收缩段线型对超音速喷管氟原子气相复合的影响

使用移轴维氏曲线和双三次方曲线作为收缩段线型分别设计了两种环形 HYLTE主喷管，给出了环形HYLTE喷管三维的多组分有反应湍流场的控制方程、边界条件和 模拟区域的选择. 计算结果表明，这两种线型的喷管均能避免边界层的分离，获得均匀的流 场分布及相同的出口马赫数分布，但移轴维氏曲线在收缩段前部收缩快速，气流速度相应较 快，因此F原子的气相复合程度弱于另外一种收缩段设计的喷管，相应地，使用移轴维氏曲 线设计的喷管F原子流量比另外一种喷管高5%左右, 因此使用移轴维氏曲线作为环形HYLTE主喷管收缩段的设计有助于提高化学激光器的效率.     

热喷干扰气体模型对飞行器气动特性影响分析

针对不同气体模型对高超声速飞行器喷流反作用控制系统(RCS)热喷干扰流场模拟的计算效率和准确性问题, 基于喷流燃气物理化学模型, 通过数值求解含化学反应源项的三维N-S方程, 建立了飞行器RCS热喷干扰流场数值模拟方法, 分别采用化学反应流、反应冻结流、二元异质流以及空气喷流四种气体模型开展了典型外形热喷干扰流场的数值模拟, 研究了不同气体模型对热喷干扰流场结构、飞行器气动力热特性的影响, 分析了不同马赫数、飞行高度下的变化规律. 研究表明: 化学反应流模型计算精度较高, 计算与风洞试验数据的吻合程度优于其他三种简化模型; 在本文的低空条件下, 采用简化模型进行热喷干扰流场数值模拟, 会低估分离区大小, 使飞行器气动力特性预测出现偏差, 同时也会低估表面热环境, 对防热系统设计不利, 随着马赫数增加, 简化模型对气动力热特性预估的误差进一步增大, 同时不同简化模型之间的差异也进一步增大; 飞行高度较高时, 模型之间的差异减小, 此时可采用简化模型进行计算以提高计算效率. 本文的研究结果可为飞行器热喷干扰流场数值模拟及喷流反作用控制系统设计提供参考.      

A simplified quasi‐two‐dimensional model for gain optimization in carbon dioxide gasdynamic lasers (GDL)

In this paper a simplified quasi‐two‐dimensional model for small signal gain optimization in gasdynamic laser is introduced. In order to obtain a homogeneous medium with maximum optical gain in the active medium, by nozzle shape formation, the shock occurrence position is controlled and is postponed to some point behind the laser active medium. Then the method of calculus of variation is used to find the supersonic part of the nozzle of a gasdynamic laser with maximum gain in the active medium. The interesting result is that the supersonic part of such a nozzle consists of a wedge as the accelerating part of the nozzle, a smooth surface for the uniformization, and finally a channel for the relaxation of the medium. (The middle section is characterized as the geometrical locus of points whose characteristic curves are concurrent at a certain point.) It is also shown that, overlooking a minor difference in the gain, the nozzle can be chosen to be a shock free one with the ultimate optical uniformity. Copyright © 2002 John Wiley & Sons, Ltd.     

爆轰驱动惰性气体磁流体发电试验研究

磁流体发电装置作为一种特殊的高功率脉冲电源,具有效率高、容量大、启动快的优点,制约其发展的关键在于如何获得高电导率的发电工质.爆轰驱动具有远超常规方式的驱动能力,在提供高温、高电导率气体方面独具优势.将爆轰驱动激波管技术应用于磁流体发电,有利于突破磁流体发电技术瓶颈,故据此开展了基于爆轰驱动激波管技术的惰性气体磁流体发电试验研究.爆轰驱动根据激波管点火位置不同分为反向和正向两种运行模式,反向爆轰驱动可提供时间较长、状态稳定的试验气流,而正向爆轰优势在于产生高焓试验气流.试验系统由爆轰驱动激波管、拉瓦尔喷管、发电通道、电磁铁和真空罐等组成,试验中分别以反向爆轰和正向爆轰驱动激波管产生发电工质,利用激波将惰性气体压缩至高温从而发生电离,形成的等离子体经喷管加速后,最终在法拉第直线型发电机内切割磁感线输出电能.磁场强度0.9 T的条件下,反向爆轰在负载3.5Ω时获得了较稳定的1.9 kW输出功率,持续时间1.5 ms;外接35 mΩ负载时,正向爆轰在0.3 ms内短时输出功率高达212 k W,功率密度为0.2 GW/m³.试验成功验证了基于爆轰驱动激波管技术的惰性气体...     

Detonation combustion of hydrogen in a Laval nozzle under rarefied atmosphere conditions

Detonation combustion of a hydrogen-air mixture entering an axisymmetric convergent-divergent nozzle at a supersonic velocity is considered under atmospheric conditions at altitudes up to 24 km. The investigation is carried out on the basis of the two-dimensional gasdynamic Euler equations for a multicomponent reacting gas. The limiting altitude ensuring detonation combustion in a Laval nozzle of given geometry is numerically established for freestream Mach numbers 6 and 7. The possibility of the laser initiation of detonation in a supersonic flow of a stoichiometric, preliminarily heated hydrogen-air mixture is experimentally studied. The investigation is carried out in a shock tube under conditions simulating a supersonic flow in the nozzle throat region.     

Analysis of high speed non‐equilibrium chemically reacting gas flows. Part I. Physical modeling and sensitivity studies

In this part, a theoretical model for high speed flow of chemically reacting gases out of thermal and chemical equilibrium is presented. The main features of the physical model are discussed together with details for a new form of the kinetic rate coefficients for non‐equilibrium flows and presentation of a two‐layer radiation model used for a plasma torch problem. This model is implemented in a new hybrid finite volume/finite element scheme, which is developed in Part II. Results from this physical model are compared with experiments and other results in the literature for an arcjet and non‐equilibrium nozzle test case. Sensitivity studies are included for the nozzle problem to simulate the influence of the rate coefficients. Copyright © 2000 John Wiley & Sons, Ltd.     

环形喷管喷口气泡演化的实验研究

水下气泡的发展演化及气泡动力学行为是气液两相动力学的基础理论与水下射流应用的重要基础. 环形喷管/喷口形成的气泡及气体射流具有其不同于圆孔实心射流的特殊表现与规律机制,随着同心筒破水发射等特殊应用的出现,环形喷口气体射流/泡流的基础现象观测和机制分析成为迫切的需求. 基于环形喷管的设计和水下射流条件的分析,设计建立了一套环形喷管水箱实验系统,对水下环形喷管喷口气泡发展演化过程进行了初步的实验研究. 为观测研究气体通过环形喷管气泡生长发展过程,在较低压力、较低流速下,采用高速摄影仪记录气泡生长及发展演化过程. 结合对气泡发展演化过程的图像处理与分析,研究分析了环形喷口气泡形成区制、气泡生长过程形态发展特点、以及气泡形成时间及气泡体积变化特点. 研究表明:在本实验气体流量范围内(50.8~237.3 dm3/min),环形喷口气泡发展演化过程呈现较为明显的三周期区制,前泡尾流影响是环形气泡呈三周期区制的主要原因;不同周期内的气泡形成时间具有较稳定规律,并受到流量影响;气泡生长过程中有较为明显的下沉、回升特征;气泡表面张力、液体惯性与流动的共同作用,造成了典型的气泡顶部坍塌现象.      

一种求解化学非平衡流动的新型解耦算法

在一种新型化学非平衡流解耦算法框架下,将WENO5M 格式用于化学非平衡流动的流场计算. 为了验证所发展算法的准确性,对多个典型算例进行了计算. 首先计算了Oran 的反射激波诱导爆轰实验,并考虑了不同化学反应机理和网格收敛性的影响,得到的计算结果与实验和其他文献给出的计算结果符合很好,并且由于采用了一种最近提出的氢氧燃烧机理,模拟得到的实验中各个事件发生的相对时间相比于与以前的计算结果与实验符合得更好. 然后计算了二维H₂/O₂/Ar 爆轰,计算得到的胞格结构与实验和其他模拟结果符合较好,并得到了详细的爆轰发展历程. 由于这种新型解耦算法的特点,仅需对现有的基于量热完全气体的可压缩流动计算程序做很小的修改,即能改造成化学反应流动计算程序,从而进一步体现了这种解耦算法的优势.      

Profiling the Supersonic Part of a Plug Nozzle with a Nonuniform Transonic Flow

The effect of transonic flow nonuniformity on the profiling of optimal plug nozzles is studied in the inviscid gas approximation. Sonic and supersonic regions providing maximum thrust for given nozzle dimensions and a given outer pressure are designed for given subsonic contours and calculated nonuniform transonic flows. As in the case of uniform flow on a cylindrical sonic surface, the initial regions of the designed contours satisfy the condition that in these regions the flow Mach number is unity or near-unity. In all the examples calculated, the optimal plug nozzles produce a greater thrust than the optimal axisymmetric and annular nozzles with a near-axial flow for the same lengths and the same gas flow rates through the nozzle. It is established that contouring without regard for transonic flow nonuniformity can result in considerable thrust losses. However, these losses are due only to a decrease in the flow rate, while the specific thrust may even increase slightly.     

Numerical modeling of detonation combustion of hydrogen-air mixtures in a convergent-divergent nozzle

The flow of igniting hydrogen-air mixtures entering an axisymmetric convergent-divergent nozzle at a supersonic velocity is considered. A possibility of stabilizing detonation combustion is numerically investigated at different freestream Mach numbers with account for nonuniform distribution of hydrogen concentration at the nozzle entry. The investigation is performed on the basis of the two-dimensional gasdynamic Euler equations for a multicomponent reacting gas. A detailed model of chemical reactions is used. The calculated thrust is compared with the drag of a conical housing containing the supersonic nozzle considered.