Investigation of Separated Flow around a Curved Air Intake

This paper prcsents an investigation of two-dimensional separated flow in and around a submerged curved intake by experiment and computation. The eniptic Navier-Stokes equations are employed which are discreted in body-fitted coordinate system by the SIMPLE method. The results show that the flow separation exists near and behind the inlet and the duct flow is distorted. Comparison between the computational and experimental data is fairly satisfactory.

Three Dimensional Numerical Analysis of Two Phase Flow Separation Using Swirling Fluidics

Vapor-water two phase flow separation in pressure vessel of nuclear power plants is accomplished with swirl motion using vanes. In order to reduce separation pressure loss and to make it economic, a new type of low cost simplified innovative separator using lattice core configuration is proposed where swirling is caused by the orthogonal driving flow. The performance of the separator has been assessed numerically with the commercial CFD code FLUENT 14.0. The numerical analysis is compared with the experiment. The geometry and flow conditions are chosen according to the experiment. In the analysis, standard k – e and realizable k – e turbulence models are implemented. The prediction of maximum air void fraction with realizable k – e model was almost the same as input air void fraction but the void fraction computed by standard k – e model was compared better with the experimental results than the realizable k – e model. Some discrepancies in flow pattern between the experimental and simulation results are observed which might be due to the difference of nozzle shape. However, a more detailed model is necessary to arrive at the final conclusion.

On the Role of Electrodes in Introducing Airflow Distortion in Residential Oil Burners

Computational Fluid Dynamics (CFD) simulations of airflow through a retention head residential oil burner were carried out to study the velocity field near and around the fuel spray. The simulations revealed (as expected, based on some previous experimental measurements) the velocity flow field to be far from axisymmetric. Moreover, the center of the swirling airflow was found to be at some radial distance away from the physical centerline of the flame tube. Since it was suspected that the two electrodes just upstream of the retention ring of the burner might be responsible for this flow distortion, additional CFD simulations were then carried out for the cases of no electrodes and 4-electrodes. The results clearly show that all flow distortions (velocity deviations from axisymmetric value) vanish when no electrodes are present and that the flow distortions are reduced by a factor of 2 when two additional dummy electrodes (for a total of 4 electrodes) are included in the burner design. Furthermore, for the 4-electrode case, the eccentricity of the swirling airflow is reduced by almost a factor of 3 as compared to the base design case of 2-electrodes.

Numerical prediction of vortex flow and thermal separation in a subsonic vortex tube

This work was aimed at gaining understanding of the physical behaviours of the flow and temperature separation process in a vortex tube. To investigate the cold mass fraction’s effect on the temperature separation, the numerical calculation was carried out using an algebraic Reynolds stress model (ASM) and the standard k-ε model. The modelling of turbulence of com-pressible, complex flows used in the simulation is discussed. Emphasis is given to the derivation of the ASM for 2D axisymmet-rical flows, particularly to the model constants in the algebraic Reynolds stress equations. The TEFESS code, based on a staggered Finite Volume approach with the standard k-ε model and first-order numerical schemes, was used to carry out all the computations. The predicted results for strongly swirling turbulent compressible flow in a vortex tube suggested that the use of the ASM leads to better agreement between the numerical results and experimental data, while the k-ε model cannot capture the stabilizing effect of the swirl.

Numerical Simulation of Turbulent Swirling Pipe Flow with an Internal Conical Bluff Body

Turbulent swirling flow inside a short pipe interacting with a conical bluff body was simulated using the commercial CFD code Fluent.The geometry used is a simplified version of a novel liquid/gas separator used in multiphase flow metering.Three turbulence models,belonging to the Reynolds averaged Navier-Stokes(RANS)equations framework,are used.These are,RNG k-ε,SST k-ωand the full Reynolds stress model(RSM)in their steady and unsteady versions.Steady and unsteady RSM simulations show similar behavior.Compared to other turbulence models,they yield the best predictions of the mean velocity profiles though they exhibit some discrepancies in the core region.The influence of the Reynolds number on velocity profiles,swirl decay,and wall pressure on the bluff body are also presented.For Reynolds numbers generating a Rankine-like velocity profile,the width and magnitude of flow reversal zone decreases along the pipe axis disappearing downstream for lower Reynolds numbers.The tangential velocity peaks increase with increasing Reynolds number.The swirl decay rate follows an exponential form in accordance with the existing literature.These flow features would affect the performance of the real separator and,thus,the multiphase flow meter,noticeably.

Serpentine Inlet Performance Enhancement Using Vortex Generator Based Flow Control

In order to provide the line-of-sight blockage of the engine face for an advanced Uninhabited Combat Air Vehicle（UCAV）, a highly curved serpentine inlet is proposed and experimentally studied. Based on the static pressure distribution measurement along the wall, the flow separation is found at the top wall of the second S duct for the baseline inlet design, which yields a high flow distortion at the exit plane. To improve the flow uniformity, a single array of vortex generators （VGs） is employed within the inlet. In this experimental study, the effects of mass flow ratio, free stream Mach number, angle of attack and yaw on the performance of a serpentine inlet instrumented with VGs are obtained. Results indicate： （1） Compared with the baseline serpentine design without flow control, the application of the VGs promotes the mixing of core flow and the low momentum flow in the boundary layer and thus prevents the flow separation. Under the design condition, the exit flow distortion （-↑△σ0） decreases from 11.7% to 2.3% by using the VGs. （2） With the descent of the free stream Mach number the total pressure loss decreases. However, the circular total pressure distortion increases. When the angle of attack rises from - 4° to 8°, the total pressure recovery and the circular total pressure distortion both go down. In addition, with the increase of yaw the total pressure recovery is fairly constant, while the circular total pressure distortion ascends gradually. （3） When Mao = 0.6-0.8, a = -4°-8° and β = 0°-6°, the total pressure recovery varies between 0.936 and 0. 961, the circular total pressure distortion coefficient varies between 1.4 % and 5.4 % and the synthesis distortion coefficient has a ranges from 3.8 % to 7.0 %. The experimental results confirm the excellent performance of the newly designed serpentine inlet incorporating VGs.

Supersonic swirling characteristics of natural gas in convergent-divergent nozzles

The supersonic nozzle is a new apparatus which can be used to condense and separate water and heavy hydrocarbons from natural gas.The swirling separation of natural gas in the convergent-divergent nozzle was numerically simulated based on a new design which incorporates a central body. Axial distribution of the main parameters of gas flow was investigated,while the basic parameters of gas flow were obtained as functions of radius at the nozzle exit.The effect of the nozzle geometry on the swirling separation was analyzed.The numerical results show that water and heavy hydrocarbons can be condensed and separated from natural gas under the combined effect of the low temperature（-80℃） and the centrifugal field（482,400g,g is the acceleration of gravity）.The gas dynamic parameters are uniformly distributed correspondingly in the radial central region of the channel,for example the distribution range of the static temperature and the centrifugal acceleration are from -80 to -55℃and 220,000g to 500,000g,respectively,which would create good conditions for the cyclone separation of the liquids.However,high gradients of gas dynamic parameters near the channel walls may impair the process of separation.The geometry of the nozzle has a great influence on the separation performance. Increasing the nozzle convergent angle can improve the separation efficiency.The swirling natural gas can be well separated when the divergent angle takes values from 4°to 12°in the convergent-divergent nozzle.

一种旋流+膜联合油水分离器流场数值模拟

相对于单原理油水分离方法而言,利用旋流+膜联合原理进行油水分离是一种新的油水分离方式。为提高井下油水分离性能,探讨一种联合原理的油水分离器。建立旋流+膜联合油水分离器的物理数学模型,并用数值模拟的方法计算其中的流场分布规律,针对不同分流比、入口流速和入口含油体积分数对其性能进行系统研究。结果表明:分流比的变化影响第一级和第二级出油口相汇流动规律,应用时应进行性能核算从而保证两级分离的效果;随着入口流速的增大,旋流+膜分离性能逐渐更优,若流速过低,则旋流+膜分离性能较差;随着入口含油体积分数增大,旋流所分离的油相占比减小,留给膜分离的油相占比增大,即含油体积分数较大时,旋流+膜联合油水分离的应用更有必要。

基于“旋流+亲油疏水膜”工艺的井下油水分离实验研究

文中综合旋流+膜分离技术于一体,设计了一种井下“旋流+亲油疏水膜”分离装置。对这种装置进行了样机实验和相关性能研究,确定了膜的最优结构形式、膜与旋流复合的最优形式。研究结果表明:当将亲油疏水膜与旋流耦合时,膜外不用安装罩时油水分离效果更优;当将旋流油水分离的出油口与膜分离后的出油口连接在一起时,在出水口分流比较小时膜的存在对于促进油水分离效果较明显,出水口分流比较大时膜对于促进油水分离效果较不明显。

WEAKLY SWIRLING TURBULENT FLOW IN TURBID WATER HYDRAULIC SEPARATION DEVICE

This article deals with the characteristics of weakly swirling turbulent flow field in a Turbid Water Hydraulic Separation Device （TWHSD） through experimental and numerical researches. The flow field was measured by PIV, which provided streamlines, vortex structure, vorticity and velocity distribution in different test planes in the TWHSD. On the basis of the experimental results, the tangential and radial velocity distributions of the swirling flow field were obtained. Meanwhile, the numerical simulations were conducted with the RNG κ-ε and RSM turbulence models, respectively. According to the experimental and numerical results, the characteristics of the clear water flow field inside the TWHSD were determined. In view of simulation accuracy and time consumption, it is suggested to apply the RNG κ-ε model instead of the RSM model, which is more time consuming, to make further study on two-phases flow fields in the device.

Mechanism of Affecting the Performance and Stability of an Axial Flow Compressor with Inlet Distortion

The purpose of the investigation is to obtain the mechanism of affecting the performance and stability of an axial flow compressor with two kinds of multi distortion area.In the investigation,the compressor inlet distortion is made by the distortion generator,which is a column and is placed in the compressor rotor passage upstream.The five-passages unsteady numerical results show that the compressor performances for two kinds of multi distortion area are both lower than that for the clean inlet,and the compressor peak efficiencies for inlet distortions of 6×12 degrees and 6×24 degrees are about 3.5%,and 9.2%lower than that for the clean inlet,respectively.Further,two kinds of multi distortion area both reduce the compressor stability,and the stall margin improvements of–2.93%and–6.11%are provided by inlet distortions of 6×12 degrees and 6×24 degrees,respectively.The flow field analyses show that the flow conditions of the rotor tip inlet upstream deteriorate after the application of multi distortion area.The values of axial velocity and flow angle of incoming flows in some regions,which are near the shroud,become small due to the adverse effect made by the inlet distortion.So,the circulation capacity of the regions becomes low,and inlet blockages appear in some rotor tip passages.The bigger the distorted range is,the greater inlet blockages and corresponding flow losses are.When multi distortion area changes from 6×12 degrees to 6×24 degrees,there are obvious separations of the boundary layer near the blade suction surface in some blade tip passages,and the serious separations prevent the incoming flows from entering the blade tip passage.As a result,overflows occur at the leading edge of the blade tip.Furthermore,as the number of the distortion generator increases by a factor of one,the effects of inlet distortion on the amplitudes of the air relative velocity and static pressure in the rotor inlet upstream at the distortion generator passing frequency of 1076.5 Hz increase by a factor of about one.

Numerical Study on Particle Motions in Swirling Flows in a Cyclone Separator

The purpose of this study is to establish the high-accurate prediction method of particle separation in a cyclone separator. Numerical simulation of the swirling flows in a cyclone separator is performed by using a large eddy simulation （LES） based on a Smagorinsky model. The validity of the simulation and the complicated flow characteristics are discussed by comparison with experimental results. Moreover, particle motions are treated by a Lagrangian method and are calculated with a one-way method. A performance for particle separation is predicted from the results of the particle tracing. As results of our investigation, the influences of the inserted height of the outlet pipe on the performance for particle separation of cyclone separator are shown.

Coupling Effect between Inlet Distortion Vortex and Fan

In the process of inlet/engine matching,large-scale distortion vortexes would be generated due to lip separation,curved duct,shock-wave boundary layer interaction and other factors of inlet,resulting in complex combination distortion of total pressure and swirl,which would affect the stable and efficient operation of fans/compressors of aero-engine.On the basis of main distortion vortex characteristics of a typical S-shape inlet and its theoretical model of velocity and pressure distribution,this paper establishes an inlet boundary condition definition method to generate three-dimensional distortion vortex,and presents a study of coupling effect between steady distortion vortex and NASA Rotor 67.The results show that the fan’s performance curve would move to smaller mass flow direction under the influence of the co-rotating distortion vortex,while fan’s operation curve would change to the opposite direction if the inlet distortion vortex direction is opposite to the fan’s rotating direction.Compared with co-rotating distortion vortex,the efficiency loss caused by counter-rotating distortion vortex would be larger and total pressure ratio loss would be smaller.The vortex core size has significant influence on the stability margin of the fan,but has little influence on the efficiency and total pressure ratio characteristic.As the vortex core size increases,the range of fan’s tip region with high attack angle would become larger and cause the fan to stall in advance.Due to the non-uniform suction of the downstream fan,the inlet distortion vortex accelerates to mix with the surrounding main flow.The total pressure distortion decreases and swirl distortion increases along sections from inlet boundary to the fan leading edge.

交流介质阻挡放电等离子体主动控制S形进气道流动分离的实验研究

S形进气道内的流动分离和二次流造成进气道出口压力损失和气流畸变较为严重,严重影响发动机的工作性能。为改善其流场特性,采用交流介质阻挡放电(Alternating current dielectric barrier discharge,AC-DBD)等离子体激励器主动控制进气道内的流场。在来流风速为10m/s,雷诺数ReD为1.35×10^(5)的工况下,探究了控制位置、布局形式对控制效果的作用规律,从流向和出口截面流场及压力分布出发,探究了主动控制的机理。结果表明,AC-DBD等离子体激励器能够提高壁面静压恢复系数,抑制流动分离并改善出口压力畸变。激励器控制位置在分离点附近最佳,且以诱导气流与来流平行的布局形式最优。在本实验范围内,出口静压系数提高了8.94%,出口稳态畸变指数降低了4.58%。其控制机理是DBD等离子体产生的诱导气流直接加速边界层运动,提高边界层抵抗逆压梯度的能力,从而抑制流动分离。同时,抑制二次流运动,降低压力畸变。

FPSO油-水旋流分离器模拟分析及应用研究

旋流分离器因其紧凑高效在海上平台污水处理单元中被广泛应用。基于巴西某海上油田的污水实况,根据该油田FPSO的污水处理工艺及设计特点,通过对比分析常见的几种含油污水处理方法,并运用FLUENT软件,建立油-水旋流器几何模型,研究旋流分离器内部流场分布特性,综合分析分离性能随来液流速的变化规律。根据运行工况,当旋流器入口流速为3 m/s时,分离效率低于70%,分离效果不理想;当入口流速为7 m/s时,分离效率高于90%,分离后污水含油质量浓度低于100 mg/L。流速过高时,分离效率下降,这是由于流速过大,导致油滴破裂,甚至加剧乳化。这一规律可为今后海上平台污水处理工艺设计提供参考。在实际运用时,应根据油田污水性质、实际环境要求、油滴变形破裂及能耗,选择合适的处理工艺及最优的入口流速。

旋转流动态特性分析的数据处理方法

本文以旋风分离器内的旋转流为研究对象,基于热线风速仪测量的流场瞬时切向速度数据,探讨旋风分离器内旋转流的动态参量可行的数据分析方法。对测量数据进行定性、定量的数据处理,从时域和频域两方面展开分析,得到了旋转流动态特性与时频特性间的关系,为定量描述旋转流动态特性提供一定参考。

Effects of Bending-torsional Duct-induced Swirl Distortion on Aerodynamic Performance of a Centrifugal Compressor

A turbocharger compressor working in commercial vehicles, especially in some passenger cars, often works together with some pipes with complicated geometry as an air intake system, due to limit of available space in internal combustion engine compartments. These pipes may generate various distortions of physical parameters of the air at the inlet of the compressor and therefore the compressor aerodynamic performance deteriorates. Sometimes, the turbocharging engine fails to work at some operation points. This paper investigates the effects of various swirl distortions induced by different bending-torsional intake ducts on the aerodynamic performance of a turbocharger compressor by both 3D numerical simulations and experimental measurements. It was found that at the outlet of the pipes the different inlet ducts can generate different swirl distortions, twin vortices and bulk-like vortices with different rotating directions. Among them, the bulk-like vortices not only affect seriously the pressure distribution in the impeller domain, but also significantly deteriorate the compressor performance, especially at high flow rate region. And the rotating direction of the bulk-like vortices is also closely associated with the efficiency penalty. Besides the efficiency, the transient flow rate through a single impeller channel, or the asymmetric mass flow crossing the whole impeller, can be influenced by two disturbances. One is from the upstream bending-torsional ducts; other one is from the downstream volute.

旋风分离器自然旋风长的试验研究

采用激光多普勒测速系统(LDV)对φ300mm、升气管直径为De=100、135和180mm的旋风分离器内气相流场进行了测量,主要分析了旋风分离器的自然旋风长。测量结果表明,旋风分离器内的旋转流呈现明显的衰减特性。沿升气管出口轴向向下,切向速度和轴向速度逐渐减小,对于直径100mm升气管,最大切向速度由2.55Vi开始衰减,并且最大切向速度的径向位置由0.28R逐渐向壁面移动,内部的刚性涡逐渐扩大,外部的准自由涡逐渐缩小,最终在轴向5.2D处最大切向速度点接近筒体壁面,准自由涡消失,此位置以下形成完全的刚性涡;对于直径135和180mm升气管,最大切向速度的值和位置也具有相似的变化。在此基础上,提出了旋风分离器自然旋风长的定义,即从升气管下口到准自由涡消失位置的距离为旋风分离器的自然旋风长Lc,依据实验结果给出了计算式(5)的关系式。最后通过分析旋风分离器内旋转流的衰减特性和两涡之间的能量传递过程,进一步说明了旋风分离器自然旋风长的物理意义。

超声速旋流天然气分离器的旋流特性数值模拟

与传统的低温分离工艺相比,超声速旋流天然气分离器是天然气处理工艺技术的一大创新。在超声速旋流天然气分离器中,气流经过拉伐尔喷管绝热膨胀形成带液滴的超声速低温混合气流,在超声速翼的作用下混合气流由轴流转换成旋流,实现超声速旋流分离。超声速翼是实现气液分离的关键部件。设计了三角薄板型超声速翼,并利用CFD软件对超声速翼段内气流温度、压力、马赫数等特性参数的变化规律和翼段沿主流方向切向速度的变化情况进行了分析。结果表明,在所设计的超声速翼段内,气流能始终保持超声速,翼段出口马赫数为1.4,翼前无激波产生;分离器的旋流加速度最高在572000g,可实现良好的超声速气液旋流分离。

基于旋流的天然气超声速喷管分离特性

采用数值模拟方法研究来流为旋流的拉伐尔喷管内的流场,考察了喷管的收缩比、收缩半角、喉部圆柱段长度和扩张半角对天然气超声速喷管旋流分离性能的影响。数值计算结果表明,增加喷管收缩比和收缩半角可以提高喷管旋流分离性能。喷管喉部圆柱段长度对喷管旋流分离性能影响较小。当喷管扩张半角小于2°时,喷管旋流分离性能较差;扩张半角在2-6°时,喷管旋流分离性能较好;继续增加扩张半角,喷管旋流分离性能下降。