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针对实验室等离子体的辐射物理条件和等离子体箍缩三温的数值模型,提出一种定量计算Z箍缩等离子体辐射能谱的近似方法。在给出计算能谱结构的理论方法之后,再将这种近似计算方法编入到Kr喷气Z箍缩等离子体X射线辐射的二维三温辐射磁流体力学模型中,得出典型Kr喷气Z箍缩X射线辐射的能谱分布。对照"强光一号"加速器Kr喷气箍缩实验测量得到的辐射能谱分布,分析了理论与实测结果之间存在的偏差。     

“阳”加速器上喷气Z箍缩负载特性

介绍了一种用于"阳"加速器的超音速单壳层喷气Z箍缩负载。利用快响应压力探针对喷气负载产生的超音速流场进行了测量,获得了流场中各个位置的冲击压力以及超音速喷嘴前端的驻室压力,结合流体力学公式,给出了流场中的压力和密度分布。气流的径向密度剖面显示,气体壳层的位置随轴向位置的变化而存在差异,并且随着到喷嘴距离的增加,轴心处的气流密度不断增加。对密度分布的径向积分结果表明,气流在靠近喷嘴处的线质量密度最大,距喷嘴越远,线质量密度越小。利用单壳层超音速喷气负载,在"阳"加速器上进行了喷气Z箍缩内爆实验,对内爆过程进行了初步分析,并利用雪耙模型计算了等离子体壳层的内爆轨迹,计算结果与实验测量较好地符合。     

拉瓦尔喷嘴的气流线质量及密度分析

喷气负载是高功率Z箍缩的主要负载之一。应用一维等熵压缩气体动力学，分析了“强光一号”加速器拉瓦尔喷嘴的基本物理过程，获得了拉瓦尔喷嘴出口处气流的马赫数，Ma=4.6，并对其进行了修正，修正值为3.5。利用由雪耙模型导出的Z箍缩聚爆时间表达式，并结合“强光一号”Z箍缩实验结果，修正了由一维等熵气体动力学得到的喷嘴气流线质量表达式。最后根据已知气流的线质量40 μg/cm ，利用B-T模型初步估算了喷嘴的气流密度分布。估算结果为:在轴向2.5~40 mm，径向0~15 mm的区域内，气体分子密度基本在1016～1017/cm3，且在轴向2 cm内基本形成空心的气体壳层结构。     

喷气Z箍缩内爆动力学过程的数值模拟研究

在分析了喷气Z箍缩内爆等离子体物理过程的基础上，作了必要的假定和简化，给出了物理模型和相应的数学方程组.研制了一维三温辐射磁流体动力学的数值模拟程序，对氖喷气Z箍缩内爆产生高温高密度等离子体过程进行了总体数值模拟，得到了等离子体各参量在内爆过程中的时空分布，再现了该内爆动力学整体过程，并与GAMBLE-Ⅱ装置的实验结果进行了比较.计算结果表明，在对热传导系数和等离子体电阻率作适当调整后，得到的计算结果是自洽的，其中内爆到心时刻、x射线辐射脉冲的脉宽和总能量等宏观量与实验结果比较接近.同时对喷气Z箍缩内爆过 关键词： 喷气Z箍缩 x射线辐射 辐射磁流体动力学     

喷气Z箍缩负载的质量线密度确定

 喷气Z箍缩的负载参数（如质量线密度及半径）必须和脉冲驱动源的电流（幅值和上升时间）相匹配。作者利用微型快速电离规测量了喷气Z箍缩中超音速喷嘴产生的气体负载的密度分布，并由此得到了负载质量线密度为43μg/cm，这符合原定的喷嘴设计指标。     

Kr喷气箍缩等离子体的数值研究

 探讨了Z箍缩等离子体辐射磁流体模拟二维三温物理模型及其数值计算方法，针对“强光一号”加速器上Kr喷气实验的具体条件，利用辐射磁流体力学程序Z-pinch 2D-DG模拟了Kr喷气等离子体聚爆过程，分析了X射线辐射的特点，给出了等离子体密度和温度的演化图像以及喷气箍缩中一些带有普遍性的结论。     

多通道软X射线Dante谱仪标定及实验

介绍了用于阳加速器上Z箍缩内爆实验诊断的Dante谱仪的结构和通道配置,详细讨论了X射线二极管、掠入射平面反射镜和滤片等主要元器件的标定结果,分析了标定结果与理论计算发生偏差的原因,给出了喷气Z箍缩等离子体辐射的测量结果,X光辐射功率30～40 GW,能量约0.8 kJ,并与闪烁体光电管测量结果进行了比较,差异约20%。     

多通道软X射线Dante谱仪标定及实验

 介绍了用于阳加速器上Z箍缩内爆实验诊断的Dante谱仪的结构和通道配置,详细讨论了X射线二极管、掠入射平面反射镜和滤片等主要元器件的标定结果,分析了标定结果与理论计算发生偏差的原因,给出了喷气Z箍缩等离子体辐射的测量结果,X光辐射功率30～40 GW,能量约0.8 kJ,并与闪烁体光电管测量结果进行了比较,差异约20%。     

强光一号Z箍缩产生keV级特征X射线初步研究

 分析了高功率Z箍缩产生keV级特征X射线辐射的物理机理和用于计算等离子体K层辐射二能级模型，给出了采用二能级模型进行数值模拟的结果，描述了强光一号装置驱动Z箍缩负载的脉冲功率源特性参数，介绍了所设计研制的双层喷Ne气和双层铝丝阵两类Z箍缩负载的结构与参数，并对下一步拟开展的实验研究工作进行了说明。利用特制真空X射线二极管测量了强光一号双层喷氖气Z箍缩实验产生的X射线波形，实验结果表明，当气室内初始气压在0.8 MPa时，喷Ne气Z箍缩可获得较好的keV量级的X射线辐射。     

应用于Z箍缩等离子体X光产额测量的闪烁体功率计

介绍了在"阳"加速器上使用的闪烁体功率计结构和测量参数,讨论了功率计在北京同步辐射装置上的标定实验,分析了标定结果及由此结果可能给最后实验结果带来的误差,并探讨了修正该误差可行的办法,利用Dante谱仪测得的能谱对功率计测试结果进行修正。修正后,两套设备之间的测试结果差异由原来的30%以上降至15%以内。最后给出了利用软X光闪烁体功率计进行喷气Z箍缩等离子体辐射测量的结果,得到"阳"加速器上喷气Z箍缩负载产生的软X光辐射峰值功率为几十GW,能量产额数百J。     

Acoustic disturbance from gas non-uniformities convected through a nozzle

The non-steady flow generated by convection of gas containing non-uniform temperature regions or “entropy spots” through a nozzle is examined analytically as a source of acoustic disturbance. The first portion of the investigation treats the “compact nozzle”, the case where all wave lengths are much longer than the nozzle. Strengths of transmitted and reflected one-dimensional waves are given for supersonic and subsonic nozzles and for one configuration of supersonic nozzle with normal shock at the outlet. In addition to a wave reflected from the nozzle inlet, the supersonic nozzle discharges two waves, one facing upstream and the other facing downstream. For reasonable values of the nozzle inlet Mach number, the pressure amplitude of each wave increases directly as the discharge Mach number.The acoustic perturbations from a supercritical nozzle of finite length, in which the undisturbed gas velocity increases linearly through the nozzle, are analyzed for several inlet and discharge Mach number values and over a wide frequency range. The results which agree with the compact analysis for low frequency, deviate considerably as the frequency rises, achieving pressure fluctuation levels of several times the compact values. It is shown that this result originates in a phase shift between the two waves emitted downstream and that the pressure fluctuations for moderate frequencies may be approximated from the compact analysis with an appropriate phase shift.In all cases, the pressure fluctuations caused by a 2% fluctuation in absolute inlet temperature are large enough to require consideration in acoustic analysis of nozzles or turbine blade channels.     

Experimental Study of Non-Equilibrium Ionization in a Supersonic CO Flow

Experimental results are presented on ionization processes in the vibrationally non-equilibrium flow of CO preliminarily heated by a shock wave and adiabatically cooled in the supersonic nozzle with a flow Mach number of M = 3.9. It is shown that for a wide range of flow stagnation temperatures, the value of the recorded semi-self-maintained current considerably exceeds the one due to thermal gas ionization in the plenum chamber.     

Influence of the adiabatic index on switching between different types of shock wave reflection in a steady supersonic gas flow

A comprehensive pattern of different types of shock wave reflection in a steady supersonic gas flow is analytically constructed with regard to a new wave configuration found by the authors-negative-angle irregular reflection. A double Mach reflection with a negative reflection angle in a steady supersonic gas flow is numerically obtained for the first time.     

Effect of stagnation temperature on the supersonic axisymmetric minimum length nozzle conception with application for air

When the stagnation temperature of a perfect gas increases, the specific heats and their ratio do not remain constant any more and start to vary with this temperature. The gas remains perfect; its state equation remains always valid, except, it is named in more by calorically imperfect gas. The aim of this work is to trace the profiles of the supersonic axisymmetric Minimum Length Nozzle to have a uniform and parallel flow at the exit section, when the stagnation temperature is taken into account, lower than the dissociation threshold of the molecules, and to have for each exit Mach number and stagnation temperature shape of nozzle. The method of characteristics is used with the algorithm of the second order finite differences method. The form of the nozzle has a point of deflection and an initial angle of expansion. The comparison is made with the calorically perfect gas. The application is for air.     

Z箍缩内爆过程中的能量转换机制研究

利用一维三温辐射磁流体力学程序对氖气和铝丝阵Z箍缩内爆过程中的能量转换过程进行了详细的数值研究，发现在内爆过程中离子和电子之间的碰撞能量交换是最主要的能量交换过程，其次是电子和光子之间的光电过程和轫致过程，而康普顿散射过程中的能量交换可以忽略不计；辐射出的x射线主要是在光电激发和光电复合过程中产生的，其次是在轫致辐射过程和康普顿散射过程中产生的.理论分析表明，辐射出的x射线能量可以超过，也可能小于其等离子体最大动能.数值模拟结果表明，在氖气Z箍缩中，辐射出的x射线能量没有超过其等离子体最大动能，而在铝丝阵列内爆中，辐射出的x射线能量超过了其等离子体最大动能，但小于磁压所做的功；在整个Z箍缩过程中欧姆加热能量是较小的. 关键词： Z箍缩 能量转换 x射线辐射     

Numerical analysis of supersonic gas-dynamic characteristic in laser cutting

The influence of the processing parameters on the dynamic characteristic of supersonic impinging jet in laser cutting is studied numerically. The numerical modeling of a supersonic jet impinging on a plate with a hole is presented to analyze the gas jet–workpiece interaction. The model is able to make quantitative predictions of the effect of the standoff distance and exit Mach number on the mass flow rate and the axial thrust. The numerical results show that the suitable cutting range is slightly different for different exit Mach number, but the optimal cutting parameter for certain exit total pressure is nearly changeless. So the better cut quality and capacity can be obtained mainly by setting the suitable standoff distance for a certain nozzle pressure.     

Influence of the opening angle of a conical supersonic nozzle on the structure of initial interval of non-isobaric jet

The ideal gas exhaustion from an infinite volume into a gas at rest through a supersonic conical Laval nozzle is considered. The problem was solved numerically by steadying in time in a unified formulation for the regions inside the nozzle and in the ambient environment. In such a statement, the nozzle outlet section is no internal boundary of the region under consideration, and there is no need of specifying the boundary conditions here. Local subsonic zones arising in the flow lie inside the region under consideration, which eliminates the possibility of using a marching technique along one of the coordinates. The numerical solution is constructed by a unified algorithm for the entire flow region, which gives a possibility of obtaining a higher accuracy. The computations are carried out in the jet initial interval, where, according to monograph [1], the wave phenomena predominate over the viscous effects. The exhaustion process is described by the system of gas dynamics equations. Their solution is constructed with the aid of a finite difference Harten’s TVD (Total Variation Diminishing) scheme [2], which has the second approximation order in space. The second approximation order in time is achieved with the aid of a five-stage Runge-Kutta method. The solution algorithm has been parallelized in space and implemented on the multi-processor computer systems of the ITAM SB RAS and the MVS-128 of the Siberian Supercomputer Center of SB RAS. The influence of the semi-apex angle of the nozzle supersonic part and the pressure jump between the nozzle outlet section and the ambient environment on the flow in the initial interval of a non-isobaric jet is investigated in the work. A comparison with experimental data is presented. The computations are carried out for the semi-apex angles of the nozzle supersonic part from 0 (parallel flow) to 20 degrees. For all considered nozzles, the Mach number in the nozzle outlet section, which was computed from the one-dimensional theory, equaled three. Computations showed that in the case of flow acceleration in a conical supersonic nozzle, its geometry is one of the main factors determining the formation of the jet initial interval in ambient environment.