基于FHT-CC的流场图像自适应运动矢量估计方法

针对河流水面图像中表现为非刚体目标的天然水面模式，提出了一种自适应的运动矢量估计方法。方法采用快速哈特利变换互相关作为相关测度，相比快速傅里叶互相关，具有更高的计算效率和更低的硬件开销。采用三点高斯曲线拟合出相关峰值的亚像素坐标，使位移估计精度提高到了0．2pixel。基于采样定理推导了示踪物满足跟随性以及分布条件时的最佳窗口尺度区间为2～3倍的待测位移；发现相关曲面的信噪比对于运动矢量估计具有明显的指示作用，正确矢量通常在最佳窗口尺度区间内出现信噪比的局部峰值；因此采用由粗到精的策略迭代搜索最接近于3倍位移的信噪比峰值，进而自适应地得到最佳窗口尺度，有效改善了流场测量的空间分辨率。

大数据挖掘技术的光流场图像匹配方法设计

光流场图像匹配可以提高图像的质量,便于后继的光流场图像处理,而当前光流场图像匹配方法存在一些不足,如匹配耗时间长,错误率较高等,为了获得更优的光流场图像匹配结果,提出了大数据挖掘技术的光流场图像匹配方法。首先采集大量的光流场图像,并对图像预处理,消除干扰因素,从中提取边缘信息,幅值特征,角度特征等特征向量,并引入大数据挖掘技术根据对提取到的特征向量进行光流场图像匹配,最后对比其它图像匹配方法。实验结果表明,大数据挖掘技术的光流场图像匹配方法用时较短,提高光流场图像匹配效率,而且光流场图像匹配精度超过95%,大幅度减少了光流场图像匹配错误率,错误率仅为3%,具有广泛的应用范围。

高速度梯度流场图像PIV-PSV混合处理算法

在流场测量中往往存在较大速度变化的区域,所获得测量图像若出现高速模糊的情况,则会出现单独使用现有PIV/PSV方法不能完全准确描述速度场的情况。本文提出一种结合PIV-PSV的图像处理方法,通过将高速度梯度图像进行高速度区域与低速度区域的拆分后,分别使用PIV和PSV方法进行对应处理,最终将结果进行整合,该方法相对于使用单一方法处理的准确度有超过2倍以上的提升,该方法具有进一步提升的空间以及处理三维速度场的可扩展性。

数字图像处理与流场测量课程教学案例设计

数字图像处理技术在各行各业的应用日益广泛,在流场测量方面尤其常见且重要。上海理工大学能源与动力工程学院开设了数字图像处理与流场测量研究生课程,拟为相关研究生后续开展相关领域的研究奠定基础。本文从笔者开展的相关研究和实验中,针对图像增强、图像分割、频域处理和数学形态学处理等方面,选取了合适的图片,作为课程教学的相关案例,并对其进行阐述和分析,为相关教学工作者及学习者提供参考。

流场动态可视化平台关键技术与应用

流场模拟是计算机仿真模拟的热点和难点,是展现水流动态变化过程、辅助寻求水流运动变化规律的重要手段。流场可视化技术的应用可以有效提高水流信息表达的直观性与综合性。本文以北江航道水流可视化为例,开发了浏览器/服务器结构的航道水流可视化平台,重点研究了平台中基于图像的流场可视化技术,采用渲染到纹理技术和通用图形处理器计算中的乒乓技术实现了流场可视化的融合,采用基于视点动态渲染的方式有效解决了水流细节层次的表现问题。在北江航道水流可视化应用中流场动态显示效果流畅,运行帧率达60帧左右。该流场可视化实现方法可以为网页端流场可视化实现与应用提供参考。

电驱动微流体粒子图像测试系统

为了研究微米量级管道机械特性对小雷诺数流体运动传质机理的影响,建立了电驱动微流体粒子图像测试系统,系统包括倒置荧光显微镜、致冷图像传感器、微流体驱动高压电源及微流场位移矢量识别算法.通过实验测试及理论分析给出了系统的关键技术参数;通过测量示踪粒子表面电荷特性,以消除粒子电泳运动对电驱动流体PIV方法产生的测量偏差;测量了水力直径为30μm微管道中电渗流场,测量结果与理论分析的塞状流型一致;分析了布朗运动、粒子电泳运动以及相关算法误差,对粒子图像测速方法不确定度的影响.

基于平衡系数的Active Demons非刚性配准算法

经典的Active demons算法利用参考图像和浮动图像的梯度信息作为驱动力,并使用均化系数调节两种驱动力之间的强度.该算法克服了Demons算法单一使用参考图像的梯度信息作为驱动力的缺点,但是Active demons算法中的均化系数无法同时兼顾大形变和小形变区域的准确配准,还会导致配准的收敛速度和精确度相互制约的问题.为此,本文提出一种新的Active demons非刚性配准算法.提出的算法在Active demons扩散方程中引入一个称为平衡系数的新参数,与均化系数联合调整驱动力,不仅可以兼顾图像中同时具有的大形变和小形变区域的准确配准,而且在一定程度上缓和了收敛速度和精确度相互制约的问题.为了进一步提高配准的收敛速度和精确度,避免陷入局部极值,在新的配准算法的实现中引入由粗到细的多分辨率策略.在Checkboard测试图像、自然图像和医学图像上的实验结果表明,提出的算法较经典的Active demons算法收敛速度更快,配准精度平均提高了54.28%,接近最新的TV-L1光流场图像配准算法的配准精度,解决了Active demons算法存在的问题.

数值计算数据的流动显示模拟

在风洞试验中，光学流动显示技术是揭示流场特性的重要手段，为了把数值计算数据与流场显示结果进行直接比较，利用可视化技术把数值计算数据转化成阴影、纹影和马赫干涉条纹图像。首先根据有关研究结果和平面流动的特点，导出适于产生计算流场图像的关系式，重新计算流场数据，然后将导出的数据进行颜色编码。为了使图像效果良好、图像生成速度快，还介绍了一种自行设计的，时空效率较高的颜色编码算法。

PIV MEASUREMENT FOR SWIRLER FLOW FIELD IN GAS TURBINE COMBUSTOR

The characteristics of swirler flow field, including cold flow field and combustion flow field, in gas tur- bine combustor with two-stage swirler are studied by using particle image velocimetry （PIV）. Velocity compo- nents, fluctuation velocity, Reynolds stress and recirculation zone length are obtained, respectively. Influences of geometric parameter of primary hole, arrangement of primary hole, inlet air temperature, first-stage swirler an- gle and fuel/air ratio on flow field are investigated, respectively. The experimental results reveal that the primary recirculation zone lengths of combustion flow field are shorter than those of cold flow field, and the primary reeir- culation zone lengths decrease with the increase of inlet air temperature and fuel/air ratio. The change of the geo- metric parameter of primary hole casts an important influence on the swirler flow field in two-stage swirler com- bustor.

Flow Field Around Rushton Turbine in Stirred Tank by Particle Image Velocimetry Measurement

In this paper, particle image velocimetry (PIV) was used to measure the mean and root meansquare(RMS) velocity in the stirred tank with six-flat blade Rushton turbine and with no baffles. Two typesof motion patterns were studied. One was that the impeller runs at constant speed, the other was that the impellerruns at time-dependent speed and in a periodic way. The emphasis of the paper was on the comparison of meanand RMS velocity vector maps and profiles between these two types of motion patterns, and especial attention waspaid to the comparison of the mean velocity, time-averaged RMS velocity, phase averaged RMS velocity betweenthe constant 3 RPS (revolution per second) and time-dependent operation. The Reynolds number was between 763and 1527. The study explained the mechanism that time-dependent RPS is more efficient for mixing than that ofconstant RPS.

Oscillatory Flow Fields over Rough Wall： An Experimental Investigation

In this paper the results of an experimental investigation, finalized to analyze the effect of roughness elements on the Oscillatory Boundary Layer （OBL）, were presented and discussed. These experiments can be useful for the characterization of the complex hydrodynamic mechanisms in coastal environment, where the bottom boundary layer is very often subject to momentum exchange processes due to the presence of macro-structures on the bottom able to strongly influence and modify its own structure. In this investigation, experiments were performed in an oscillating water tunnel, covering a range of frequencies to from 0.646 up to 2.319 rad.s^-1. The roughness elements were modelled by mean of a matrix of stiff cylinders arranged on the bottom of the tunnel and two densities of cylinders were considered, corresponding to low and high density respectively. Velocity measurements were obtained by 2C DPIV （2 Component Digital Particle Image Velocimetry） technique. A detailed visualization of the flow through adjacent cylinders, including scalar velocity maps and streamlines are presented. Furthermore phase-averaged velocity distributions are here provided. Moreover, root-mean-squared velocities are considered and an empirical relation between （1） the root-mean-squared velocities and the distance from the bottom; （2） the velocity attenuation coefficient and the Reynolds number is obtained for both the considered configurations.

Effect of Swirl Cup's Secondary Swirler on Flow Field and Ignition Performance

In a gas turbine engine combustor, highly swiding combustion is usually adopted to stabilize flame and reduce pollutant emissions. Swirl cup, as an air blast atomizer, is widely used to provide a uniform presentation of fuel droplets to the combustor dome. This paper investigated the effect of secondary swirler on the flow field down- stream of the swirl cup using particle image velocimetry （PIV）. Three swirl cups＇ non-reacting flow field were studied： case A, B and C with secondary swirler vane angle 53°, 60° and 68° respectively. Detailed mean and transient velocities and vorticity in the center plane were obtained. From the PIV results, a sharp contrast flow field was obtained for case A to other two cases due to the lower secondary swirling intensity. The recirculation zone is collapsed in disorder for the case A. Ignition tests of the three cups were completed in a single cup com- bustor. In general, the ignition performance increases with the increasing of the secondary swirling intensity. For case A, the ignition performance is very unstable and has much randomness and there is no clear lean ignition boundary can be generated. This work can further understand the swirl behavior and ignition mechanism.

Experimental study of a supersonic turbulent boundary layer using PIV

Particle image velocimetry was applied to the study of the statistical properties and the coherent structures of a fiat plate turbulent boundary layer at Mach 3. The nanoparticles with a good flow-following capability in supersonic flows were adopted as the tracer particles in the present experiments. The results show that the Van Driest transformed mean velocity profile satisfies the incompressible scalings and reveals a log-law region that extends to yld=0.4, which is further away from the wall than that in incompressible boundary layers. The Reynolds stress profiles exhibit a plateau-like region in the log-law region. The hairpin vortices in the streamwise-wall-normal plane are identified using different velocity decompositions, which are similar to the results of the flow visualization via NPLS technique. And multiple hairpin vortices are found moving at nearly the same velocity in different regions of the boundary layer. In the streamwise-spanwise plane, elongated streaky structures are observed in the log-law region, and disappear in the outer region of the boundary layer, which is contrary to the flow visualization results.

Experimental investigation on the wing-wake interaction at the mid stroke in hovering flight of dragonfly

This paper focuses on flow structures of the wing-wake interaction between the hind wing and the wake of the forewing in hovering flight of a dragonfly since there are arguments whether the wing-wake interaction is useful or not.A mechanical flapping model with two tandem wings is used to study the interaction.In the device,two identical simplified model wings are mounted to the flapping model and they are both scaled up to keep the Reynolds number similar to those of dragonfly in hovering flight since our experiment is conducted in a water tank.The kinetic pattern of dragonfly(Aeschna juncea) is chosen because of its special interesting asymmetry.A multi-slice phase-locked stereo particle image velocimetry(PIV) system is used to record flow structures around the hind wing at the mid downstroke(t/T=0.25) and the mid upstroke(t/T=0.75).To make comparison of the flow field between with and without the influence of the wake,flow structures around a single flapping wing(hind wing without the existence of the forewing) at these two stroke phases are also recorded.A local vortex identification scheme called swirling strength is applied to determine the vortices around the wing and they are visualized with the iso-surface of swirling strength.This paper also presents contour lines of z at each spanwise position of the hind wing,the vortex core position of the leading edge vortex(LEV) of hind wing with respect to the upper surface of hind wing,the circulation of the hind wing LEV at each spanwise position and so on.Experimental results show that dimension and strength of the hind wing LEV are impaired at the mid stroke in comparison with the single wing LEV because of the downwash from the forewing.Our results also reveal that a wake vortex from the forewing traverses the upper surface of the hind wing at the mid downstroke and its distance to the upper surface is about 40% of the wing chord length.At the instant,the distance of the hind wing LEV to the upper surface is about 20% of the wing chord length.Thus,there must be a wing-wake interaction mechanism that makes the wake vortex become an additional LEV of the hind wing and it can partly compensate the hind wing for its lift loss caused by the downwash from the forewing.

Study on the flow field and concentration characteristics of the multiple tandem jets in crossflow

The characteristics of single and multiple tandem jets(n=2,3,4) in crossflow have been investigated using the realizable k-ε model.The results of this model agree well with experimental measurements using PIV(Particle Image Velocimetry) or LIF(Laser Induced Fluorescence).We analyzed the calculated results and obtained detailed properties of velocity and concentration of the multiple jets in the pre-merging and post-merging regions.When the velocity ratio is identical,the bending degree of the leading jet is greater than that of the rear jets.The last jet penetrates deeper as the jet number increases,and the shielding effect of the front jet declines with jet spacing increase.Interaction of the jet and crossflow induces formation and development of a counter-rotating vortex pair(CVP).CVP makes the distribution of concentration appear kidney-shaped(except in the merging region),and maximum concentration is at the center of the counter-rotating vortex.Concentration at the CVP center is 1.03-1.4 times that of the local jet trajectory.Post-merging velocity and concentration characteristics differ from those of the single jet because of the shielding effect and mixing of all jets.This paper presents a unified formula of trajectory,concentration half-width and trajectory dilution,by introducing a reduction factor.

Investigation on 3D flow field induced by a plasma actuator with serrated electrode

This paper presents an experimental investigation on flow field induced by a dielectric barrier discharge(DBD) plasma actuator with serrated electrodes in still air to further improve its flow control effectiveness. For comparison, the actuator with widely used linear electrodes was also studied. Experiments were carried out using 2D particle image velocimetry. Particular attention was given to the flow topology, discharge phenomenon, and vortex formation mechanism. Results showed that a 2D wall jet was induced by the linear actuators, whereas the plasma actuators with serrated electrode introduced a series of streamwise vorticities, which might benefit flow control(e.g., enhancing the momentum transport in the separated boundary flow). In addition, the mechanism of 3D flow topology induced by the serrated DBD actuator was analyzed in detail.