Experimental Study on Effect of A New Vortex Control Baffler and Its Influencing Factor

The horseshoe vortex generated around the sail-body junction of submarine has an important influence on the non-uniformity of submarine wake at propeller disc. The flow characteristics in the horseshoe vortex generated area are analyzed, and a new method of vortex control baffler is presented. The influence of vortex control baffler on the flow field around submarine main body with sail is numerically simulated. The wind tunnel experiment on submarine model is carried out, and it is proved that the vortex control baffler can weaken the hoi-seshoe vortex and decrease the non-uniformity of the wake at propeller disc. It is shown from the experiment results that the effect of vortex control baffler depends on its installation position; with a proper installation position, the non-uniform coefficient of submarine wake would be declined by about 50%; the Reynolds number of submarine model has an influence on the effect of vortex control baffler too, and the higher the Reynolds number is, the better the effect of the vortex control baffler is.

VORTEX CONTROL BY THE SPANWISE SUCTION FLOW ON THE UPPER SURFACE OF DELTA WING

The numerical investigation has been performed to explore the feasibility of vortex control by leading edge sucking excitation on a delta wing. The results reveal that the flow on the upper surface of the delta wing changes significantly in a wide range of the angle of attack. For the vortical flow at moderate angle of attack, the secondary and tertiary vortices are weakened or suppressed, and the total lift is almost unchanged. For the stalled flow at high angle of attack, the leading edge concentrated vortex is recovered, and the lift is enhanced with increasing suction rate. For the bluff-body flow at even high angles of attack, the lift can still be improved. The concentrated vortex disappears on the upper surface, and the load increment is nearly unchanged along the chordwise direction.

NUMERICAL SIMULATION AND EXPERIMENTAL STUDY OF THE NEW METHOD OF HORSESHOE VORTEX CONTROL

The horseshoe vortex generated around the sail-body junction of a submarine has an important influence on the uniformity of the submarine wake at the propeller disc.In this article,the horseshoe vortex is simulated by the Detached Eddy Simulation（DES） method,and a new method to control the horseshoe vortex by vortex control baffler is proposed.The numerical simulation shows that a kind of attached vortex,with the rotation direction opposite to that of horseshoe vortex,is generated by the vortex control baffler.With the attached vortex,the strength of the horseshoe vortex is significantly reduced.The wind tunnel experiment on a submarine model is carried out,and the axial velocities at the propeller disc of the submarine with and without vortex control baffler are measured by a hot wire anemometer system.It is shown from the experimental results that the vortex control baffler can enhance the uniformity of the wake at the propeller disc,which helps to improve the propeller performance.The engineering applicability of the vortex control baffler is discussed.

Open loop control of vortex-induced vibration of a circular cylinder

In this paper both numerical and experimental investigations have been carried out to suppress the vortex-induced vibration （VIV） of a circular cylinder in an electrically low-conducting fluid. The electromagnetic forces （Lorentz forces） in the azimuthal direction were generated through the mounted electrodes and magnets locally on the surface of the cylinder, which have been proved having an accelerating effect to the fluid on the surface of the cylinder. Results of computations are presented for synchronous vibration phenomenon of a cylinder at Re = 200, which are in good agreement with previous computational results. With the Lorentz forces loaded, the VIV of the cylinder has been suppressed successfully. Experimental results have also shown the same tendency and are in reasonable agreement with the numerical results.

Control of Vortex Shedding at Moderate Reynolds Numbers

The suppression method of vortex shedding from a circular cylinder has been studied experimentally in the Reynolds number range from 300 to 1600. The test is performed in a water channel. The model cylinder is 1 cm in diameter and 38 cm in length. A row of small rods of 0.18 cm in diameter and 1.5 cm in length are perpendicularly connected to the surface of the model cylinder and distributed along the meridian, The distance between the neighboring rods and the angle of attack of the rods can be changed so that the suppression effect on vortex shedding can be adjusted. The results show that vortex shedding can be suppressed effectively if the distance between the neighboring rods is smaller than 3 times and the cylinder diameter and the angle of attack is in the range of 30degreesless than or equal tobeta<90&DEG;.

Vortex dynamics over an airfoil controlled by a nanosecond pulse discharge plasma actuator at low wind speed

The vortex dynamics of flow over an airfoil controlled by a nanosecond pulse dielectric-barrierdischarge(NS-DBD) actuator is studied at a Reynolds number of 1?×?10~5 through wind tunnel experiments and numerical simulation. The numerical method is validated through comparison of the simulated and measured results regarding the effect of the discharge of an NS-DBD actuator placed on a flat plate. The simulated results show that vorticity is mainly induced by the baroclinic torque after plasma discharge, i.e. the term(■) in the equation of vorticity evolution. Both experimental and simulated results demonstrate that after the discharge of the NS-DBD actuator a series of vortices are developed in the shear layer and pull the high-moment fluid down to the wall, enhancing the mixing of internal and external flows.

The Design and Analysis of Helium Turbine Expander Impeller with a Given All-Over-Controlled Vortex Distribution

To make the large-scale helium cryogenic system of fusion device EAST （experimen- tal advanced super-conducting tokamak） run stably, as the core part, the helium turbine expander must meet the requirement of refrigeration capacity. However, previous designs were based on one dimension flow to determine the average fluid parameters and geometric parameters of impeller cross-sections, so that it could not describe real physical processes in the internal flow of the tur- bine expander. Therefore, based on the inverse proposition of streamline curvature method in the context of quasi-three-dimensional flows, the all-over-controlled vortex concept was adopted to design the impeller under specified condition. The wrap angle of the impeller blade and the whole flow distribution on the meridian plane were obtained; meanwhile the performance of the designed impeller was analyzed. Thus a new design method is proposed here for the inverse proposition of the helium turbine expander impeller.

基于改进涡流搜索算法的外骨骼迭代学习控制

为提升康复外骨骼机器人的步态跟踪性能,提出一种基于改进涡流搜索算法的迭代学习控制方法。首先针对传统迭代学习控制抗扰性差和控制信息缺失问题,引入PD控制器、自适应遗忘因子、误差过渡曲线和控制信息搜索等策略,改进迭代学习控制律;其次,基于多种策略对涡流搜索算法进行改进,提出了一种改进涡流搜索算法,改进后的算法可优化迭代学习控制的PD参数;最后进行行走实验,将提出的迭代学习控制方法与现有的同类算法进行仿真和数值比较,并测试了扰动情况下的跟踪性能。实验结果表明,所提方法的误差更小,跟踪性能更强。该算法改进了迭代学习控制的不足,具有较强的抗扰性能,保证了使用时的稳定性。

控制杆-强制旋转对圆柱涡激振动的抑制作用研究

为实现圆柱涡激振动的高效抑制,本文基于控制杆-强制旋转组合结构讨论圆柱涡激振动的抑制问题。对低雷诺数下的圆柱涡激振动进行数值模拟研究,对比分析不同控制杆数量和圆柱转速比下的流场特性、振动响应和流体力响应等。结果表明:与裸圆柱相比,控制杆具有一定的涡激振动抑制效果;对于三、五控制杆,通过调节转速比,可以实现最高98%的圆柱振幅抑制(对三控制杆,转速比为0.4~0.6;对五控制杆,转速比为0~0.2);圆柱振幅抑制与圆柱减阻区间相同;对于四、六控制杆,旋转对振幅抑制的影响较小;主圆柱表面的漩涡脱落和漩涡的合并会引起流体力系数的高幅波动,导致圆柱高振幅响应;没有漩涡合并和圆柱表面脱涡不明显时,流体力系数则无明显波动,圆柱振幅也显著降低。

大跨度钢-混结合梁悬索桥涡激振动控制指标体系研究

为保证已建桥梁发生涡激振动后桥梁结构的安全以及桥上行车和行人安全,提出综合考虑人员舒适性、结构受力和停车线形三方面的大跨度钢-混结合梁悬索桥涡激振动控制指标体系。该体系包含9项指标,分别为驾乘人员舒适度、驾乘人员晕动症、行人舒适度(狄克曼指标)、加劲梁强度、加劲梁应力、加劲梁挠度、桥面纵坡、竖曲线半径和停车视距。以武汉鹦鹉洲长江大桥为背景,分别计算了“限速”和“封桥”2个交通管制措施下9项指标对应的涡激振动振幅限值。在此基础上,将9项指标对应的涡激振动振幅限值的最小值作为涡激振动限值建议取值。结果表明:当该桥发生低阶竖弯涡激振动(VS1、VAS1)时,涡激振动的控制因素为加劲梁挠度指标;当大桥发生VAS2模态的竖弯涡激振动时,涡激振动由驾乘人员晕动症指标和行人舒适度指标共同控制;当大桥发生高阶竖弯涡激振动(VAS3、VAS4)时,涡激振动由行人舒适度指标控制。涡激振动控制指标体系及限值标准的计算框架可适用于不同桥型涡激振动限值的计算。

带碰撞的惯质调谐质量阻尼器对斜拉索涡激振动控制研究

在以往惯质调谐质量阻尼器(tuned mass damper-inerter, TMDI)的研究基础上,引入非线性碰撞机制,提出一种带碰撞的新型惯质调谐质量阻尼器(pounding tuned mass damper-inerter, PTMDI)来对斜拉索的涡激振动进行控制。该阻尼器不仅能减小装置尺寸,又能利用振子在碰撞过程中产生的加速度突变来提高惯质器的质量放大效应,在一定程度上解决传统惯质型阻尼器一端尽量固接的安装方式,布置上更为灵活。建立了设有该装置的斜拉索涡激减振控制方程,分析了拉索涡激振动特性,并对其减振性能进行了研究。对阻尼器惯容参数和碰撞参数的影响及优化问题进行了探讨,给出了最优参数的取值方法。算例表明,所提PTMDI能显著降低斜拉索的涡激振动响应,且在所提优化方法得到的最优参数下具有更为优越的控制能力。对于常遇风时拉索出现的多模态涡激振动控制分析表明,碰撞机制能使PTMDI的鲁棒性得到提升,对多模态涡激振动也有相当程度的控制效果。

圆端形墩台尾迹水动力特性开缝控制三维数值分析

水流绕流水闸闸墩、导流墩等水工建筑物后产生旋涡分离流,其三维尾迹结构水动力特性复杂,对旋涡分离流进行流动控制,不仅是闸墩优化设计的需要,而且关系到工程运行的效率和工程安全。在验证三维水动力数学模型的基础上,对圆端形墩台开缝后的旋涡分离流和流动控制的三维水动力特性进行了研究,对比了无缝与开缝墩台方案下纵向、横向和竖向方向的时均流速分布,紊流动能以及紊流强度分布等水力学指标,探究了开缝墩台水动力特性。分析表明,墩台开缝后可以明显改善墩台后方的水流结构,开缝位置越靠近水深的中部位置,对墩后尾流旋涡的抑制越大,对绕流墩台绕流的控制越来越好,水深中部位置开缝最大程度的影响了开缝墩后的上部水流和下部水流,使得开缝对时均流速的影响最大,开缝对旋涡的抑制也最大最佳。为抑制墩后的旋涡对工程的不利影响,工程的设计中应首先确定墩台后的水深,开缝位置应尽量设置在墩台后水深的中部位置。

压气机内部旋转不稳定的研究综述

旋转不稳定是压气机工作在高负荷近失速工况时的一种常见现象。研究旋转不稳定在降低压气机工作噪声、减小流致振动以及保障航空发动机稳定工作等方面具有重要意义。首先对旋转不稳定现象进行了回顾,详细讨论了旋转不稳定的特征。其次,重点调研了旋转不稳定的起源和机理,将旋转不稳定产生的原因归纳为叶尖泄漏流、涡脱落以及流动剪切等类别。此外,回顾了模拟旋转不稳定的数值方法,讨论了多种流动控制手段对旋转不稳定的作用效果。最后,对旋转不稳定的研究现状进行了总结,对未来的研究趋势进行了展望。

高速列车开闭机构涡流发生器的气动减阻设计

为了降低列车高速运行受到的气动阻力,采用基于SST(shear stress transport)k−ω湍流模型的雷诺时均法研究高速列车尾车开闭机构位置安装涡流发生器对尾部流动特征以及列车气动载荷的影响。研究结果表明:涡流发生器能显著改变尾车周围的流场,产生一对与原涡流旋向相反的涡流结构,降低尾流涡强度和范围,在尾车安装涡流发生器后,气流流动受到涡流发生器的阻碍产生积聚,从而在尾车表面形成较大的正压区域,降低尾车压差阻力和气动升力;随着涡流发生器安装位置向尾车鼻尖靠近,减升效果逐渐降低,尾车最大减升率为36.8%;尾车阻力随着涡流发生器安装位置向后移动呈现出先减小后增大的趋势,尾车气动阻力最大减阻幅度为4.54%。合理的开闭机构涡流发生器能有效控制尾流结构,进而控制尾车气动力,为高速列车气动减阻提供新思路。

旋涡空化水动力学特性研究进展与展望

涡空化作为一种在推进器叶顶涡心处产生的空化现象,在推进器原型上往往最早出现,其一旦发生将会严重影响舰艇的声隐身性能(噪声增加10 dB以上),在很大程度上限制了舰艇临界航速的进一步提升,因而长期以来一直是空化水动力学领域研究的重点与难点课题之一.本文首先简要介绍了旋涡空化流动相较于其他形式空化流动的特点,并以梢涡空化为主要对象,系统阐述了旋涡空化初生、发展的演变行为与流动机理研究,从空化三要素的角度深入讨论了其影响因素与作用机制.在此基础上,本文分别对旋涡空化流动中尺度效应、流动控制等关键问题的相关研究进展进行了回顾,较为系统地梳理了旋涡空化尺度效应的内在原因以及旋涡空化流动控制方法与控制思路.最后,本文针对目前旋涡空化研究领域关注的重点与难点问题,对旋涡空化流动研究中采用的实验测量及数值模拟技术进行了总结与展望.

太赫兹多维度相位调控反射超表面研究

数字编码超表面可以控制电磁波传输,受到了广泛关注。大多数报道的编码超表面基于几何相位或传输相位实现对反射或者透射线极化波和圆极化波的2π相位覆盖,限制了太赫兹波调控灵活性。提出传输相位和几何相位相结合排布超表面,在线极化太赫兹波入射下,基于传输相位机理设计的超表面产生了涡旋波束。根据几何相位原理,在圆极化太赫兹波入射下,设计的超表面产生了反射波束的偏转,超表面可以在多个频点产生涡旋波束,在0.9和1.2 THz处产生拓扑荷数l=1和l=2的涡旋波束,通过卷积生成偏折涡旋波束。最后设计聚焦超表面,实现了反射聚焦。研究结果表明,设计的超表面提供了一种多自由度的太赫兹波偏振和相位操控方法,在太赫兹系统具有广阔的应用潜力。

基于气动措施和滑轮式TMD的人行景观桥涡振混合控制研究

为了解决传统式调谐质量阻尼器(tuned mass damper, TMD)在控制低频桥梁结构中弹簧静伸长过长的问题,介绍了滑轮式TMD及其用于结构振动控制时的特点,指出滑轮式TMD可以有效减小弹簧静伸长量。以一座人行景观桥为例,研究了采用气动措施和滑轮式TMD对该桥的涡振控制效果。风洞试验结果显示,在最优气动措施下,主梁的涡振振幅减少了一半以上,但仍未达到行人舒适性要求。基于Scanlan线性涡激力模型进行滑轮式TMD的优化设计,在气动措施的基础上进一步辅以滑轮式TMD进行涡振控制。分析结果表明,气动措施结合滑轮式TMD进行涡振控制能够满足行人舒适性要求,并确保滑轮式TMD质量块的工作行程不超过限值。通过同时采用气动措施和滑轮式TMD,可以满足主梁涡振限值、TMD弹簧静伸长量和工作行程等多重要求,从而有效控制主梁的涡振现象。本文提出的混合控制方案为类似工程中的涡振控制提供了有益参考,可为工程实践提供指导。

CONTROL OF UNSTEADY VORTICAL LIFT ON AN AIRFOIL BY LEADING-EDGE BLOWING-SUCTION

The effects of leading-edge blowing-suction on the vortex how past an airfoil at high incidence are investigated numerically by solving the Navier-Stokes equations. The results indicate that the frequency of the flowfield excited by the periodic blowing-suction locks into the forcing frequency, which is half of the dominant frequency for the flow past a fixed airfoil without injection. In that case, a well-developed primary leading-edge vortex occupies the upper surface of the airfoil and the largest lift augmentation is obtained.

基于光泵效应诱导涡旋光的通断控制实验教学设计

随着对涡旋光研究的深入,对涡旋光在各种介质中的传输控制提出了更高的要求。本实验利用光泵效应在三能级热源子系统中完成了对涡旋光传输通断的控制,通过分别控制信号光的失谐程度、泵浦光的光功率大小以及铷原子气体池的温度高低等参数来调控信号光的传输透过率,从而实现对涡旋光传输的通断控制。本文将理论与实验相结合,使学生通过实验更加充分地理解理论知识,培养和提高了学生的实践能力和创新意识。

涡流控尘装置径轴向风量分配规律试验研究

针对涡流控尘装置径轴向风量分配问题,提出通过监控风机频率来调控径轴向风量的思路。实验室搭建了由压入式风机、涡流控尘装置和试验管道组成的试验系统,在压入风机40、45、50 Hz频率下,以及在涡流风机30、35、40、45、50 Hz频率下,采用截面动压法测试得到径轴向风量分配规律:压入风量Q压和轴向风量Q轴与压入风机频率f_(1)呈单调增的关系,与涡流风机频率f_(2)呈单调减的关系。基于径轴向风量分配规律,建立了关于5f_(1)-f_(2)的一次函数和关于f_(1)/f_(2)的二次函数风量调控模型。最后通过试验实测验证,模型计算值与实测值基本一致,最大绝对误差为7.2 m^(3)/min,调控模型的准确性较好。