超声速进气道起动与不起动的流动特征结构的机理分析

基于Wagner等实验的超声速进气道模型,采用RANS-SST计算方法分析超声速进气道起动和不起动流场特性。通过拓宽计算域和采用来流边界层自由发展方法,准确预测了典型的进气道不起动过程中可能出现的周期性振荡流现象,包括进气道内部高压的产生和降低、下壁面大尺度分离泡的膨胀收缩和迁移,并伴随不起动激波的传播。进气道完全起动状态(末端活门挡板角度β=0°)时得到的波系结构、壁面压强和流向速度分布计算结果与实验测量值相吻合;不起动状态(β=28°)时流场的振荡周期和振幅与实验结果一致。对进气道不起动的非定常流场进行动态模态分解,发现了3个特征频率：主频f₁=69.8 Hz的流场模态揭示了进气道出口的压强振荡最强,而入口及上壁面的速度振荡最强;二倍频f₂=139.7 Hz和三倍频f₃=209.5 Hz捕捉到的流场模态主要是离散的小尺度高能结构。在不起动状态的振荡过程中,进气道入口外部流场产生了较大的速度和压力脉动,所以对进气道内外流场相互作用的准确描述是预测不起动状态振荡流动的重要因素。     

平面倾斜冲击射流场的数值分析

采用SIMPLE算法和RNGk-ε湍流模型,对平面射流倾斜冲击平板的半封闭空间内的流场进行了数值分析。针对喷口宽度B=10mm、冲击高度H=2B和射流雷诺数Re=20000的流场,分别得到了三种射流倾角下的速度、流函数、压力和湍动能分布。计算结果表明,射流倾角的变化对流场结构具有显著的影响。当倾角减小时,左侧回流区变小,而右侧回流区变大,最大压力区和最大湍动能区都随着滞止点的左移向流场的左侧移动。     

大雷诺数下方柱绕流PIV试验及数值模拟

基于风洞试验利用粒子图像测速技术(PIV)研究了大雷诺数(Re=3.42×10~4)下方柱绕流流场,并应用本征正交分解(POD)法分解PIV瞬态速度场,获得了方柱尾流的低阶模态和重构流场结果,研究方柱绕流的流动机理.采用γ-Re_θ和k-ωSST两种湍流模型研究了大雷诺数下方柱尾流的速度分布以及湍动能变化。风洞PIV试验可准确的观测方柱尾流脉动流场,基于POD方法得到的前6阶模态占总能量的78.7%,前6阶模态即可较准确重构流场并捕获流场的主要特征。通过对比,γ-Re_θ模型是较优的湍流模型,可较好地得到尾流的湍动能及其变化规律。     

旋流泵内部盐析两相流速度场的PDPA实验

以旋流式模型泵内部氯化钠盐析两相流场为研究对象,采用相位多普勒粒子测速仪(PDPA)对该泵在最优工况下的两相速度场进行了测量,给出各相在无叶腔及叶轮内部的三维速度及其对应的脉动速度分布曲线.通过对两相的周向速度、轴向速度及径向速度分布情况的分析,揭示了该型泵内盐析两相流速度场的分布特征.泵内同时存在循环流与贯通流,是强制涡旋和自由涡旋的叠加,与前人提出的流动模型相符;在叶轮进口处,液流已有强力预旋;随着半径增大,两相的周向和轴向速度呈现先增大后减小趋势,而径向速度先减小后增大,对应的脉动速度变化趋势则相反;泵内两相速度及脉动速度有滑移,但差异总体上并不显著.本文的研究有助于进一步认识盐析与流动的关系.     

矩形通道内层流对流换热的最优速度场

针对矩形通道内的层流对流换热问题,通过数值求解速度场协同方程,得到了给定黏性耗散条件下通道内的最优速度场为多纵向涡的流动结构,表明多纵向涡流型可在流阻增加不多的情况下使换热显著强化.通过在通道壁面布置不连续双斜肋,在通道内产生了接近于最优速度场的多纵向涡流动,数值计算结果表明,在Re=1000时,与光滑通道相比,不连续...     

二维空腔黏性流的格子Boltzmann方法模拟

用13速六方格子BhatnagarGrossKrook(缩写为BGK)模型模拟二维空腔黏性流.给出了上边界流体作匀速运动时,具有不同雷诺数的空腔黏性流的流场速度分布情况,模拟了在雷诺数Re=3000时,流场中的涡旋形成过程及流场稳定后,腔内密度、压力和温度的分布情况 关键词：     

串列双圆柱时均流场特性分析

对Re=12000,间距比L/D=1.167,2.333,3.500和4.667的串列双圆柱后方速度场进行了实验测量,分析串列双圆柱后方不同剖面处的速度分布规律和湍流度分布规律.并通过流函数理论模型对小间距比串列双圆柱后方流场进行了分析,得出如下结论:与单圆柱相比,当串列双圆柱间距比较小时,后方圆柱的自由剪切层明显向内...     

近壁方柱绕流非定常特性的TR-PIV测量

本文采用时变粒子图像速度场测试技术(TR-PIV),研究了低速循环水槽中近壁(G/D=0.1)二维方柱绕流的非定常流动特性.通过对实验得到的20000个连续瞬态速度场进行分析,得到了时均速度矢量场,速度大小分布和流向速度脉动强度分布.根据回流间歇系数的分布确定了时均再附点的位置.通过对原始速度场进行互相关分析,得到了流场中低频大尺度相干结构输运速度Uc=0.4U0.     

柔性旋涡发生器对翼型前缘分离的自适应控制

采用边长为10 mm的三角形柔性和刚性旋涡发生器,安装在二维NACA0018翼型上翼面前缘不同弦长处,用于控制翼型前缘分离流动.实验在低速直流式风洞中进行,以翼型弦长为特征长度的Reynolds数Re=1.1×105,采用单丝热线风速仪测量尾流速度剖面.分别研究柔性和刚性两种材料的三角形旋涡发生器对翼型前缘分离的控制效果.实验结果表明,与刚性旋涡发生器相比,柔性旋涡发生器利用来流能量实现自适应控制,使剪切层下移,从而明显抑制前缘分离.      

超声速气膜气动光学效应与Reynolds数相互关系实验研究

目前,随着相关项目研究的不断推进,如何在高Reynolds数下研究其对气动光学效应的影响成为重要命题.通过设计变Reynolds数气动光学效应实验平台,模拟的单位Reynolds数可以在7.2×106~2.2×108 m-1范围内变化.搭建的基于背景纹影（background oriented schlieren,BOS）的波前测试系统可以达到6 ns的时间分辨率.此系统测量的平凸透镜波前结果表明:实验测量结果与理论计算结果的误差在±4%以内.通过测量9种不同Reynolds数下的超声速气膜瞬态波前数据,分析结果表明:在高Reynolds数条件下,Reynolds数对于超声速气膜气动光学效应的影响比较明显,通过对实验数据进行函数拟合发现OPD_rms∝Re0.88,与推导结果OPD_rms∝Re0.9十分接近;利用小波分析方法研究了高Reynolds数条件下气动光学效应沿流向的分布特征,发现OPD_rms的低频部分（信号的主体）先降低后升高,但是高频部分的震荡幅度先升后降.分析认为OPD_rms的低频部分主要受到流场整体结构的影响,而高频部分更多地受到涡的空间分布影响.      

基于FLUENT的动态高压微射流内部孔道流场的数值模拟

 以动态高压微射流振荡反应腔内部孔道流场为研究对象,建立了反应腔内部孔道的几何模型和网格模型,选择SIMPLEC算法和RNG k-ε模型,运用FLUENT软件对流场进行数值模拟,以揭示流场内各位置上的静压和速度分布。计算结果表明：高速射流撞击增加了流场内的撞击作用力,流速的急剧增加使速度梯度迅速加大,剪切应力极大增强,保证了微射流均质机极佳的作用效果;由于反应腔内部孔道流场的静压与速度变化相反,静压的急剧变化使空穴效应及压力释放效应极大增强,空穴作用力得以强化,对微射流均质机反应腔内的材料产生“腐蚀”作用。设计反应腔内部孔道时,在保证撞击区速度的前提下,应适当减小进料速度和分流管进口拐角角度,并选用较短的出料管。     

Aerothermodynamic Analysis of a Reentry Brazilian Satellite

This work deals with a computational investigation on the small ballistic reentry Brazilian vehicle SAtélite de Reentrada Atmosférica (SARA). Hypersonic flows over the vehicle SARA at zero-degree angle of attack in chemical equilibrium and thermal nonequilibrium are modeled by the direct simulation Monte Carlo method, which has become the main technique for studying complex multidimensional rarefied flows, and which properly accounts for the nonequilibrium aspects of the flows. The emphasis of this paper is to examine the behavior of the primary properties during the high-altitude portion of SARA reentry. In this way, velocity, density, pressure, and temperature field are investigated for altitudes of 100, 95, 90, 85, and 80?km. In addition, comparisons based on geometry are made between axisymmetric and planar two-dimensional configurations. Some significant differences between these configurations were noted on the flowfield structure in the reentry trajectory. The analysis showed that the flow disturbances have different influence on velocity, density, pressure, and temperature along the stagnation streamline ahead of the capsule nose. It was found that the stagnation region is a thermally stressed zone. It was also found that the stagnation region is a zone of strong compression, high wall pressure. Wall pressure distributions are compared with those of available experimental data, and good agreement is found along the spherical nose for the altitude range investigated.     

Detection of separation in S-duct diffusers using shear sensitive liquid crystals

In the present experimental investigation, shear sensitive liquid crystals have been successfully used to study the flow characteristics and detect separation in two-dimensional Sduct diffusers of different curvatures. Tapered-fin vortex generators in two different orientations were used to control flow separation that was observed on one of the curved walls of the diffuser. The results were verified by conventional oil flow visualization technique and excellent agreement was observed. In addition to visualization, detailed measurements that included wall static pressure, skin friction, diffuser exit total pressure and velocity distributions were taken in a uniform inlet flow with Reynolds number of 3.49 × 10⁵. These results are presented here in terms of skin friction distribution, distortion and total pressure loss coefficients. The extent of the separation zone (in terms of intensity of red distribution) in the diffuser with and without vortex generators (in both configurations) compared well with the Preston tube measurements. The present study demonstrates that shear sensitive liquid crystals can be efficiently used to study the flow physics in complex internal flows. In addition, the results also indicate that shear sensitive liquid crystals can be effectively used not only as flow visualization tool but also to gain quantitative information about the flow field in internal flows.     

变角度百叶窗翅片的数值模拟和性能分析

为研究变角度百叶窗结构对平行流蒸发器换热性能的影响,文中建立了一种均匀角度百叶窗和两种变角度百叶窗的计算模型;采用fluent软件数值模拟了空气侧的传热和流动过程,得到了百叶窗翅片的速度场、温度场及压力场;将数值模拟结果与相关文献实验关联式结果进行对比,验证了数值模拟的可行性,分析了迎面风速对换热和压降特性的影响;并利用公式j/f1/3,比较了三种翅片的综合性能,发现变角度百叶窗翅片综合性能优于均匀角度百叶窗翅片。     

On formation of a stagnation zone in the flow between conical flame and flat obstacle

The structure of a jet flow formed by the combustion products of conical propane-air flame and impinging onto a normally oriented flat cooled surface is studied experimentally. The velocity field is measured by the particle image velocimetry technique. Based on the non-intrusive measurements, formation of a recirculation zone in the flow between the flame cone and surface has been detected for the first time. Mechanism for the observed phenomenon is proposed. Presence of the low-intensity recirculation bubble on the jet axis can explain the effect of a heat transfer decrease near the stagnation point on the surface, observed in the previous studies.     

水力旋流器参数对高炉污泥分离的影响

本文采用简化的多流体多相流模型及雷诺应力湍流模型建立了水力旋流器内液固多相湍流流动的数学模型,对水力旋流器在不同结构参数和进口压力下的高炉污泥分离进行了数值模拟,获得了水力旋流器内高炉污泥不同情况下的颗粒分级效率曲线。数值结果表明,在高炉污泥颗粒分离的应用范围内,锥角增大,旋流器直径增大,分离粒径会增加, 进口压力增加,分离粒径降低。     

低速气流三参数动态测量软件初探

本文采用虚拟仪器概念和技术,构建了三孔探针动态测量系统。该系统集成了高速数据采集、储存及现代数据处理模块,通过该系统可动态显示低马赫数下压气机内部流场的总压、静压、速度矢量等物理参数的变化趋势,并可对动态信号进行时域显示和频域分析。系统还具备自动标定、零漂消除及线性度拟合的功能,实现了流场动态测试技术在线处理与测试同步进行的目的。     

Structure conditioned velocity statistics in a high pressure swirl flame

A piloted, partially premixed, liquid-fueled swirl burner is operated at high pressure (1 MPa). High-speed (6 KHz) stereoscopic PIV is used to investigate the characteristics of the stagnation line separating the pilot jet and the central recirculation zone (CRZ) with varying pilot-main ratio and global equivalence ratio. The mean curvature of the stagnation line displayed a large spatial scale pattern that was present for all operating conditions. All three components of velocity, in-plane shear, and swirling strength are conditioned upon the instantaneous stagnation line. Mean distributions of the velocity normal to the stagnation line show that velocity is oriented towards the CRZ when the stagnation line is found nearer the centerline of the combustor. The conditioned out-of-plane velocity (w) shows a distinct concentration of large mean and fluctuation RMS values towards the center of the measurement domain. Varying fuel flow does not significantly change this spatial structure, only the magnitudes of the w statistics. The in-plane shear stress was the largest for the pilot biased condition as a stronger shear layer develops. For the leanest flame, large fluctuation RMS values of shear stress were confined to a region where the pilot jet begins to interact more heavily with the main jet. Operating with less pilot fuel flow enhanced the mean conditional swirling strength indicating that the pilot shear layer was shedding more intense eddies. Disregarding spatial relations, a scatter plot of w, shear stress, and swirling strength displayed trends between the variables. The largest swirling strength values coincide with highest magnitude shear stresses and the widest range of w. These conditioned statistics highlight how certain aspects of the combustor flow field are invariant with fuel distribution. This is desirable for aeropropulsive combustors that must maintain stable ignition from a range of conditions from landing/take-off to cruise.     

全浸水带间隙发射高速射弹的入水冲击载荷分析

全浸水带间隙发射方式可以将发射环境由水介质转化为气体介质。为了研究高速射弹在此条件下的入水冲击载荷,建立了射弹入水冲击载荷的理论模型。针对射弹在入水速度、头部锥角和入水攻角不同情况下的入水冲击载荷进行了计算,分析了入水速度、射弹头部参数和入水攻角对冲击载荷的影响。研究结果对全水下高速射弹入水冲击载荷的预测和射弹头部结构的设计具有重要意义。     

Optimizing the source distribution in fluid mixing

A passive scalar is advected by a velocity field, with a nonuniform spatial source that maintains concentration inhomogeneities. For example, the scalar could be temperature with a source consisting of hot and cold spots, such that the mean temperature is constant. Which source distributions are best mixed by this velocity field? This question has a straightforward yet rich answer that is relevant to real mixing problems. We use a multiscale measure of steady-state enhancement to mixing and optimize it by a variational approach. We then solve the resulting Euler-Lagrange equation for a perturbed uniform flow and for simple cellular flows. The optimal source distributions have many broad features that are as expected: they avoid stagnation points, favour regions of fast flow, and their contours are aligned such that the flow blows hot spots onto cold and vice versa. However, the detailed structure varies widely with diffusivity and other problem parameters. Though these are model problems, the optimization procedure is simple enough to be adapted to more complex situations.