双柱双锥形液—流旋流分离管内流场的LDV诊断

本文采用ＴＳＩ二维ＬＤＶ系统,对一种双锥双柱形液－液旋流分离管内流场进行了全场范围的精细ＬＤＶ诊断,先后考试了处理量、压差比、溢流比和气芯等因素对旋流分离管内流场的影响,结果表明：该旋流分离管中下游区的切向速度呈较为明显的Ｒａｎｋｉｎｅ双涡结构,在上游位涡区中发现有未曾报道过的双峰分布现象;轴向速度由近轴处的上行流、近壁处的下行流以及介于两者之间的零速区组成,其中该零速区随旋流分离管截面的收缩而减     

单柱双锥型液—液旋流分离管内流场的IDV诊断

对所开发的一种单柱双锥型液－－液旋流分离管的内流场进行了全场范围内的多工况流动诊断。与典型的Ｆ型旋流管相比,其湍流仍具有各向异性的特性,且其中的湍流脉晚强。     

双柱单锥型液-液旋流管内流场的激光诊断

应用激光测速仪，对一种双柱单锥型液 液旋流管内的流动结构，进行了全场范围内的多工况流动诊断研究．揭示出其切向速度由内旋流区和外旋流区构成，其中内旋流区中的速度分布符合准强制涡关系，外旋流区中的速度分布符合准自由涡关系；轴向速度由上行流动区和下行流动区构成，两者之间在直管段以零速点作分界，在锥体段则以零速区作过渡并伴随有一定的回流出现，且该过渡区或回流区的大小随锥体截面的收缩而减小，直到进入直管段后消失；各湍流量的分布以管芯处最大向外逐渐减小，沿轴向是直管段中的湍流度大于锥体段中的湍流度，而且湍流度在旋流管内具有各向异性的特性．     

液-液旋流分离管中强旋湍流的k-ε数值模拟

采用标准k-ε湍流模型,对一种典型液-液旋流分离管中的强旋湍流进行了数值模拟研究.结果表明:该模型对切向速度的数值预报夸大了Rankine涡中的似固核范围,抹煞了似固核外的位涡区;对轴向速度的数值预报未给出中心回流区;对其它流场参数的预报结果也都存在有明显的不合理之处.由此证明这种基于Boussinesq假设的各向同性湍流模型,虽然在管道流、平面射流和无旋流等简单流动问题中经受住了大量计算实践的检验,但在强旋湍流的数值预报方面的确存在有较大缺陷.此问题的解决有赖于对该模型进行必要的修正或转而采用更加高级的各向异性模型.     

液—液旋流分离管中强旋湍流的K—ε …

采用标准ｋ－ε湍流模型,对一种典型液－液旋流分离管中的强旋湍流进行了数值模拟研究。结果表明：该模型对切向速度的数值预报夸大了Ｒａｎｋｉｎｅ涡中的似固核范围。抹煞了似固核外的位涡区;对轴向速度的数值预报未给出心回流区;对其它流场参数的预报结果也都存在有明显的不合理之处。由此证明这种基于Ｂｏｕｓｓｉｎｅｓｑ假设的各向同性湍流模型,虽然在管道流、平面射流和无旋流等简单流动问题中经受住了大量计算实践的检验     

液固旋流器分离效率的研究

对分离效率与液相流速、油水比例和旋流器级数之间的关系进行了系统的实验研究. 通过受力分析从理论上对细颗粒易受参数影响的原因进行了阐述,并根据量纲分析和实验数据得到了分离效率与$Re$数和$St$数之间的函数关系. 在此基础上,对液固旋流器的现场应用提出了有价值的建议.     

用LDV系统测量转盘萃取塔内流场

本文应用激光多普勒测速仪对二种转盘萃取塔模型进行切向速度、轴向速度和湍流度测量。实验结果表明，在ＲＤＣ是切向速度比较大，因而有较大的搅拌效果，它的内部流场比较均匀稳定，有利于传质，所以ＲＤＣ是广泛应用于化学工业中的一种液－液萃取设备。     

两相流测量的三光束偏振型LDV装置

两相流的测量是许多工业装置中遇到的一个十分重要的课题,本文引入了一种新的测量装置。它采用三光束偏振型光路消除了边缘效应,输出信号由计算机软件处理,采用双阁值法方便、有效地对两相流的速度进行测量。适当改进后,本装置能同时对两相流的粒子尺度及粒子速度进行测量。     

Flow visualization and LDV measurements of laminar flow in a helical square duct with finite pitch

Flow visualization and LDV measurements are performed on laminar flow in a helical square duct with finite pitch. The experimental observations are compared to results of numerical calculations employing the finite-volume method and assuming a fully developed flow. Good agreement is found between measured and computed velocity profiles. This suggests that the physical velocity components used in the numerical calculations are suitable to describe the flow. It is further demonstrated that the contravariant velocity components employed by some authors may lead to results that are difficult to interpret. Two stable solution branches are detected in the numerical calculations. For Reynolds numbers between the stable branches, unsteady and fully developed computations predict an oscillating flow between a two-vortex and a four-vortex structure. In the experiments, the flow normally retained a stable two-vortex structure in the numerically predicted unstable regime. However, by disturbing the flow at the duct inlet, a four-vortex flow that showed similarities to the computed flow could occasionally be obtained. For Reynolds numbers above 600, unsteady flow behavior was observed both experimentally and numerically, which might be an early sign of transition. In the experiments, Gdrtler-like extra vortices emerged spontaneously from the outer wall without disturbing the flow at the inlet. The same phenomenon was observed in the numerical calculations, assuming an unsteady and fully developed flow, but the extra vortices appeared with a lower frequency than in the experiments.     

光束穿越不同介质时LDV的测试及其误差分析

本文应用平面几何及光学原理,从理论和实践上分析了应用激光多普勒测速仪(LDV)进行实际测量时,在有窗口的情况下应该注意的几个问题,并给出了测量点位置偏差修正的定量公式以及光轴方向上测速精度相对误差的评估方程,省略了繁琐的理论推导.     

圆柱、圆锥和圆台的平衡裕度分析

提出了平衡裕度的新概念,并给出了保守力场中物体或系统静力平衡裕度的定义。以此为基础,分析计算了圆柱、圆台和圆锥体的静平衡裕度,并讨论了各几何参数的变化对平衡裕度的影响。文中提出了对静力平衡系统平衡状态差别的定量评价问题,并给出了利用平衡裕度对系统平衡状况进行定量分析的方法。文中提出的研究思路是一种新的系统安全评价方法,对其它系统的研究也有借鉴意义,研究结果对工程安全设计也有启发。     

有环壳过渡段的锥—柱组合壳的应力和稳定性

用解析方法计算了受静水外压载荷作用的有环壳过渡段的锥—柱组合壳中的应力值，并用瑞利法计算了其失稳临界载荷。计算结果说明，利用环壳过渡值锥—柱壳形成光滑连接，可使连接部位的局部应力值显著降低，并使失稳临界载荷有所提高     

Calculation of the Flow Pattern and the Heat Fluxes in the Interaction of a Shock Wave with a Cylinder in a Supersonic Flow

The problem of determining the mechanical and thermal action on a cylinder in a supersonic flow with account for the interference between an incident shock and the detached bow shock has been studied extensively, both experimentally and theoretically, in the last few decades [1–12]. A fairly complete survey can be found in monograph [12]. The interest in the problem is mainly due to the fact that in this case the so-called fourth type of shock interaction can occur, leading to a sharp local increase in the mechanical and thermal loads. As for the problem of the interference flow past a cylinder itself, it can serve as a model problem for testing techniques of calculating the separation flow past the controls of hypersonic flight vehicles.In this paper, we attempt to demonstrate the possibility of using a fairly simple approach to the calculation of the above-mentioned flows, including those with a separation zone. The approach is based on a combination of numerical simulation within the framework of the inviscid gas model and subsequent calculation of the heat transfer parameters and does not require an excessive amount of computing power.     

Evolution of the Flow Field around a Circular Cylinder and a Sphere upon Instantaneous Start with a Supersonic Velocity

Evolution of the flow field around a circular cylinder and a sphere instantaneously starting with a constant supersonic velocity (M = 5 and Re = 10⁵) from the state at rest is studied by means of numerical integration of unsteady twodimensional Navier–Stokes equations.     

应用小干扰柱体控制角区马蹄涡结构的实验研究

本文提出一种简单的抑制和控制角区马蹄涡的被动控制方法.即在角区平板上游放置一个远小于主柱体的小干扰柱体,用其产生的弱马蹄涡来抑制和控制角区的马蹄涡结构.目的是使角区原来的马蹄涡结构由强变为弱、由大变为小、由多变为少、由非定常变为定常,以获得减小冲刷、抑制湍流、降低噪声、避免振动的工程效果.作者在风洞中采用烟线法和激光片光流动显示的方法开展研究,实验表明,在平板上游适当位置放置小干扰柱体的确可以有效抑制和控制角区马蹄涡结构.实验发现,当小干扰柱体放置在原角区马蹄涡生成区时,其抑制和控制效果最佳;当小干扰柱体放置在上游区或下游区时,控制效果不好.本文讨论了小干扰柱体控制角区马蹄涡的机理.此外,实验还研究了小干扰柱体相对尺度和截面形状对角区马蹄涡结构抑制和控制的影响.