冲击高度对半封闭紊流冲击射流流场影响的实验研究

采用热线风速仪给出了在半封闭、雷诺数为23000时四种不同的冲击高度下紊流冲击射流流场的详细的测量结果,并与文献结果作了比较。表明壁面的“阻尼”影响主要集中在近壁面0.5D以内,在径向上流动既有顺压梯度,又有逆压梯度。小板间距时径向速度曲线下降得比大板间距时明显要快,且曲线的峰值也稍大;在r/D≤1.0的区间内,板间距为2和4时紊动能的数值大小和分布趋势与板间距为6和8时的不同,在其它位置紊动能的分布趋势基本一致,只是大板间距下的值较大;流动结构在z4和z6之间发生了较大的变化,这种变化与势流核心区有关,在势流核心区的顶端以及下游的一段距离内紊流度都很高。     

钢轨轨缝接触-冲击的有限元分析

基于弹性点支承梁模型，采用三维非线性动力分析有限元程序ANSYS／LS-DYNA3D，建立了轮轨轨缝处接触一冲击有限元分析模型，通过模拟车轮经过轨缝时冲击钢轨接头的过程，研究了冲击过程中轨头的应力分布情况．结果表明：车轮冲击钢轨接头时，轮轨间最大垂向接触力出现在冲击开始后0．5ms左右，约为静载时的2．6倍，且在一定时间段里，轮轨间出现瞬时脱离现象．同时，轮轨间接触力及各种最大应力均随着轴重的增加成正比增大；当车轮冲击轨端瞬时，最大Von Mises等效应力出现在轨端头部，约为静接触时的3倍；最大剪应力发生在离轨顶面5mm处．研究结果对于揭示轨头的冲击破坏机理和改善铁路轨缝连接方式具有指导作用．     

压敏漆测压在低速射流撞击壁面的应用研究

压敏漆(pressure sensitive paint,PSP)测压是一种基于发光分子氧猝灭效应的测压技术,与传统测压方式相比具有成本小、空间分辨率高等特点.实验搭建了压敏漆测压硬件平台,开发了数据处理软件系统.利用驻点处的压强与灰度关系拟合了标定曲线,研究了低速射流撞击平板表面的压强分布特性,分析了喷管距离壁面高度和雷诺数的影响.结果表明,当喷管高度h/d<6时,压强分布曲线的峰值压强和半宽度随喷管高度变化基本不变;当喷管高度h/d>6时,随着高度的增大,峰值压强线性减小,半宽度线性增加.采用峰值压强和半宽度对不同喷管高度的压强分布曲线进行无量纲化,压强分布曲线呈现自相似特性.进一步研究表明,在实验雷诺数范围内,压强分布受雷诺数影响较小.      

近距离下射流冲击平板PIV实验研究

运用时间分辨粒子成像测速系统(time-resolved particle image velocimetry, TR-PIV)对近距离下射流冲击平板时的流场进行了直接测量, 通过对两个正交的平面流场开展测量, 揭示了冲击距离和雷诺数对射流间隙内三维流动特征及涡系结构演化规律的影响. 结果表明: 射流间隙存在三种典型的涡系结构, 分别为双涡环模式、单涡环模式和卷吸模式, 但在大流量湍流状态下, 射流可能会冲破涡环, 形成随机的高速出流, 各流动模式的出现主要与射流流态及壁面约束作用有关. 运用涡量分析对三种典型涡系结构的能量传递和损失特性进行了比较. 结果表明: 近距离冲击时, 射流的能量通过涡环模式向外传递. 在双涡环模式下, 两个涡环的旋向相反, 端面的约束作用使得两个涡环都被严格约束在射流棒端面之内, 且一次涡环强度显著大于二次涡环强度. 最后, 运用本征正交分解方法对射流间隙内的流动模态及其能量分布进行了分析. 单涡和双涡模式前十阶模态分析结果表明: 能量脉动在较低阶时即以配对的模式出现, 这表明一次涡环与二次涡环均具有良好的对称性, 同时在双涡模式中, 一次涡环是占主导作用的大尺度流动结构. 卷吸模式的前三阶模态分析表明: 射流的能量集中在射流上游, 能量随紊动扩散急剧衰减.      

近壁声空泡溃灭微射流冲击流固耦合模型及蚀坑反演分析

超声场下液体环境中近壁空泡溃灭会产生强烈的微射流,为探究微射流冲击壁面流固耦合效应,利用流体力学及冲击动力学,考虑了率相关的J-C材料本构模型,建立并分析了微射流冲击壁面流固耦合三维模型,并通过超声空化试验和基于球形压痕试验理论的反演分析进行了验证。结果表明:微射流冲击下材料表面出现微型凹坑,凹坑深度由微射流速度和微射流直径共同决定且随其增大而增大,凹坑直径主要与微射流直径正相关,而凹坑径深比则主要与微射流速度负相关;壁面压强基本呈对称分布且最大压强出现在微射流冲击边缘;超声空化试验验证了微射流冲击下材料表面出现的微型凹坑,反演分析方法表明,在16~18的径深比下,微射流冲击强度为420~500MPa,对应的微射流速度为310~370m/s。试验及反演分析结果与理论分析结果相符,验证了流固耦合模型及反演分析方法的合理性及准确性,为后续工程应用中空化强度、微射流速度等的控制提供了理论参考。     

液腔体中气体射流冲击压力的实验测量

对充液腔体中气体射流的冲击效应进行了实验研究. 测量结果表明了冲击压力的瞬态最 大值、稳态平均值和脉动值随喷管进口压比的增加而增加，冲击区是主要的噪声源和动态压 力承载部位. 通过充气与充水两种状态的对比实验，还揭示了腔体充水时气体射流冲击压力 出现一个上冲阶段，其瞬态最大值比充气值有显著的增加.     

复合材料板受低速冲击时能量吸收的实验研究

利用落锤装置，对玻纤／环氧和碳纤／环氧两种复合材料层合板进行了低速低能量的冲击实验研究。利用传感器技术记录了落锤冲击板过程中速度随时间变化曲线，计算了冲击动能和材料损伤时的能量吸收。通过数学处理得到了冲击载荷和冲击点位移随时间变化曲线。还对多次冲击的能量吸收问题进行了实验研究。     

半封闭狭缝湍流冲击射流的数值模拟

将Yakhot和Orszag提出的RNGk-ε模型推广应用于半封闭狭缝冲击射流场的数值模拟，以评价该模型对这种复杂湍流的预测能力。将计算得到的流场平均速度分布、湍流强度分布和流函数分布与标准k—ε模型的预测结果以及相应的实验数据进行了比较，结果表明：RNGk—ε模型的预测结果总体上要好于标准k—ε模型，但与实验值相比，所有预测结果都还存在不同程度的误差，尤其是近壁区和滞止点较远下游处的湍流强度分布。说明RNG模型虽然已在某些湍流的预测中取得了一定的成功，但要定量准确地预测冲击射流场，还必须针对其流动特征对模型加以改进。     

褐煤爆炸冲击气流传播特性与CO生成特性数值模拟

为研究褐煤爆炸过程中冲击气流传播特性及CO毒气生成特性,以水平管道煤尘爆炸实验装置为依托,按1∶1比例建立水平管道几何模型,在构建煤尘爆炸动力传播特性数学模型的基础上,展开冲击气流传播特性与CO生成特性模拟分析。结果表明:通过对比不同时刻褐煤爆炸火焰传播距离模拟值与实测值,验证了模拟方法的可靠性。以冲击气流传播速度模拟值划分空间区域,得到:z=0～0.1 m为初始扬尘区,z=0.1～0.42 m为冲击气流速度跃升区,z=0.42～0.98 m为冲击气流高速传播区,z=0.98～1.4 m为冲击气流缓冲区。z=0.2 m与z=0.4 m截面上距圆心越远,冲击气流传播速度越大,这是由流体流动的“壁面效应”导致的,壁面附近空隙率大于流体内部,流动时所受阻力比较小,因此出现冲击气流在近壁处流速较大的分布特征。模拟CO毒气产物生成特性发现,管内z=0.3～0.6 m为CO质量分数相对最高的空间范围,局部最高达到0.024%～0.026%。在z＞0.7 m时,由于颗粒受重力作用,同时爆炸产生的高温气体受浮力作用,导致CO气体产物出现下沉的趋势。     

冲击射流的研究概述

冲击射流是一种既有工程应用背景,又有理论研究价值的独特的流动现象．经过长期的研究和探索,人们对这种具有很强换热效果的流动的认识不断加深,研究方法也日趋精细,从简单的实验装置发展到先进的测量系统,从单纯的实验研究发展到实验与理论计算相结合,并且不断地将其应用于新的工业流动问题,所考虑的影响因素也日益增多．但是对这种流动现象还需作更进一步的研究,特别是在冲击射流的冲击区壁面附近,实验结果和理论计算还有一定的差距．本文对冲击射流的研究现状进行了综述．     

Computations for a jet impinging obliquely on a flat surface

A SIMPLE-C algorithm and Jones-Launder k-ε two-equation turbulence model are used to simulate a two-dimensional jet impinging obliquely on a flat surface. Both the continuity and momentum equations for the unsteady state are cast into suitable finite difference equations. The pressure, velocity, turbulent kinetic energy and turbulent energy dissipation rate distributions are solved and show good agreement with various experimental data. The calculations show that the flow field structure of the jet impinging obliquely on a flat surface is strongly affected by the oblique impingement angle. The maximum pressure zone of the obliquely impinging jet flow field moves towards the left as the oblique impingement angle is decreased.     

NUMERICAL PREDICTION OF SEMI-CONFINED JET IMPINGEMENT AND COMPARISON WITH EXPERIMENTAL DATA

The standard k–ε eddy viscosity model of turbulence in conjunction with the logarithmic law of the wall has been applied to the prediction of a fully developed turbulent axisymmetric jet impinging within a semi-confined space. A single geometry with a Reynolds number of 20,000 and a nozzle-to-plate spacing of two diameters has been considered with inlet boundary conditions based on measured profiles of velocity and turbulence. Velocity, turbulence and heat transfer data have been obtained using laser–Doppler anemometry and liquid crystal thermography respectively. In the developing wall jet, numerical results of heat transfer compare to within 20% of experiment where isotropy prevails and the trends in turbulent kinetic energy are predicted. However, stagnation point heat transfer is overpredicted by about 300%, which is attributed directly to the turbulence model and inapplicability of the wall function.     

An Experimental Investigation of the Turbulence Structure of a Lifted H2/N2 Jet Flame in a Vitiated Co-Flow

Measurements of mean velocity components, turbulent intensity, and Reynolds shear stress are presented in a turbulent lifted H₂/N₂ jet flame as well as non-reacting air jet issuing into a vitiated co-flow by laser doppler velocimetry (LDV) technique. The objectives of this paper are to obtain a velocity data base missing in the previous experiment data of the Dibble burner and so provide initial and flow field data for evaluating the validity of various numerical codes describing the turbulent partially premixed flames on this burner. It is found that the potential core is shortened due to the high ratio of jet density to co-flow density in the non-reacting cases. However, the existence of flame suppressed turbulence in the upstream region of the jet dominates the length of potential core in the reacting cases. At the centreline, the normalized axial velocities in the reacting cases are higher than the non-reacting cases, and the relative turbulent intensities of the reacting flow are smaller than in the non-reacting flow, where a self-preserving behaviour for the relative turbulent intensities exists at the downstream region. The profiles of mean axial velocity in the lifted flame distribute between the non-reacting jet and non-premixed flame both in the axial and radial distributions. The radial distributions of turbulent kinetic energy in the lifted flames exhibit a change in distributions indicating the difference of stabilisation mechanisms of the two lifted flame. The experimental results presented will guide the development of an improved modelling for such flames.     

Proper orthogonal decomposition analysis of coherent motions in a turbulent annular jet

A three-dimensional incompressible annular jet is simulated by the large eddy simulation(LES) method at a Reynolds number Re = 8 500. The time-averaged velocity field shows an asymmetric wake behind the central bluff-body although the flow geometry is symmetric. The proper orthogonal decomposition(POD) analysis of the velocity fluctuation vectors is conducted to study the flow dynamics of the wake flow.The distribution of turbulent kinetic energy across the three-dimensional POD modes shows that the first four eigenmodes each capture more than 1% of the turbulent kinetic energy, and hence their impact on the wake dynamics is studied. The results demonstrate that the asymmetric mean flow in the near-field of the annular jet is related to the first two POD modes which correspond to a radial shift of the stagnation point. The modes 3 and 4 involve the stretching or squeezing effects of the recirculation region in the radial direction. In addition, the spatial structure of these four POD eigenmodes also shows the counter-rotating vortices in the streamwise direction downstream of the flow reversal region.     

Numerical and experimental study of turbulent impinging twin-jet flow

The two dimensional impinging circular twin-jet flow with no-cross flow is studied numerically and experimentally. The theoretical predications are carried out through numerical procedure based on finite volume method to solve the governing mass, momentum, turbulent kinetic energy and turbulent kinetic energy dissipation rate. The parameters studied were jet Reynolds number (9.5 × 10⁴  Re  22.4 × 10⁴), nozzle to plate spacing (3  h/d  12), nozzle to nozzle centerline spacing (l/d = 3, 5 and 8) and jet angle (0°  θ  20°). It is concluded that the stagnation primary point moves away in the radial main flow direction by increasing the jet angle. This shift becomes stronger by increasing the nozzle to nozzle centerline spacing (l/d). A secondary stagnation point is set up between two jets. The value of pressure at this point decreases by decreasing Reynolds number and/or increasing the jet angle.

The sub atmospheric region occurs on the impingement plate. It increases strongly by increasing Reynolds number and decreases as the jet angle and/or a nozzle to plate spacing increases. The spreading of jet decreases by increasing nozzle to plate spacing. The intensity of re-circulation zone between two jets decreases by increasing of h/d and jet angle. The increase of turbulence kinetic energy occurs within high gradient velocity.     

Flow field characterization of coaxial conical and serrated (chevron) nozzles

PIV measurements were performed to provide insight into the effect of serrated (chevron) nozzles on the flow field of a coaxial circular jet. The serrations were tested on the primary nozzle. Mean flow results showed that the chevron effectively redistributes momentum from the high velocity center stream outward to the lower velocity secondary stream by creating lateral jets. This leads to a more rapid decay of the peak jet velocity and a consequent reduction in the length of the jet potential core. Local increases of up to 65% in the outer stream velocity were measured. The interaction of the secondary jets with the lower velocity outer stream produces increases in turbulent kinetic energy (TKE) near the center nozzle lip. These flow field effects correlate with the jet’s acoustic emissions: Reduction of low-frequency noise due to large scale mixing and potential core shortening, and increased high-frequency noise due to increased near-field turbulence.     

An experimental investigation on flow structures of confined and unconfined impinging air jets

The flow characteristics of both confined and unconfined air jets, impinging normally onto a flat plate have been experimentally investigated. The mean and turbulence velocities, and surface pressures were measured for Reynolds numbers ranging from 30,000 to 50,000 and the nozzle-to-plate spacings in range of 0.2–6. Smoke-wire technique is used to visualize the flow behavior. The effects of Reynolds number, nozzle-to-plate spacing and flow confinement on the flow structure are reported. In the case of confined jet, subatmospheric regions occur on both impingement and confinement surfaces at nozzle-to-plate spacings up to 2 for all Reynolds numbers in consideration and they lie up to nearly the same radial location at both surfaces. However, there is no evidence of the subatmospheric region in unconfined jet. It is concluded that there exists a linkage among the subatmospheric region, turbulence intensity and the peaks in heat transfer coefficients for low spacings in impinging jets.     

激励小尺度模式在湍流圆管射流中的应用

采用非涡黏性的激励小尺度（Stimulated Small Scale)模式对空间发展的轴对称湍流圆管射流进行了大涡模拟。以雷诺数为10000的流动为例,考证了激励小尺度模式在自由剪切流模拟中的可行性,描述了湍流强度、雷诺应力和湍流耗散量的变化,同时与标准的Smagorinsky涡黏性模式的计算结果进行了比较。数值结果显示,激励小尺度模式能够更为合理地描述湍流的耗散特性和能量传输特性,从而较为准确地展示出空间发展射流中由于流动不稳定而出现的旋涡产生、发展、破碎及合并等过程。     

Experimental study of an impinging jet with different swirl rates

A stereo PIV technique using advanced pre- and post-processing algorithms is implemented for the experimental study of the local structure of turbulent swirling impinging jets. The main emphasis of the present work is the analysis of the influence of swirl rate on the flow structure. During measurements, the Reynolds number was 8900, the nozzle-to-plate distance was equal to three nozzle diameters and the swirl rate was varied from 0 to 1.0. For the studied flows, spatial distributions of the mean velocity and statistical moments (including triple moments) of turbulent pulsations were measured.

The influence of the PIV finite spatial resolution on the measured dissipation rate and velocity moments was analyzed and compared with theoretical predictions. For this purpose, a special series of 2D PIV measurements was carried out with vector spacing up to several Kolmogorov lengthscales.

All terms of the axial mean momentum and the turbulent kinetic energy budget equations were obtained for the cross-section located one nozzle diameter from the impinging plate. For the TKE budget, the dissipation term was directly calculated from the instantaneous velocity fields, thereby allowing the pressure diffusion term to be found as a residual one. It was found that the magnitude of pressure diffusion decreased with the growth of the swirl rate. In general, the studied swirling impinging jets had a greater spread rate and a more rapid decay in absolute velocity when compared to the non-swirling jet.     

等离子体激励器诱导射流的湍流特性研究

为了进一步掌握等离子体流动控制机理, 完善等离子体激励器数学模型, 提升等离子体激励器扰动能力, 采用粒子图像测速技术, 在静止空气下开展了介质阻挡放电等离子体激励器诱导射流特性研究. 实验时, 将非对称布局激励器布置在平板模型上, 随后将带有激励器的模型放置在有机玻璃箱内, 从而避免环境气流对测试结果的影响. 基于激励器诱导流场, 分析了激励电压对诱导射流特性的影响, 揭示了较高电压下诱导射流近壁区的拟序结构, 获得了卷起涡、二次涡等拟序结构的演化发展过程, 计算了卷起涡脱落频率, 阐述了卷起涡与启动涡的区别, 初步探索了卷起涡的耗散机制. 结果表明: (1)层流射流不能完全概括等离子体诱导射流特性, 激励电压是影响射流特性的重要参数. 当电压较低时, 诱导射流为层流射流; 当电压较高时, 诱导射流的雷诺数提高, 射流剪切层不稳定, 层流射流逐渐发展为湍流射流. (2)等离子体诱导湍流射流包含着卷起涡、二次涡等拟序结构; 在固定电压下, 这些涡结构存在恒定的卷起频率. (3)当激励电压较高时, 流动不稳定使得卷起涡发生了拉伸、变形, 引起了流场湍动能增大, 从而加速了卷起涡的耗散. 研究结果为全面认识激励器射流特性, 进一步挖掘激励器卷吸掺混能力, 提升激励器控制能力积累基础.