关于HL—1M马赫探针及其诊断数据处理

在简要回顾了马赫探针主要物理模型的基础上,论述了ＨＬ－１Ｍ装置的马赫探针诊断。分析表明,马赫探针阵列设计中的问题和对非平行流数据处理物理模型上的问题,导致处理所得物理实验数据失去意义,为了获得可靠结果,建议改进探针阵列设计,并采用正确数据处理方法。     

金刚石镀膜装置中的等离子体参数测量

利用平行马赫探针和单探针对金刚石镀膜装置中的等离子体漂移速度、,离子密度及电子温度进行了测量,采用ＣｈｕｎｇＫｙｕ－Ｓｕｎ理论对平行马赫探针数据进行分析得到的马赫数为０．２８,电子温度为５ｅＶ,等离子体流速约为９８０ｍ．ｓ＾－１。单探针测行离子密度在１０＾１８～１０＾２０ｍ＾－３的范围内,电子温度在２－８ｅＶ的范围内。     

利用x射线激光干涉诊断等离子体电子密度

x射线激光探针干涉方法是诊断高温高密度激光等离子体电子密度等信息的重要工具.利用神光Ⅱ装置输出激光驱动的类镍-银x射线激光作为探针，成功地进行了马赫-曾德尔干涉法诊断实验，获得了清晰的包含等离子体信息的动态干涉条纹图像，并据此给出了待测C8H8等离子体临界面附近电子密度的空间分布. 关键词： 等离子体电子密度诊断 x射线激光 马赫-曾德尔干涉仪     

HL-1M装置边缘等离子体结构研究

描述HL-1M装置上几种典型放电中的边缘等离子体物理实验结果.利用马赫/朗缪尔6探针组、静电4探针组、20组三探针阵列研究了低杂波电流驱动、超声分子束注入、多发弹丸注入和中性束注入放电中的粒子约束性能、等离子体旋转和边缘静电雷诺胁强的变化对改善约束的影响.给出了雷诺胁强和极向相速度的关系.结果表明，雷诺胁强的径向变化可以自发产生托卡马克等离子体的剪切极向流.LHCD能使低密度放电的粒子约束增加1至2倍.弹丸注入后，粒子约束时间和极向旋转至少可增加1倍，而SMBI可使粒子约束时间增加约一个数量级并取得高性能等离子体. 关键词： 粒子约束 雷诺胁强 极向流剪切 马赫/朗缪尔6探针组     

HL—1M装置边缘等离子体测量

本文研究了ＨＬ－１Ｍ装置运行初期第一壁材料对等离子体删削层杂质流通量及分布的影响，并与ＨＬ－１装置的结果进行比较。利用热通量探针测量，给出了ＨＬ－１和ＨＬ－１Ｍ装置删削层的热通量分布。在不同运行状态下，利用马赫探针组，测量了ＨＬ－１Ｍ装置边缘等离子体流的变化特性。     

单发次测量软X射线多层膜分束镜光学特性实验

用X射线激光作为探针，探测激光等离子体临界面附近的电子密度，对惯性约束聚变(ICF)的研究具有很大的应用价值。2003年11月，在“神光”Ⅱ装置上进行的X射线激光干涉法诊断等离子体电子密度实验研究取得了重大进展：利用类镍-银X射线激光作为探针，采用分束镜分光的马赫-贞德尔干涉仪在国内首次拍摄到清晰的动态干涉图。     

弹丸和超声束流注入对边缘电场和等离子体旋转的影响

在欧姆放电，超声束流入和多发弹丸注入期间，利用马赫／朗缪尔探针组测量了ＨＬ－１Ｍ装置刮层和边界层的边缘电场和等离子体旋转；环向马赫数Ｍａ、极向流速度ｖｐｏｌ和电场Ｅｒ的径向分布是分别在超声束注入和多发弹丸注入期间进行测量的。     

HL-1M装置边缘参数测量

在HL－1M装置上利用马赫／郎缪尔探针分别在欧姆放电,低杂波注入,中性束注入,离子回旋加热和电子回旋加热等情况下测量下刮离层和等离子体边缘的极向流速度和电场,得到了它们的径向分布,研究了LHW,NBI,ICRH和ECRH对改善等离子体约束性能,边缘粒子的径向传输的影响。     

激光应用 其他应用

TL653 2005042666 利用X射线激光干涉诊断等离子体电子密度=Experi- mental diagnose of plasma electron density by interferome- try using an X-ray laser as probe[刊,中]／王琛(上海激光等离子体研究所,上海(201800)),王伟…／／物理学报．- 2005,54(1),-202-205 X射线激光探针干涉方法是诊断高温高密度激光等离子体电子密度等信息的重要工具。利用神光Ⅱ装置输出激光驱动的类镍-银X射线激光作为探针,成功地进行了马赫-曾德尔干涉法诊断实验,获得了清晰的包含等离     

HL-2A装置边缘等离子体参数测量

等离子体的杂质含量由杂质源分布以及SOL和芯部等离子体中各种杂质输运过程确定。HL-2A装置主真空室的活动马赫／雷诺协强／朗缪尔10探针阵列具有很高的时间和空间分辨能力，能够直接测量边缘等离子体参数并研究边缘扰动和相关特性。大量的实验表明：约束的改进与旋转速度的增加和边缘涨落的下降密切相关。     

Effect of neutral pressure on the He plasma flow measurement in a linear device

Axial and azimuthal flow velocities have been measured in a linear plasma device called NAGDIS-II (NAGoya DIvertor Simulator-II), along with plasma density and electron temperature, using a vector Mach probe composed of two Mach probes, one of which is for the axial flow, and the other is for the azimuthal flow. To study the effect of neutral pressure on the deduction of the Mach numbers, the ratio of upstream to downstream currents are measured by changing the neutral pressure for the deduction of flow velocities. Helium plasma was generated with pressure of 2–35 mTorr. Since the ion gyro-radius at the magnetic flux of 300 G is larger than the probe size, an unmagnetized collisionless Mach probe theory was used for the deduction of Mach numbers and their variations. In order to check the range of collisionality, plasma density (n_e = 10¹⁰–10¹¹ cm^?3) and electron temperature (T_e = 2–9 eV) are measured by a single electric probe using a conventional collisionless probe theory. Variations of Mach number, electron temperature and plasma density with collisionless models are to be compared with those using collisional models for different pressures where ionization and ion-neutral collision are included. Mach numbers by the collisionless model are found to be overestimated by 120% for the maximum difference even in weakly collisional plasmas. A clear flow reversal exists in the axial direction with higher pressure plasma, even in the linear machine. Azimuthal flows are also measured simultaneously along with axial flows, yet they seem to be very small in the present cold ion plasma (T_i/T_e << 1).     

HL-2A 装置的边缘参数测量

HL-2A 装置中平面边缘的等离子体特性通过磁力传动的马赫/ 雷诺协强/ 朗缪尔10 探针组进行了研究。10 探针组安装在可径向向里和向外移动, 并可绕轴旋转360^o 的传动杆上, 用于测量主等离子体边缘的温度、密度、悬浮电位、空间电位、径向和极向电场、湍流的雷诺协强、径向和极向等离子体流速及其径向分布。HL- 2A 装置的实验结果表明, 边缘等离子体扰动诱发的雷诺协强产生了边缘极向流; 雷诺协强的径向梯度驱动带状流抑制了湍流输运。     

A negative biasing experiment to test numerical calculations basedon a neoclassical L-H transition model in stellarators

Numerical calculations based on Shaing's L-H transition theory in stellarators and performed by Dahi et al. determine viscosity as a function of ion flow speed in the interchangeable module stellarator (IMS). The calculations predict local maximums in viscosity at flows corresponding to Mach numbers -2 and -10, but not elsewhere. The local peaks manifest themselves as jumps in flow speed, and as regions of high radial electric field (E_r) shear. By inducting flows swept between Mach numbers ±5, an electron injection biasing probe revealed a jump at -2, but none at +2, in agreement with the numerical results. A series of flow profiles at constant bias confirmed this result. Altogether, these data agree well with the numerical calculations and provide support for Shaing's L-H transition model as applied to stellarators     

Thermal grating velocimetry

A method is reported for time- and space-resolved nonintrusive velocimetry of high-speed gas flows by measurement of the Doppler shift of light scattered from a laser-induced thermal grating. The principle is demonstrated by use of a pulsed frequency-doubled Nd:YAG laser to induce a thermal grating in NO(2) seeded into an argon flow. Signals are generated by Bragg scattering of probe beams at the fundamental frequency of the same Nd:YAG laser. Flow velocities in the range 30-180 ms(-1) are measured, in agreement with values obtained with a Pitot tube. The measurement uncertainties obtained indicate that a precision of 1% is feasible for flows at Mach 1.     

Alleviation of cancellation problem of preconditioned Navier–Stokes equations

An approach to alleviate the cancellation problem of preconditioned Navier-Stokes equations is proposed. Adiabatic laminar viscous flows around a circular cylinder are calculated at different Mach numbers. It is shown that a redefinition of total enthalpy to reduce the magnitude of total enthalpy can alleviate the cancellation problem for adiabatic laminar flows at low Mach numbers.     

Probe Method for Measuring the Mach Number and the Flow Vector in Edge Plasma

A planar Mach probe to measure the Mach number and the flow vector with respect to the magnetic field in the edge plasma of e.g. a tokamak is being proposed. The probe is constructed as a double probe and the saturation ion current is measured as function of the angle of rotation of the probe surface normal with respect to the magnetic field. The saturation current as function of the angle is calculated by taking a drifted Maxwellian distribution for ions and an effective size of the probe depending on the angle. From the ratio of the saturation currents for plus and minus biases respectively and from the envelope of the saturation current with respect to the rotation angle, the Mach number and the flow vector can be determined.     

任意马赫数非定常流动数值模拟的统一算法

发展适用于从低速到高速任意马赫数非定常流动数值模拟的统一算法.通过引入一个伪时间导数项和一个新的预处理矩阵,得到双时间非定常预处理可压缩Navier-Stokes方程.方程的对流项采用三阶Roe通量近似差分格式离散,粘性项采用二阶中心差分格式离散.基于数值通量的线性化技术,实现伪时间步的隐式ADI-LU格式迭代,进而获得物理时间步的二阶推进精度.重点以低马赫数流动为例,求解了圆柱绕流和NACA0015翼型等速上仰动态失速问题.计算结果表明该统一算法能够较好地模拟低马赫数乃至任意马赫数非定常流动.     

Measurement of Mach probe on plasma flow velocity in highly collisional plasma jet

A normalized plasma flow velocity in highly collisional plasma formed by a microwave plasma jet, which is dimensionless unit for plasma flow velocity/ion acoustic velocity, was measured by the parallel Mach probe. To deduce the normalized plasma flow velocity under highly collisional plasma conditions, the collisional model of a Mach probe was proposed. In addition, neutral gas flow velocity which assumed to be plasma flow velocity was calculated by the turbulent model. The results for the two different models were compared with those for the collsionless models of the Mach probe. The turbulent model produced 2–4 times reduced values than by measurements with collsionless models. The measured results with the collisional model were shown as approximately 100–250% lower than those for collsionless models. They were obtained to be in good agreement with difference rate of 10–30% when compared to those for the turbulent model.     

基于预处理HLLEW格式的全速域数值算法

基于HLLEW(Harten-Lax-Van Leer-Einfeldt-Wada)格式引入预处理技术发展适合求解全速域流场的三维Navier-Stokes求解器.引入低速预处理技术,重新构造HLLEW格式的耗散项,给出预处理后的HLLEW格式,并根据预处理后的雅克比矩阵构造相应的隐式时间推进方程.利用预处理方法求解NACA 4412低速不可压流动与RAE 2822跨声速可压缩流动,并与实验结果及原有方法的计算结果对比.结果表明:预处理HLLEW格式不仅提高低速不可压缩流动的计算效率和精度,也保持了对可压缩流动的处理能力,是一种适用于全速域流场数值模拟的有效方法.