Evaluation of FFT-based cross-correlation algorithms for PIV in a periodic grooved channel

The design of a pneumatic droplet generator to produce small (~0.2 mm diameter) water droplets on demand is described. It consists of a cylindrical, liquid-filled chamber with a small nozzle set into its bottom surface, connected to a gas cylinder through a solenoid valve. Rapidly opening and closing the valve sends a pressure pulse to the liquid, ejecting a single droplet through the nozzle. Gas in the chamber escapes through a vent hole so that the pressure drops rapidly and more droplets do not emerge. We photographed droplets as they emerged from the nozzle, and recorded pressure fluctuations in the chamber. We determined the duration of the pressure pulse required to generate a single drop; longer pulses produced satellite drops. The length of the water jet when its tip detached and the diameter of the droplet that formed could be predicted using results from linear stability analysis. The peak pressure in the cavity could be increased by raising the supply pressure, increasing the width of the pressure pulse, or by reducing the size of the pressure relief vent.     

A pneumatic droplet-on-demand generator

The design of a pneumatic droplet generator to produce small (~0.2 mm diameter) water droplets on demand is described. It consists of a cylindrical, liquid-filled chamber with a small nozzle set into its bottom surface, connected to a gas cylinder through a solenoid valve. Rapidly opening and closing the valve sends a pressure pulse to the liquid, ejecting a single droplet through the nozzle. Gas in the chamber escapes through a vent hole so that the pressure drops rapidly and more droplets do not emerge. We photographed droplets as they emerged from the nozzle, and recorded pressure fluctuations in the chamber. We determined the duration of the pressure pulse required to generate a single drop; longer pulses produced satellite drops. The length of the water jet when its tip detached and the diameter of the droplet that formed could be predicted using results from linear stability analysis. The peak pressure in the cavity could be increased by raising the supply pressure, increasing the width of the pressure pulse, or by reducing the size of the pressure relief vent.     

复合射孔压力加载下铜柱测压计测试实验和数值分析

进行基于铜柱测压和实测压力时间曲线的石油井射孔压裂实验,建立铜柱测压计的数学模型,并采用交互式计算方法得出其作用过程的解析解。分析结果表明,井下射孔压裂过程中,压力上升沿很陡,活塞在外部压力达到峰值时,速度很大,会继续压缩铜柱直到速度为零。活塞的运动可以分为加速和减速撞击2个过程。活塞的最大速度决定了铜柱测压计最终测试值,且与速度成正比。射孔脉冲压力加载过程中铜柱测压计的误差取决于压力上升时间、脉冲宽度、峰值压力等影响因素。火炮膛压加载下铜柱测压计误差较小。     

基于单射流冲击试验的复合材料高速雨滴撞击损伤研究

飞行器高速飞越云雨区时,前表面会受到雨滴的冲击侵蚀。基于一级轻气炮搭建了一种单射流冲击试验平台用于材料雨蚀试验,可产生速度200～600 m/s、直径4～7 mm、头部呈光滑圆弧形的稳定水射流;并对一种碳纤维树脂基复合材料层合板进行了不同速度和直径的单射流冲击试验。结果表明,复合材料单次水射流冲击的典型损伤形貌为:冲击表面凹陷,中心几乎完好无损伤,周围产生一环状损伤带,环内有树脂去除、基体开裂、少量纤维断裂等损伤形式;内部损伤主要由基体开裂和层间分层组成。损伤尺寸呈现典型的各向异性,纵向尺寸大于横向尺寸;随射流速度和直径的增加,表面环状损伤和内部损伤的尺寸均向外扩展,环状损伤面积和内部分层面积也随之增加。水锤压力的压缩和卸载、侧向射流的剪切和应力波的相互作用是造成复合材料单射流冲击损伤的主要机理。     

高速斜入水和水平入水气炮水箱实验系统

为开展模型高速斜入水和水中高速航行的水流场实验研究,研制了立式和卧式气炮与水箱组合的实验系统。通过快速阀和活塞阀控制气炮激发和驱动状态,一级气炮采用高压空气直接驱动弹托和模型,二级气炮采用高压空气驱动重活塞压缩使集气腔中产生高压气体,再驱动弹托和模型达到预定速度。通过调节水箱和发射管角度,使高速模型斜入水或水平入水。其中,立式可变发射角二级气炮可发射质量1～1000 g的模型至2500 m/s最大速度,卧式一级气炮可发射质量1～100 kg的模型至300 m/s最大速度。和小气室、高燃气压力火药驱动方式相比,新型气炮采用大体积、中低驱动压力气室,高压气体更接近等熵膨胀做功,调节高压气体压力,能较好地满足模型质量和速度的宽范围要求。结合光反射通断法测速、高速摄影和阴影流场显示等测量技术,得到立式气炮压缩管重活塞运动速度、压缩管末端压力时间曲线和模型倾斜与水平入水的流场阴影图像。结果表明:重活塞速度在膜片破裂前和理论计算值符合较好,但破膜后差异较大。立式气炮流场阴影图像反映了模型斜入水产生的空中和水中激波以及在气水界面的反射激波、空泡形成和侧向气水界面的破碎与飞溅等现象。从卧式气炮的模型水平入水阴影图像提取气泡轮廓,清楚地看出尾部气泡气水界面的波动和失稳。和商业计算软件Fluent计算结果相比,空泡上游区域基本重合,但尾流区域强湍流导致两者存在明显差异。和水洞实验相比,气炮水箱实验系统近真实地再现高速入水过程伴随的冲击和动态空化等物理现象和模型尺度效应。     

Parametric investigation of particle acceleration in high enthalpy conical nozzle flows for coating applications

A modified cold gas-dynamic spray technique is under development by using shock tunnel technology, which can enhance the coating quality by increasing the solid particle velocity up to 1,500 m/s. The particle diameter typically amounts to 10 μm. A theoretical model based on gas-particle flows is employed to describe the behaviour of the flow and the solid particles. This quasi-1D model is capable to consider non-equilibrium effects of the gas phase due to high reservoir temperatures, and the influence of wall friction and heat transfer averaged over the nozzle cross section. This model is used for the design and optimization of the nozzle geometry by a parametric study, which results in a conical nozzle with a half opening angle of 2.8° and a length of 325 mm. Particles for coating are injected at about 55 mm downstream of the throat. A shock tunnel facility has been set up at the Shock Wave Laboratory for performing an experimental study of this new technique. The theoretical performance of this setup is evaluated by the KASIMIR simulation software and the quasi-1D method described in this paper. The high reservoir conditions required to achieve particle velocities of 1,500 m/s can be realized by using either a very high driver pressure of about 600 bar for air as driver gas or a relatively low driver pressure of about 200 bar for helium as driver gas.      

驱动气体的密度梯度对弹丸发射速度的影响

为进一步提升轻气炮的发射能力,提出采用梯度气体替代单一氢气或氦气作为驱动气体的方法,通过对等直径发射器进行分析,建立了弹丸在梯度气体驱动下的加速运动模型,对比了氖-氦梯度气体驱动与单一氦气驱动的发射能力差异,分析了梯度气体参数对发射性能的影响。结果表明,与单一氦气驱动相比,氖-氦梯度气体驱动能够提升0.4～1.4 km/s的发射速度或降低0.2～0.9 GPa的发射过载;气体的密度和活塞的运动速度对发射速度和过载的影响最大,气体压力和多方气体指数的影响次之;梯度气体中,高密度气体应选择多方气体指数和密度较高的气体（如氖气、氩气等）;梯度气体界面位置（高密度气体占比）对发射速度的影响不大,但高密度气体占比少有利于降低弹底压力。     

Visualization of a confined accelerated bubble

High-speed photography was used to study the collapse of a confined two-dimensional, air cavity in water, subjected to a propagating pressure disturbance. The 5–6 mm diameter cavity was confined in a rectangular duct. A sustained pressure disturbance was created by an accelerating piston in contact with the water 240 mm away from the bubble. The pressure increased from 0.1 MPa to about 0.12 MPa with a rise time of the order of 2 ms. The pressure pulse was not reflected until its arrival at the end of the duct, 320 mm from the piston. A microjet was produced at the proximal wall which penetrated the distal cavity wall, thereby producing a pair of bubbles which was thought to be regions of intense vorticity. The features of such confined bubble collapse were not found in previous investigations of unconfined bubble accelerations by weak pressure disturbances. Confinement apparently intensified the effect of the disturbance significantly. Received 18 August 1998 / Accepted 12 May 1999     

淹没条件下不同结构参数的自激吸气式脉冲射流喷嘴压力变化试验研究

运用自行研制的试验装置对淹没条件下的自激吸气式脉冲射流喷嘴特性进行了大量的试验,研究了吸气对喷嘴内的压力变化和脉冲射流峰值打击力的影响。通过研究淹没条件下10-16-125-75和8-14-85-60结构参数喷嘴在不同吸气根数下的腔套内各测点压力及峰值打击力的变化,得出不同结构喷嘴的压力和峰值打击力随吸气量的增大而逐渐提高,存在最优吸气量使脉冲射流峰值打击力最大。通过研究淹没条件下结构参数分别为8-14-85-60、10-16-105-75、14-28-125-105的喷嘴在不吸气及吸气根数为4情况下的射流峰谷差及峰值打击力,得出三种喷嘴在吸气时的射流峰值打击力分别提高45%~78%、40%~46%、22%~38%。研究表明:对于不同结构参数喷嘴,吸气可提高射流压力波动值和峰值打击力,随上喷嘴直径和振荡腔内容积的增大,该吸气方式对射流打击力的提高程度呈减小趋势。结果对进一步研究淹没条件下自激吸气式脉冲射流喷嘴特性具有指导意义。     

深海采矿中试系统水力提升管道水击压力分析

深海采矿系统可能由于突然停泵、断电或机械故障等引起提升管道中流体速度瞬间变化, 导致管道内压力剧烈变化, 这种水击现象对管道破坏极大. 基于固液两相流体连续性原理和动量定理, 推导出含粗颗粒的固液两相流体管道水击压力的计算公式. 采用深海采矿中试系统参数, 模拟计算不同水体流速、不同流体浓度以及不同管径条件下的水击压力. 分析结果表明, 流速、体积浓度和管径是影响水击压力的重要因素, 其中, 流速影响最大. 研究结果可为深海采矿系统工程设计提供依据.     

Supersonic liquid jets: Their generation and shock wave characteristics

The generation of high-speed liquid (water and diesel fuel) jets in the supersonic range using a vertical single-stage powder gun is described. The effect of projectile velocity and mass on the jet velocity is investigated experimentally. Jet exit velocities for a set of nozzle inner profiles (e.g. straight cone with different cone angles, exponential, hyperbolic etc.) are compared. The optimum condition to achieve the maximum jet velocity and hence better atomization and mixing is then determined. The visual images of supersonic diesel fuel jets (velocity about 2000 m/s) were obtained by the shadowgraph method. This provides better understanding of each stage of the generation of the jets and makes the study of their characteristics and the potential for auto-ignition possible. In the experiments, a pressure relief section has been used to minimize the compressed air wave ahead of the projectile. To clarify the processes inside the section, additional experiments have been performed with the use of the shadowgraph method, showing the projectile travelling inside and leaving the pressure relief section at a velocity of about 1100 m/s. Received 23 January 2001 / Accepted 2 July 2001     

Experimental research on the rotating detonation in gaseous fuels�Coxygen mixtures

An experimental study on rotating detonation is presented in this paper. The study was focused on the possibility of using rotating detonation in a rocket engine. The research was divided into two parts: the first part was devoted to obtaining the initiation of rotating detonation in fuel–oxygen mixture; the second was aimed at determination of the range of propagation stability as a function of chamber pressure, composition, and geometry. Additionally, thrust and specific impulse were determined in the latter stage. In the paper, only rich mixture is described, because using such a composition in rocket combustion chambers maximizes the specific impulse and thrust. In the experiments, two kinds of geometry were examined: cylindrical and cylindrical-conic, the latter can be simulated by a simple aerospike nozzle. Methane, ethane, and propane were used as fuel. The pressure–time courses in the manifolds and in the chamber are presented. The thrust–time profile and detonation velocity calculated from measured pressure peaks are shown. To confirm the performance of a rocket engine with rotating detonation as a high energy gas generator, a model of a simple engine was designed, built, and tested. In the tests, the model of the engine was connected to the dump tank. This solution enables different environmental conditions from a range of flight from 16 km altitude to sea level to be simulated. The obtained specific impulse for pressure in the chamber of max. 1.2 bar and a small nozzle expansion ratio of about 3.5 was close to 1,500 m/s.     

环空流道液流失速水击特性及其成因的研究

环空流道与圆管的结构差异,使得其失速水击特性及其成因亦有不同。为了对其进行分析研究,利用PIV对套管环空和圆管流水击流场进行拍摄,并通过Tecplot显示流场,提取轴向速度和径向速度、等速度线等参数加以分析;同时采用高精度智能动态压力传感器采集了套管环空内、外壁及内管内壁压力,对环空中水击特性进行了进一步研究。结论是:水击发生时环空断面外壁面水击压力大于内壁面水击压力;同初速情况下环空液流水击压力大于圆管流水击压力;环空中水击压力衰减速度快于圆管中;涡流是水击压力衰减以及速度变化的主要因素;水击压力振荡变化主要是压力涡流引起的断面能量的相互转化形成的。     

圆管流动水击压力波测量及水力计算

为探索水击现象的物理过程和机理,研制了自循环定常流动管路瞬态特性计算机控制试验装置,并利用该装置进行圆管流动水击压力波实验测量。用12只扩散硅压力传感器测定圆管流动水击压力波瞬态分布及最大、最小压力值,由试验数据拟合出水击波波形,揭示了水击压力波传播方式、特性及衰减规律。通过分析随机捕捉测量技术方法,理论上推断出测量数据达到可信精度。在归纳分析试验数据基础上,得出最大压力随关阀时间的关系曲线,对圆管流动直接水击等概念进行了探讨,用数值分析方法拟合出水击最大压力水力计算修正方程式。     

The local measurement of the size and velocity of bubbles rising in liquids

An experimental study of the rise of small air bubbles (0.1 to 1.0 mm in diameter) in a quiescent pool is described. Local measurements of rise velocity were obtained as a function of height above the source nozzle using a laser-Doppler method. In addition, the bubble diameter was determined simultaneously from the same optical signals. Data are presented for various bubble diameters and spacings in bubble columns for both distilled water and a dilute polymer solution.It was found that for distilled water the rise velocity near the nozzle reaches the maximum observed in other studies before decelerating to its terminal velocity due to surfactant accumulation at its interface. The maximum rise velocity in dilute polymer was much lower for the same bubble diameter and reached its terminal velocity much faster. The results are shown to be in closer agreement with predictions for a solid sphere in this case.     

A ballistic compressor-based experiment for the visualization of liquid propellant jet combustion above 100 MPa

 This paper describes the components and operation of an experimental setup for the visualization of liquid propellant (LP) jet combustion at pressures above 100 MPa. The apparatus consists of an in-line ballistic compressor and LP injector. The ballistic compressor, based on a modified 76 mm gun, provides high-pressure (ca. 55 MPa) clear hot gas for the jet ignition. A piston (projectile) is fired toward a test chamber beyond the barrel’s end, and its rebound is arrested in a transition section that seals the test chamber to the barrel. The LP jet is injected once the piston is restrained, and combustion of the jet further elevates the pressure. At a preset pressure, a disc in the piston ruptures and the combustion gas vents sonically into the barrel. If a monopropellant is used, the jet injection-combustion process then resembles liquid rocket combustion but at very high pressures (ca. 140 MPa). This paper discusses the ballistics of the compression and compares experimental results to those predicted by a numerical model of the apparatus. Experimentally, a pressure of 70 MPa was achieved upon a 12.5 volumetric compression factor by firing a 10 kg piston into 1.04 MPa argon using a charge of 75 g of small-grain M1 propellant. Received: 16 December 1996/Accepted: 15 July 1997     

Experimental simulation of heat transfer in an HF-plasmatron with lengthened segmented discharge channel

Subsonic and supersonic air induction plasma flows in a VGU-4 100 kW plasmatron with segmented water-cooled cylindrical nozzle with the outlet cross-section 40 mm in diameter are investigated experimentally. The enthalpy on the axis of flow is measured in subsonic air jets. The heat fluxes are measured at the stagnation flow point on a cylindrical water-cooled model 50 mm in diameter located in subsonic air and nitrogen jets. The effect of the generator power, nozzle length, and pressure in the plasmatron pressure chamber on the distributions of the heat flux and the pressure at the stagnation point on the surface of cylindrical models 20 mm in diameter with a plane and hemispheric nose is investigated along the axis of underexpanded dissociated air jets.     

Zr基非晶合金破片冲击破碎反应机制研究

为研究Zr基非晶合金破片的冲击破碎反应机制,进行了准密封箱冲击超压实验,测试了破片的碎片粒度,分析了碎片尺寸分布关系,并对不同粒径尺度的碎片进行了X射线衍射分析。实验结果表明,材料在冲击加载下的反应程度随着撞击速度的升高而增大;碎片分布符合分段式幂次律分布规律;材料冲击诱发的化学反应主要为Zr元素与空气中氧气的燃烧,其主要反应产物为ZrO₂。基于冲击升温-碎片分布-碎片燃烧的冲击破碎反应理论模型能较好地解释冲击作用下Zr基非晶合金破片的反应规律,理论计算与实验结果吻合度较高。     

The trajectories of large fire fighting jets

This article describes a computer simulation of the trajectories of large water jets which allow the effects of changes in initial velocity, elevation, nozzle diameter, and head and tail winds to be examined. The rather limited information on aerodynamic drag of large jets obtained by other workers is used. The predicted trajectories compare well with the limited data available in the literature.The results also show that for a given flow rate an optimum pressure, and hence an optimum nozzle diameter, exists for maximum throw distance which has important implications for the design of the whole system including the pumps. The optimum elevation in still air lies in the range 30–40°. Wind effects are shown to be very important.     

Finite element for the dynamic analysis of pipes subjected to water hammer

An axisymmetric finite element is developed for the dynamic analysis of pipes subjected to water hammer. The analysis seamlessly captures the pipe response due to water hammer by solving first the water hammer mass and momentum conservation equations, to recover the spatial–temporal distribution of the internal pressure, and then uses the predicted pressure history to form a time-dependent energy equivalent load vector within a finite element model. The study then determines the pipe response by solving the finite element discretized equations of motion. The formulation of the pipe response is based on Hamilton’s principle in conjunction with a thin shell theory formulation, and captures inertial and damping effects. The results predicted by the model are shown to be in agreement with those based on an axisymmetric shell model in Abaqus for static, free vibration and transient responses for benchmark problems. The water hammer and structural models are seamlessly integrated to enable advancing the transient solution well into the time domain to capture the effect of reflected pressure wave due to water hammer. The results indicate that the radial stress/displacement oscillations approach those of the quasi-steady response when the valve closure time exceeds eight times the period of radial vibrations obtained for the case of instantaneous valve closure.