Tight focusing of axially symmetric polarized vortex beams

Tight focusing of axially symmetric polarized vortex beams is studied numerically based on vector diffraction theory. The mathematical expressions for the focused fields are derived. Simulation results show that the focused fields and phase distributions at focus are largely influenced by both the polarization order and topological charge of the incident beams. Moreover, focal spots with flat-topped or tightly-focused patterns can be flexibly achieved by carefully choosing the polar- ization order and the topological charge, which confirms the potential of such beams in wide applications, such as optical tweezers, laser printing, lithography, and material processing.

Numerical Investigation on Vortex Structure and Aerodynamic Noise Performance of Small Axial Flow Fan

The details of unsteady flow field in small axial fans are described and the relationship between the internal flow char- acteristics and aerodynamic noise of small axial flow fans are explored in the manuscript. Firstly, the broadband noise model is introduced to calculate the distributions of broadband noise sources in fan’s internal flow field, and further fan’s internal flow characteristics affecting broadband noise sources are analyzed by the main distributions of broad- band noise sources. Secondly, the unsteady characteristics of vortex structure in fan’s internal flow field are analyzed by large eddy simulation, and FH-W acoustic model is introduced to calculate aerodynamic noise affected by the unsteady characteristics of vortex structure. Finally, Monitoring points are set up near and far field of small axial fans, at which sound pressure level and spectral characteristics are analyzed. The results show that broadband noise sources are mainly distributed at the tip clearance close to blade trailing edge and one third of chord length of blade trailing edge of small axial fans. The maximum sound power of broadband noise sources at the tip clearance is greater than that at blade trail- ing edge. Sound power level of broadband noise near one third of blade chord length of blade trailing edge is first in- creasing and then decreasing when the distance between radial planes and the center of fan hub increases. Fan’s internal flow characteristics affecting broadband noise sources are the tip leakage vortex and the trailing edge vortex shedding. The tip leakage vortices at the leading edge of blade tip first integrate and then break down, while vortex cores of the trailing edge vortex shedding gradually move from blade hub to one-third of blade chord length and then move to far field within a one-seventh of the rotation cycle. Within a flow passage of fan rotation period, sound pressure level of the monitoring points is relevant to the unsteady feature of vortex structure and the main bands of aerodynamic noise of monitor points are irrelevant to the unsteady feature of vortex structure, relating to the distance between the monitor points and fan. With the above distance increasing, the main bands of aerodynamic noise are widened and moved from the low bands to high bands. All conclusions in the paper will provide significant references for reducing the noise of small axial flow fans.

两相出口对轴向涡流分离器的影响研究

为了更好地预测分离器的分离效率和设计出更高效的分离器,应进一步了解其内部流场分布特性及不同结构参数对内部流场的影响。为此,采用Fluent软件对轴向涡流分离器内部流场分布特性和分离器两相出口结构对内部流场及分离性能的影响展开研究。研究结果表明:当水相出口直径增加到40 mm时,轴向涡流分离器水相出口处会形成一个低速回流区域,可通过减小管径收缩程度等方法来缓解该现象的影响;在其他结构参数不变的情况下,分离器的分离效率是关于雷诺数和两相出口与入口直径之比的函数;分离效率正比于油相出口与入口直径之比,与雷诺数、水相出口与入口直径之比均为二次函数关系。研究结论可为进一步优化轴向涡流分离器的分离性能提供理论参考。

“Click”运动高升力机制

研究了具有“Click”运动的模型翼在三维流场中的气动特性.采用计算流体力学方法求解三维非定常不可压缩Navier-Stokes方程,对比了简谐和“Click”运动所产生的升力与阻力,研究了升力最大时的前缘涡特性和展向流动.结果表明,在下拍过程的升力最大处,“Click”和简谐运动的前缘涡能够分别维持至翼展的80%和60%处.两种运动都会在翼展方向存在维持展向流动的压力梯度,而“Click”运动具有更显著的展向压力梯度,对展向涡度的能量输运效率更高,因此其前缘涡能够保持更完整的形态.在上拍过程中,两种运动的前缘涡形态差异不明显,“Click”运动快速上拍的运动特点使其能够快速地摆脱尾涡的干扰,从而维持升力.

基于叶片表面附面层分析的风扇性能研究

为了提高轴流散热风扇效率,本文应用孤立翼型设计法,将高升阻比翼型CAP-12应用到轴流风扇的设计,设计出一款轴流风扇,并对设计出的轴流风扇进行了数值模拟研究,基于附面层理论,分析了风扇的静特性、内部流场与气动特性。计算结果表明:在叶片吸力面叶尖靠近尾缘处会产生有限叶高的诱导旋涡,是导致风扇性能效率降低的主要原因,在对轴流风扇进行结构优化时,应着重考虑该区域,该研究结果可为轴流风扇的性能优化设计提供理论基础。

EXPERIMENTAL INVESTIGATION OF TIP CLEARANCE FLOW FOR AN AXIAL FLOW FAN ROTOR

The flow field in the tip region of an axial ventilation fan is investigated with a particle image velocimeter （PIV） system at the design condition. Flow fields with three different tip clearances are surveyed on three different circumferential planes, respectively. The phase-locked average method is used to investigate the generation and the development of a tip leakage vortex. The result from PIV system is compared with that from a particle dynamics anemometer（PDA） system. Both data are in good agreement and the structure of the tip leakage vortex for the rotor is illustrated. The characteristic of a leakage vortex is described in both velocity vectors and vortical contours. The unsteadiness of the leakage vortex and the position of the vortex are surveyed in detail, which interprets the discrepancy between the numerical simulation and PDA experimental results to a certain extent. The center loci of tip leakage vortex at different times and the mean center loci of the leakage vortex are displayed particularly. Finally, the trajectories of the tip leakage vortex by the experimental measurement are compared with predictions from the existing models for high speed and high-pressure compressors and turbines when appropriately interpreted. A good agreement is obtained.

COMPUTATIONAL AND EXPERI-MENTAL STUDY ON TIP LEAKAGE VORTEX OF CIRCUMFERENTIAL SKEWED BLADES

In the steady operation condition, the experiments and the numerical simulations are used to investigate the tip leakage flow fields in three low pressure axial flow fans with three kinds of circumferential skewed rotors, including the radial rotor, the forward-skewed rotor and the back- ward-skewed rotor. The three-dimensional viscous flow fields of the fans are computed. In the experiments, the two-dimensional plane particle image velocimetry （PIV） system is used to measure the flow fields in the tip region of three different pitchwise positions of each fan. The results show that the computational results agree well with the experimental data in the flow field of the tip region of each fan. The tip leakage vortex core segments based on method of the eigenmode analysis can display clearly some characteristics of the tip leakage vortex, such as the origination position of tip leak- age vortex, the development of vortex strength, and so on. Compared with the radial rotor, the other two skewed rotors can increase the stability of the tip leakage vortex and the increment in the forward-skewed rotor is more than that in the backward-skewed one. Among the tip leakage vortices of the three rotors, the velocity of the vortex in the forward-skewed rotor is th6 highest in the circumferential direction and the lowest in the axial direction.

C_3-Symmetric Molecules with Axial Chirality and Handed Arrangement of Dipole Fields

Introduction Chirality is defined as the absence of inversion symmetry,however,it is actually a pseudo-scalar of objects or figures,and does not depend for its definition on any connection to the physical world[1-5]. Logically,chiral molecules may possess other inherent physical quantity that guarantees the connection to the physical world[6,7].

Experimental study on inlet vortex in pump sump

In order to study the mechanism of the vortex generation at the bottom of the pump sump below the flare tube,twenty pressure pulsation monitoring points were arranged at the bottom of the pump sump below the flare tube,and the pressure fluctuation experiments were carried out under different flow conditions.The experimental results show that the frequency of pressure fluctuation at the bottom of the pump sump is twice of the rotational frequency of the impeller blade.The vortex below the flare tube is easy to generate under the large flow conditions and mainly concentrates at the right front position below the flare tube.The position of the vortex occurring is corresponding to the position of the low-pressure region below flare tube.

Design of Half-Ducted Axial Flow Fan Considering Radial Inflow and Outflow

Half-ducted fan and ducted fan have been designed and numerically analyzed for investigating the radial flow effect on the overall performance and the three dimensional flow field in design. Based on quasi-three dimensional flow theory, the meridional flow was calculated by adopting the radial balance equations, while the calculation of the blade to blade flow was obtained by 2D cascade data with the correction by a potential flow theory. Two types of axial flow fan were designed. One is the full ducted case as if it was in the straight pipe and another is the half-ducted case with the radial inflow and outflow. The previous experimental results of authors were used to decide the inclinations of both the inflow and outflow. And the circular arc blade with equal thickness was adopted. The numerical results indicate that both of the designed fans can reach the specified efficiency and also the efficiency surpasses more than 11%. Furthermore, the static pressure characteristic of half-ducted fan is much better than that of ducted fan. In comparison of the three dimensional internal flow of these two fans, the improvement of the flow angle at inlet and outlet, the distributions of velocity in the flow field and the pressure distributions on the blade surfaces can be achieved more successfully in accordance with the design intension on consideration of flow angle in design. The conclusion that half-ducted design with considering radial inflow and outflow is feasible and valid in comparison with ducted design for axial flow fans has been obtained at the end of the paper.

Effect of Tip-Blade Cutting on the Performance of Large Scale Axial Fan

The effect of tip-blade cutting on the performance of a large scale axial fan was investigated using computational fluid dynamics(CFD)methods.Experiments verified the numerical simulations.The original fan was compared with the one with tip-cutting in terms of dimensionless characteristic and aerodynamic performance in tip region under the conditions of the maximum efficiency point and near-stall point.The results showed that double leakage flow occurred in tip clearance at maximum efficiency point and spillage of leakage flow from leading edge occurred in tip-blade region at near-stall point for the both two fans;and that tip-cutting with 6% of blade height could reduce the intensity of tip-leakage vortex and increase flow capacity in tip blade region,and hold the stall margin almost the same as the original fan.The maximum efficiency of the fan with tip-cutting was improved by1%,and the ability of total pressure rising was obviously greater than the original fan.

叶顶喷气对跨音速轴流压气机稳定裕度影响的数值研究

为了研究叶顶喷气机匣处理方式对轴流压气机稳定裕度的影响,针对Rotor37开展了叶顶喷气的定常数值研究。相关文献指出,喷嘴出口气流角、喷嘴轴向位置、喷嘴覆盖比率及喷嘴进口总压4个参数对稳定裕度的影响最为显著。因此,本文着重对这四个参数构建响应面,同时结合主流的单通道计算模型,详细分析了它们之间的交互关系及相应的参数变化对压气机稳定性的影响,并拟合出回归方程。结果显示,在最佳参数设置下,单通道计算模型中压气机的稳定裕度最大可以增加8%左右。在此基础上,又对四通道压气机计算模型进行了气动计算与分析,发现叶顶喷气射流会按照与压气机旋转相反的方向作用于相邻的叶片流道,抑制该流道泄漏涡的产生,进而改善该流道内的流动。研究表明,采用叶顶喷气方法可以降低叶片前缘载荷,改变压气机的失速类型,从而增加压气机的稳定裕度。

轴向间距对FBCDZ-10-No20型对旋风机失速过程的影响

对旋风机在小流量工况运行时容易出现失速甚至喘振等不稳定现象,为研究轴向间距对对旋风机失速起始及其发展与传播过程的影响,采用Shear Stress Transport(剪切应力输运)k-ω湍流模型,对一台FBCDZ-10-No20型对旋风机全通道内的非定常流动进行数值模拟,探究了2种轴向间距下对旋风机的失速发展过程。结果表明:轴向间距对对旋风机失速起始及发展过程具有显著影响。在失速起始阶段,当对旋风机两级叶轮的轴向间距为170 mm时,失速起始扰动首先发生于后级叶根吸力面的尾缘区域,之后扰动沿径向从叶根向叶顶发展,沿周向向某个叶片通道聚集,导致该叶片通道堵塞,从而引起对旋风机失速;当轴向间距为70 mm时,失速起始扰动先后发生于前、后级的叶顶区域,之后扰动逐渐增强,最终发生失速。在完全失速阶段,轴向间距对于失速涡团沿周向、轴向及径向的传播都具有显著影响。轴向间距为170 mm时对旋风机进入单涡团全叶高失速,失速涡团沿轴向传播范围限于后级叶轮区域,沿周向以33.3%的后级转速旋转;轴向间距为70 mm时对旋风机进入多涡团部分叶高失速,失速涡团先后在两级叶轮叶顶区域产生,沿轴向向上、下游传播,沿径向分散于各叶片通道的70%叶高以上区域。由于两级叶轮轴向间距的改变,引起了对旋风机的失速起始扰动类型发生了由“局部喘振型”向“突尖型”的转变。

叶根前缘VG对微型轴流风扇性能的影响

为降低微型轴流风扇叶根端壁区域二次流所引起的损失,根据涡流发生器的流动控制思想,提出一种在叶根前缘压力面侧设置微型直板的新型流动控制方法;以某微型轴流风扇为研究对象,采用数值模拟结合实验的方法,重点分析了不同安装角的涡流发生器对轴流风扇气动性能及内部流场的影响;研究结果表明:涡流发生器存在提高风扇静压与静压效率的最佳几何安装角,涡流发生器会对叶轮内部流场产生影响,由涡流发生器所形成的诱导涡与压力侧马蹄涡分支进行掺混,会削弱马蹄涡的强度,在一定程度上抑制了由马蹄涡参与演变成的通道涡的发展,使叶轮流道中流体进行再分配;在宏观方面,结构匹配的涡流发生器可提高风扇的气动性能,当涡流发生器安装角度为15°时,在风扇高效运行区间内同原型风扇相比,安装涡流发生器的风扇其静压最多提高8%,静压效率最大可提升2.4%。对于大轮毂比微型轴流风扇,由通道涡所引起的二次流损失不容忽视,同时在对叶轮进行设计优化时应重视叶根端壁处的结构设计。

圆偏振涡旋光致非轴向自旋和轨道运动研究

为了实现粒子的非轴向旋转操控,对圆偏振涡旋光的光致旋转特性进行了研究。理论上,利用T矩阵理论,计算光场作用于微粒的光力和力矩,分析圆偏振涡旋光场中自旋角动量和轨道角动量的取向对非轴向旋转效应的影响。研究结果表明:当轨道角动量和自旋角动量的方向相同时,粒子除受轨道矩和轴向自旋矩作用外,还受一个可观的横向自旋矩作用,可以诱导粒子同时做轨道和非轴向自旋运动;当轨道角动量和自旋角动量方向相反,则粒子受到的横向自旋矩难以驱动其做非轴向自旋运动。实验上,利用全息光镊系统捕获微米尺度的粒子,观察到粒子做轨道运动时的非轴向自旋现象,对理论研究结果进行了初步验证。

叶片数对轴流风机气动性能影响的数值研究

叶片数量是影响风机气动性能与经济性的重要因素。本文针对空调器室外机用轴流风机的性能要求,设计了二叶片、三叶片和四叶片轴流风机。采用数值计算方法,研究了叶片数量对轴流风机气动性能的影响。研究结果表明:叶片数量越少,湍流度越大,风机进出口气流扰动加剧,气动涡流噪声也随之增大;二叶片风机由于其叶片数最少,其出口风量相比四叶片风机减少了23.5%,三叶片风机相比四叶片风机其出口风量减少了4.7%。随着叶片数量的减少,尽管风机做功能力有所下降,但叶片用材减少,风机的加工制造成本也相应降低。

变张力细长柔性立管涡激振动响应特性数值研究

基于尾流振子模型,对轴向时变张力下细长柔性立管涡激振动响应特性进行数值研究。研究考虑三种不同的流剖面:线性剪切、指数剪切、以及真实阶梯流剖面;采用二阶中心差分方法求解结构振动和尾流振子的耦合方程;系统地比较三种不同流剖面下结构的振动位移、振动频率、位移包络线,以及位移时空演化等VIV响应特性。数值结果表明,线性剪切流下VIV振动位移和振动频率均与真实阶梯流下位移和频率存在很大差别,指数剪切流下VIV振动位移与真实阶梯流下情况非常接近,但指数剪切流下VIV振动频率与真实阶梯流下频率仍有较大差别。

涡流空气分级机圆弧形叶片转笼的设计

涡流空气分级机分级粒径主要受转笼转速与入口风速匹配关系的影响。入口风速一定时,转笼转速越高,分级粒径越小,但这会造成流场速度分布不均匀,而降低分级精度。利用Fluent软件对具有直叶片转笼结构的涡流空气分级机进行建模和数值模拟,分析转笼内流场特性,针对其流场不均匀及转笼入口冲角大等现象,对转笼叶片的形状及安装角进行改进,提出一种圆弧形叶片转笼的设计方法。通过数值模拟及物料试验对改进结果进行验证,数值模拟结果表明:圆弧形叶片转笼入口冲角减小,流道内流场更加均匀,分级粒径减小。碳酸钙分级试验结果与数值模拟结果吻合:设计工况即入口风速为12 m/s,转笼转速为1 200 r/min时,采用设计的圆弧形叶片转笼在保持分级精度不变的情况下,分级粒径减小了11.5%。

制动工况下液力偶合器涡轮轴向漩涡流场试验分析

轴向漩涡流动是研究液力偶合器能量损耗的重要基础。该文基于粒子图像测速技术采集制动工况下液力偶合器轴向漩涡流场图像,通过图像处理技术识别并提取液力偶合器外壁面上特殊几何结构所呈现的光学特征,完成流动图像动态标定。利用霍夫变化直线检测算法识别泵轮轴向流场流速方向,通过图像互相关算法并采用查询窗口偏移技术提取涡轮轴向漩涡流场结构,应用误矢量识别算法检测错误流速矢量并予以剔除,获得优化的流动图谱。研究结果表明:泵轮轴向流场中液流是一种复合加速运动;涡轮轴向流场中液流是一种多尺度漩涡流动,主流区域上流速值为0.2~0.4 m/s,叶片与壁面组成的角隅区域上形成小尺度涡旋,角隅区域上流速值为0.6~1.1 m/s。上侧叶片与泵轮、涡轮交界面处的角隅区域上存在与主流循环流动方向相同的小尺度涡旋,涡量数值为?8 s?1,此处涡旋将促进液力能量的传递与转换,其他3个角隅区域上的涡旋方向与此相反,涡量数值分别为13、15和20 s?1,由于该局部区域小尺度涡与主循环涡的相互混合作用,引起流动迟缓,造成能量损耗。试验研究结果将为液力偶合器轴向漩涡流动现象提供有价值的参考依据。

前伸式双叶片污水泵内部流场PIV试验

以一台比转速为70的前伸式扭曲双叶片污水泵为研究对象,采用PIV(particle image velocimetry)技术对双叶片污水泵进行内部流场测量,分析了该泵在不同流量工况下(Q/Qdes=0.4、0.6、0.8、1、1.2、1.4)叶轮内部流场的相对速度分布,研究了轴向旋涡和低速区随流量变化的形态特性,发现在流道中部靠近叶片工作面上存在低速区及与叶轮旋转方向相反的轴向旋涡,且随着流量的增大,低速区与轴向旋涡逐渐减小;引入少叶片数离心泵内部流动理论,揭示了低速区和轴向旋涡存在和发展的内在机理。分析了在流量Q/Qdes=0.6时叶轮和蜗壳不同相对位置的相对速度场分布,研究了叶轮和蜗壳之间动静干涉作用对轴向旋涡的影响,发现当轴向旋涡经过蜗壳隔舌时,其与叶轮之间的干涉作用使得轴向旋涡向下游偏移。研究结果对前伸式扭曲双叶片污水泵的内部流动规律研究具有重要参考价值。