to take place when an electron temperature gradient is present in a magnetically confined plasma and the evolving electron temperature fluctuations are anisotropic. The width of the reconnecting layer remains significant even when large macroscopic distances are considered. In view of the fact that there are plasmas in the Universe with considerable electron thermal energy contents this feature can be relied upon in order to produce generation or conversion of magnetic energy, high energy particle populations and momentum and angular momentum transport.     

电磁流体表面推进机理与效果分析

电磁流体表面推进是在推进单元周围的导电流体中(海水、等离子体等)激励出电磁体积力,并利用电磁体积力的反作用力达到推进的目的. 基于电磁场和流体力学的基本控制方程,采用有限体积法对电磁流体表面推进的效果进行了数值模拟研究,分析了在不同姿态(攻角)和不同电磁体积力的作用下,航行器周围流场结构的变化规律和推力的变化特点.研究结果表明:沿航行器表面分布的电磁体积力可以有效地改变流体边界层的结构,并能向流体边界层传输动量与能量,从而使航行器获得所需的推力.流体对航行器的黏性阻力和压差阻力的影响随作用参数的增大而减弱 关键词： 表面推进 航行器 推进单元 电磁体积力     

Z箍缩等离子体磁重联现象

分析了磁重联对晕等离子体加速和能量平衡过程的影响。分析表明晕等离子体向轴心的加速过程分为两个阶段:第一阶段晕等离子体在磁压或热压(依赖于丝数)作用下向轴心运动;第二阶段晕等离子体由于磁重联过程被加速到阿尔芬速度,并到达轴心形成先驱等离子体。估算表明重联层的厚度与离子的惯性长度具有相同的数量级,电流片内电子运动和离子的运动是解耦合的。在内爆滞止阶段电荷分离产生强的径向电场,这个电场将磁能转化为等离子体轴向(z方向)动能,内爆动能和轴向动能共同转化为X射线辐射能,以此解释了X射线能量大于内爆动能这一观测结果。分析了磁重联电磁脉冲的性质,对于1 MA驱动条件,电磁脉冲的总能量可达kJ量级。