电感耦合等离子体原子光谱光源工作气体的现状与发展

电感耦合等离子体(ICP)光源氩气用量通常超过12L/min,是ICP光谱仪运行分析的最主要的消耗品,价格较贵。现介绍并评论多种低氩气耗量ICP光源,包括低气流炬管、水冷炬管、微型ICP炬管、双原子分子气体光源及混合气体光源等。讨论了节省氩气ICP光源技术的最新发展。

EXPERIMENTAL INVESTIGATION ON INDUCED FLOW VELOCITY OF PLASMA AERODYNAMIC ACTUATION

Plasma flow control is an active flow control technology that based on the plasma aerodynamic actuation. It can be used to enhance the aerodynamic characteristics of aircraft and propulsion systems. To study the phenomena occurring in plasma aerodynamic actuation and the mechanism of plasma flow control, the induced flow velocity of the plasma aerodynamic actuator is experimentally investigated under a variety of parameter conditions. The results indicate that plasma aerodynamic actuation accelerates the near surface air at velocities of a few meters per second, and there is an angle about 5° between the mainstream and the actuator wall and a spiral vortex is formed when the induced flow is moving along the wall. Besides, with the fixed frequency, the induced flow velocity increases linearly with the applied voltage, but it is insensitive to the frequency when the applied voltage is fixed. And the configuration is an effective factor for the performance of the plasma aerodynamic actuator.

A comparison among optical emission spectroscopic methods of determining electron temperature in low pressure argon plasmas

In this article, four kinds of optical emission spectroscopic methods of determining electron temperature are used to investigate the relationship between electron temperature and pressure in the cylindrical plasmas of dc glow discharges at low pressures in laboratory by measuring the relative intensities of ArI lines at various pressures. These methods are developed respectively on the basis of the Fermi-Dirac model, corona model, and two kinds of electron collision cross section models according to the kinetic analysis. Their theoretical bases and the conditions to which they are applicable are reviewed, and their calculation results and fitting errors are compared with each other. The investigation has indicated that the electron temperatures obtained by the four methods become consistent with each other when the pressure increases in the low pressure argon plasmas.

Non-Thermal Plasma Assisted Reforming of Ethanol in Dynamic Plasma-Liquid Systems

The paper presents experimental and theoretical studies of non-thermal plasma assisted reforming of liquid ethanol into hydrogen-rich syngas in dynamic plasma-liquid systems （PLS） using electric DC and pulsed discharges in a gas channel with liquid wall （DGCLW） and DC discharge in a reverse vortex gas flow of Tornado type with ＂liquid＂ electrode （TORNADO-LE）. Results of experiments show the energy efficiency of plasma-chemical conversion of ethanol in studied systems. Results of model calculations explain the kinetic mechanism of non-equilibrium plasma-chemical transformations in different conditions. The proposed technique of plasma-fuel reforming can be used in alternative biofuels combustion technologies in advanced diesel engines and power plants.

Development of an Emulator for the Plasma Process Control

This work aims at developing an automatic system for the control of the APS （air plasma spraying） plasma process in which some instability phenomena are present. APS is a versatile technique to produce coatings of powder material at high deposition rates. Using this technique, powder particles are injected into a plasma jet, where they are melted and accelerated towards a substrate. The coating microstructures and properties depend strongly on the characteristics of the plasma jet, which can be controlled by the adjustment of the process parameters. However, the imeractions among the spray variables, render optimization and control of this process are quite complex. Understanding relationships between coating properties and process parameters is mandatory to optimize the process technique and the product quality. We are interested in this work to build an on-line control model for the APS process based on the elements of artificial intelligence and to build an emulator that replicates the dynamic behavior of the process as closely as possible.

电弧加热器铜污染组分效应发射光谱定量研究

电弧加热器是研究飞行器气动热防护问题的重要地面试验平台,其采用电极放电加热获得高温气体的方式,会产生铜蒸汽粒子,并随同进入地面试验模拟的等离子体气流,产生电弧风洞地面试验铜污染组分效应。本研究利用发射光谱诊断技术,发展了一套电弧加热器高温流场组分在线诊断测量系统,开展对10 MW高焓叠片式电弧加热器铜电极烧蚀的在线测量,获得了铜原子浓度的实时测量结果。基于所选铜原子谱线,开展了对电弧加热器起弧过程和稳定工作过程的测量,同时分析了管式电极和环形电极下电极烧蚀的情况。研究结果表明:起弧瞬间,电极烧蚀较明显,管式电极的铜原子峰值浓度要明显高于环形电极;稳定工作后,环形电极铜原子烧蚀量迅速下降,并保持在一个较低水平(<10-6),管式电极仍然存在较高、不稳定的烧蚀,显示管式电极的烧蚀量要明显高于环形电极,且管式电极烧蚀量随着电弧加热器运行电流的增加而增加。基于该测量结果,建立了判定电极失效的直接判据,并用于保障电弧加热器运行安全。为研究电弧加热器电极烧蚀及地面试验铜污染组分效应提供了非接触式测量手段,目前,该测量系统已经作为电弧加热器的常规测试手段,提供电弧加热器高温气流的在线诊断。

Low Speed Axial Compressor Stall Margin Improvement by Unsteady Plasma Actuation

This research investigates the use of single dielectric barrier discharge(SDBD) actuators for energizing the tip leakage flow to suppress rotating stall inception and extend the stable operating range of a low speed axial compressor with a single rotor.The jet induced by the plasma actuator adds momentum to the flow in the tip region and has a significant impact on the tip-gap flow.Experiments are carried out on a low speed axial compressor with a single rotor.The static pressure is measured at both the rotor inlet and outlet.The flow coefficient and pressure rise coefficient are calculated.Then the characteristic line is acquired to show the overall performance of the compressor.With unsteady plasma actuation of 18kV and 60W the compressor stability range improvement is realized at rotor speed of 1500 r/min – 2400 r/min.

Computational and experimental analysis of Mach 2 air flow over a blunt body with plasma aerodynamic actuation

According to the mechanism of the arc plasma heating effect,and from a phenomenological perspective of view,the plasma actuation was simplified as heating energy injected into the supersonic flow field for the numerical research on controlling detached shock of the blunt body in non-center symmetrical positions.Besides,experimental research on the form and strength of detached shock wave control by plasma aerodynamic actuation in non-center symmetrical positions was conducted in a high-speed shock tunnel(M=2).The results showed that the detached distance of shock wave increased and the strength of normal shock wave ahead of the detached shock wave reduced when plasma actuation was applied.The control effect was greatly improved after the magnetic field was applied and the effect of upwind-direction flow was the best one.When the upwind-direction flow was applied with 1000 V voltage actuation,the distance of detached shock wave would increase from 3.4 to 7.6 mm and the time average strength of normal shock wave was weaken by 5.5%.At last,the mechanism of plasma actuation on controlling the detached shock wave was briefly analyzed.

Aerodynamic control of NACA 0021 airfoil model with spark discharge plasma synthetic jets

Spark discharge plasma synthetic jets(SPJs) have been used for the active flow control study on an NACA 0021 straight-wing model in a wind tunnel. The model forces and moments were measured using a six-component sting balance at a 20 m/s wind speed. The aim was to explore the SPJ's effect on airfoil aerodynamic by examining SPJ generators' position along the chordwise and the jet flow direction about the chord. Near the wing leading edge, two SPJ generators raised the stall angle by 2° and increased the maximum lift coefficient by 9%. The drag coefficient was decreased by 33.1%, and the lift-drag ratio was increased by 104.2% at an angle of attack above 16°. The rolling-moment coefficient was modified by 0.002, and the yawing-moment coefficient was changed by 0.0007 at angles of attack in the range of 0°–16°. The results showed that SPJs can control wing aerodynamic forces at a high angle of attack and moments at a low angle of attack.