高压燃气射流在整装液体中扩展过程的实验和数值模拟

为研究高压燃气射流在整装液体中的扩展规律,探索提高射流稳定性的控制方法,设计了4级渐扩型圆柱观察室.采用高速录像系统,观察了燃气射流在液体模拟工质中扩展与掺混的过程,获得了射流扩展形态的序列照片,测量了Taylor空腔的扩展速度,对比了观察室内壁形状对射流扩展过程的影响.建立了二维轴对称气液两相湍流模型,模拟射流扩展过...     

含能气体射流与液体相互作用的实验研究

为了研究整装式液体发射药的燃烧稳定性的控制方法,设计了点火喷射模拟装置及4种多级渐扩型观察室,利用数字高速摄像系统,观察含能气体射流在液体模拟工质中的扩展过程,并对实验中出现的喷孔壅塞现象进行了分析.结果表明:射流在渐扩型结构中扩展稳定,喷射压力、喷孔直径和渐扩结构对射流扩展形态和气液掺混过程有显著影响,通过合理调整这些参数,可以实现对射流扩展过程的有效控制;喷孔壅塞时射流扩展形态非对称,影响气液掺混,不利于控制射流的稳定性.     

圆柱形充液室中4股贴壁燃气射流扩展特性的实验研究

为了探索高温高压周向均布4股贴壁燃气射流在受限空间中的扩展特性,设计了贴壁燃气射流在圆柱形充液室内扩展的实验装置,借助数字高速录像系统,观察了4股贴壁燃气射流在充液室中的扩展过程,发现由Kelvin-Helmholtz不稳定性引起的表面不规则一直存在于整个射流扩展过程;通过处理拍摄记录的射流扩展序列图,获得不同时刻射流扩展的轴向和径向位移; 对比了不同破膜喷射压力和喷孔结构参数对4股贴壁燃气射流扩展过程的影响。实验结果表明:喷孔面积越大,贴壁射流初期轴向扩展速度越大,但由于径向扩展达到交汇的时间较早,湍流掺混和干涉强烈,衰减也越快;破膜喷射压力越高,射流径向扩展到达交汇的时间越短; 破膜喷射压力从12 MPa升高到20 MPa,射流轴向扩展速度大幅增加,气液湍流掺混效应增强。     

等离子射流与渐扩边界中液体工质相互作用特性的模拟实验

为了探索整装式液体工质电热化学炮中药室边界形状对燃烧控制的影响,采用数字高速录像系统对等离子体射流在液体工质中的扩展过程进行了测试,研究了不同放电电压、不同喷嘴直径、不同渐扩边界结构下等离子射流与液体工质的相互作用特性.获得了等离子射流在液体工质中扩展形态的时间序列图,处理出不同工况下Taylor空腔扩展的轴向位移与时...     

燃烧轻气炮多级渐扩型燃烧室流场特性数值研究

为了分析多级渐扩型燃烧室结构对燃烧轻气炮氢氧燃烧特性的影响, 通过计算流体力学方法, 分别对采用传统圆柱型燃烧室和多级渐扩型燃烧室的燃烧轻气炮氢氧燃烧发射过程进行数值模拟。对比结果表明, 多级渐扩型燃烧室结构能够明显地减小燃烧室压力波动幅度, 提高氢氧燃烧稳定性; 多级渐扩型燃烧室内形成回流区, 可以减小气流轴向运动速度; 火焰扩展形态与渐扩型结构相吻合, 燃烧反应区表面变化平稳; 多级渐扩型燃烧室结构对氢氧火焰传播过程和压力波动现象有着重要影响。     

固体火箭燃气射流驱动液柱过程的CFD分析

固体火箭燃气射流驱动液柱过程会产生一个复杂的非稳态多相流场,为了研究液柱对固体火箭发动机工作过程中射流流场的降温效果,并揭示燃气冲击液柱的流动演化和气水之间的相互作用,利用FLUENT软件中耦合了液态水汽化方程的VOF多相流计算模型对燃气与液柱之间的耦合流动及相变过程进行了数值模拟,并与无液柱情况下射流流场的计算结果进行了对比分析。计算结果表明,当有液柱平衡体时射流流场中的压力、温度、速度波动幅度均减小,减弱了射流流场中的湍流脉动强度;液柱与燃气之间的汽化以及液柱的阻碍作用减小了射流流场的轴向发展位移,尾管后的完全发展射流流场核心区域内的压力峰值降低了0.9 MPa,温度峰值降低了503 K,速度峰值降低了291 m/s,验证了实验中液柱对燃气射流流场的降温效果。     

燃气射流冲击传热特性的数值模拟

针对射流传热问题,利用基于RNGk-ε湍流模型的数值方法模拟了射流垂直冲击平板的流动过程,并与实验数据比较,验证了模型的可行性。在此基础上,以火箭喷管入口参数为入口条件,建立了超音速燃气射流垂直冲击平板和冲击浸没平板的计算模型,分析了不同冲击条件下努塞尔数分布规律和温度分布规律, 论述了超音速射流传热的特性及影响传热特性的因素。得到了冲击距离为(14~18)D的努塞尔数取值范围,并表明冲击距离和射流温度是影响传热效率的关键因素;冲击距离增加,传热效率降低,冲击平板表面的射流温度越高,传热效率越高。     

轻型火箭发射噪声场的分布特性

为了解小火箭发射噪声特性及其在喷口外围的声压场分布规律,针对燃气射流产生噪声问题进行了实验研究和数值计算。讨论了超声速射流噪声的3个主要成分(湍流混合噪声、啸音和宽带激波相关噪声)及相关特点,指出它们产生的根本原因是湍流射流的速度扰动。通过分析不同实验测点的射流噪声声压级峰值,得到了燃气射流噪声在轴向和径向上的分布规律,即随着离喷口距离的增大,轴向噪声的衰减程度大于径向。在实验基础上,利用大涡模拟与FW-H(Ffowcs Williams-Hawkings)声学比拟相结合的方法对燃气射流噪声的声学特性进行计算。结果表明,此方法获得的计算结果与实验结果吻合较好,可为进一步研究射流噪声控制提供参考。     

含裂纹损伤充液圆柱壳的振动响应求解方法

薄壁圆柱壳流体冲击振动响应是一个复杂的流固耦合(FSI)动力学问题，对于薄壳状态监测与缺陷识别具有重要意义。基于Flügge壳体应力理论，得到壳体运动的高阶偏微分方程组(PDE)，利用波传播方法获得圆柱壳系统振动响应。将壳体周围流体定义为理想声学介质，通过亥姆霍兹方程描述声压场，得到流固耦合条件下的薄壁圆柱壳受迫振动响应演变规律。针对薄壳裂纹损伤识别问题，基于断裂力学理论建立局部柔度矩阵，结合呼吸型线弹簧模型(LSM)，构造裂纹附近应力及位移连续条件，获得含裂纹损伤充液圆柱壳的振动响应，进而给出一种基于振动能量流的裂纹损伤识别方法。研究结果表明：充液圆柱壳耦合系统在非线性激励下，位移响应在沿轴向、周向和径向的传播特性差异明显；裂纹的存在会导致结构局部柔度的降低和耦合系统固有频率下降；归一化输入功率流能够有效地对充液圆柱壳耦合系统进行结构裂纹损伤识别。研究结果可为充液薄壳振动响应方面的研究提供有益参考，也可为流固耦合条件下的结构裂纹损伤识别方面提供技术支持。     

充液金属圆柱壳受弹体冲击的整体变形与局部破坏分析

在地基梁类比方法基础上,建立了一组充液金属圆柱壳受平头弹体侧向正冲击的理论分析模型,该模型可以确定冲击过程圆柱壳的整体变形及弹性的穿透破坏,利用该模型计算了弹道极限速度,弹体及圆柱壳的冲击响应历程,特别地,分析了内压对弹道极限速度等参数的影响,得到了内压与弹道极限速度的关系帮一些有意义的结论,理论结果与已有实验结果基本吻合。     

Study on Expansion Characteristic of Twin Combustion Gas Jets in Five-Stage Cylindrical Stepped-wall Observation Chamber

The five-stage cylindrical stepped-wall observation chamber is designed to investigate the method of controlling the interior ballistic stability in bulk-loaded propellant guns. The expansion and mixing process of twin combustion gas jets in liquid is studied by means of high speed photographic system. The influence of multiple parameters on jet expansion shape is discussed. Based on the experiment, the three-dimensional mathematics model is established to simulate the expansion process of twin gas jets in liquid. The pressure, density, temperature, velocity contours and evolutionary process of vortices are obtained. Results show that vortices behind the corner of the steps are formed due to the inducing effect of steps. The jets can expand along the axial and radial direction simultaneously, weakening the Kelvin-Helmholtz instability. The numerical simulation results of axial expansion displacement are in good agreement with the experimental data.     

Study on the influences of interaction behaviors between multiple combustion-gas jets on expansion characteristics of Taylor cavities

The purpose of this study is to investigate means of controlling the interior ballistic stability of a bulk-loaded propellant gun(BLPG).Experiments on the interaction of twin combustion gas jets and liquid medium in a cylindrical stepped-wall combustion chamber are conducted in detail to obtain time series processes of jet expansion,and a numerical simulation under the same working conditions is also conducted to verify the reliability of the numerical method by comparing numerical results and experimental results.From this,numerical simulations on mutual interference and expansion characteristics of multiple combustion gas jets(four,six,and eight jets) in liquid medium are carried out,and the distribution characteristic of pressure,velocity,temperature,and evolutionary processes of Taylor cavities and streamlines of jet flow Held are obtained in detail.The results of numerical simulations show that when different numbers of combustion gas jets expand in liquid medium,there are two different types of vortices in the jet flow field,including corner vortices of liquid phase near the step and backflow vortices of gas phase within Taylor cavities.Because of these two types of vortices,the radial expansion characteristic of the jets is increased,while changing numbers of combustion gas jets can restrain Kelvin-Helmholtz instability to a certain degree in jet expansion processes,which can at last realize the goal of controlling the interior ballistic stability of a BLPG.The optimum method for both suppressing Kelvin-Helmholtz instability and promoting radial expansion of Taylor cavities can be determined by analyzing the change of characteristic parameters in a jet flow field.     

Study on three-dimensional expansion characteristics of four wall combustion-gas jets in confined liquid space

To explore further the launch mechanism of the new underwater launching technology proposed in this paper, the expansion characteristics of four wall combustion-gas jets in confined liquid space must be studied firstly. The experimental device is designed, and the high-speed digi-tal photographic system is adopted to obtain the expansion sequence processes of Taylor cavities formed by the four wall jets. Meanwhile, the influence of the injection pres-sure on the axial expansion property of the four wall jets is discussed. Based on the experiments, a three-dimensional unsteady mathematical model is established to simulate the turbulent flow process of the four wall jets expanding in liquid, and the temporal and spatial distribution laws of phase, pressure, temperature, and velocity and the evolution rules of vortices are illustrated in detail. Results show that, accompanied by the jets expanding downstream, the four wall combustion-gas jets get close to each other and achieve convergence eventually under induction of the interference effect between multiple jets. Meanwhile, the heads of the Taylor cavities separate from the observation chamber wall and offset to the central axis of the observation chamber with time going on. The numerical simulation results of the four wall combustion-gas jets coincide well with the experimental data.     

On the experimental investigation on primary atomization of liquid streams

The production of a liquid spray can be summarized as the succession of the following three steps; the liquid flow ejection, the primary breakup mechanism and the secondary breakup mechanism. The intermediate step—the primary breakup mechanism—covers the early liquid flow deformation down to the production of the first isolated liquid fragments. This step is very important and requires to be fully understood since it constitutes the link between the flow issuing from the atomizer and the final spray. This paper reviews the experimental investigations dedicated to this early atomization step. Several situations are considered: cylindrical liquid jets, flat liquid sheets, air-assisted cylindrical liquid jets and air-assisted flat liquid sheets. Each fluid stream adopts several atomization regimes according to the operating conditions. These regimes as well as the significant parameters they depend on are listed. The main instability mechanisms, which control primary breakup processes, are rather well described. This review points out the internal geometrical nozzle characteristics and internal flow details that influence the atomization mechanisms. The contributions of these characteristics, which require further investigations to be fully identified and quantified, are believed to be the main reason of experimental discrepancies and explain a lack of universal primary breakup regime categorizations.     

Interaction Between an Oscillating Sphere and a Thin Elastic Cylindrical Shell Filled with a Compressible Liquid. Internal Axisymmetric Problem

The problem on the interaction between a spherical body that oscillates in a prescribed manner and a thin elastic cylindrical shell filled with an ideal compressible liquid is formulated. It is assumed that the geometrical center of the sphere is located on the cylinder axis. The problem is solved based on the possibility of representing a partial solution of the Helmholtz equation written in cylindrical coordinates in terms of partial solutions in spherical coordinates, and vice versa. By satisfying the boundary conditions on the surfaces of the sphere and the shell, we obtain an infinite system of linear algebraic equations to determine the coefficients of expansion of the liquid-velocity potential into a Fourier series in terms of Legendre polynomials. The hydrodynamic characteristics of the liquid filling the cylindrical shell are determined and compared with the cases where a sphere oscillates in an infinite liquid and in a rigid cylindrical vessel     

内爆加载下金属柱壳的冻结回收方法

针对内爆炸载荷下膨胀态金属柱壳的回收问题，设计了冻结回收试验方法，实现了起爆后不同时刻金属柱壳的冻结回收。基于一体式壳体提出了3种改进结构，并分别对4种柱壳结构在内爆载荷下的膨胀断裂过程进行数值模拟。结果表明，两段式结构最有利于减小非起爆端对预期回收中间段壳体的影响。根据选定的最优壳体结构和金属柱壳在起爆后不同时刻的膨胀外形特征，设计与之匹配的冻结回收装置并进行冻结回收试验。试验结果表明，设计的冻结回收试验方法可以实现膨胀态金属柱壳的回收，回收壳体的轴向和径向尺寸与设计理想值符合较好，整体误差可控制在10%以内。     

充满液体弹塑性圆柱壳轴向冲击屈曲的数值模拟

基于对充满液体的弹塑性圆柱壳轴向冲击屈曲的实验观察 ,建立了相应的计算模型 ,借用 LS-DYNA软件包 ,在 HP-C36 0工作站上完成了数值模拟 ,得到了动画显示 ,给出的屈曲模态及一些特征量的时程曲线与实验结果相当一致。文中对壳的几何、物理参数对屈曲性能的影响进行了较详细的讨论