A Lagrangian criterion of unsteady flow separation for two-dimensional periodic flows

The present paper proposes a Lagrangian criterion of unsteady flow separation for two-dimensional periodic flows based on the principle of weighted averaging zero skin-friction given by Haller （HALLER, G. Exact theory of unsteady separation for two-dimensional flows. Journal of Fluid Mechanics, 512, 257-311 （2004））. By analyzing the distribution of the finite-time Lyapunov exponent （FTLE） along the no-slip wall, it can be found that the periodic separation takes place at the point of the zero FTLE. This new criterion is verified with an analytical solution of the separation bubble and a numerical simulation of lid-driven cavity flows.

Unsteady Flow Separation and High Performance of Airfoil with Local Flexible Structure at Low Reynolds Number

The unsteady flow separation of airfoil with a local flexible structure(LFS)is studied numerically in Lagrangian frames in detail,in order to investigate the nature of its high aerodynamic performance.For such aeroelastic system,the characteristicbased split(CBS)scheme combined with arbitrary Lagrangian-Eulerian(ALE)framework is developed firstly for the numerical analysis of unsteady flow,and Galerkin method is used to approach the flexible structure.The local flexible skin of airfoil,which can lead to self-induced oscillations,is considered as unsteady perturbation to the flow.Then,the ensuing high aerodynamic performances and complex unsteady flow separation at low Reynolds number are studied by Lagrangian coherent structures(LCSs).The results show that the LFS has a significant influence on the unsteady flow separation,which is the key point for the lift enhancement.Specifically,the oscillations of the LFS can induce the generations of moving separation and vortex,which can enhance the kinetic energy transport from main flow to the boundary layer.The results could give a deep understand of the dynamics in unsteady flow separation and flow control for the flow over airfoil.

THE EVOLUTION OF STARTING VORTEX AND SECONDARY SEPARATION ON AN ELLIPTIC CYLINDER

Flow visualization was used to investigate experimentally the evolution process from symmetrical shedding to staggered shedding of the starting vortex and the phenomenon of secondary separation on an elliptic cylinder at moderate Reynolds numbers.The vortex structure of the flow separation was studied.The temporal variation of separation angle and length of wake vortex were given. The photographs and experimental results provided basis for further investigation of the complicated feature of the starting process of unsteady separated flows around an elliptic cylinder.

Numerical study on the separation and superposition of the influences from up-and downstream rotors

A three-dimensional Navier-Stokes solver is used to investigate the separation and superposition of the influences from upstream and downstream rotors in an axial-radial combined compressor for unsteady design applications. The data from rotor/stator and stator/rotor configurations show that the unsteady flow response in axial stator passage is caused only by one rotor. The results from the rotor/stator/rotor configuration revealed the superimposed characteristic of influences from upstream and downstream the rotor. The impact of the superimposed characteristic was studied by analyzing the virtual relative flow angle at the stator exit. The results show that the axial velocity in the passage of axial stator can be influenced by wake from upstream axial rotor and potential field of downstream radial rotor. While they are coupled to have an effect on the unsteady flow in axial statot passage, the excitation or suppression phenomena appear and lead to different levels of deterministic fluctuation kinetic energy. Their locations are determined by the frequencies of the involved influences. In addition, the variability of superimposed characteristic （ excitation and suppression） at the stator exit modulates the inlet flow angle for downstream rotor.

A modified VLES model for simulation of rotating separation flow in axial flow rotating machinery

The internal flow in an axial flow rotating machinery is affected by the rotating characteristics, often accompanied by a strong rotating separation under small flow conditions. At present, the very large eddy simulation (VLES) model commonly used for the separation flow simulation still has certain limitations in simulating such rotating separation flow: (1) The Reynolds stress level is overestimated in the near-wall region. (2) The influence of the rotating effect cannot be effectively considered. The above two limitations affect the simulation accuracy of the VLES model for the rotating separation flow under small flow conditions in the axial flow rotating machinery. The objective of this paper is to provide a new hybrid unsteady Reynolds average Navier-Stokes/large eddy simulation (URANS/LES) model suitable for the simulation of the rotating separation flow in an axial flow rotating machinery. Compared with the original VLES method, the modifications are as follows: (1) A Reynolds stress damping function in the near-wall region is introduced to reduce the overestimation of the Reynolds stress caused by the near-wall Reynolds average Navier-Stokes (RANS) behavior of the VLES model. (2) A control function driven by the vortex is introduced to reflect the influence of the rotating effect. Three typical cases are used to verify the calculation accuracy of the modified model. It is shown that the modified model can capture more turbulent vortices based on the URANS grids, and the prediction accuracy of the rotating separation flow is effectively improved. Compared with the original VLES model, the modified model can accurately predict the head change in the hump region of the axial flow pump.

Aerodynamic characteristics of store during lateral jet assisted separation from cavity using free drop technique

Aimed at the problem of store separation from internal cavity,this paper innovatively puts forward a separation scheme of using lateral jet to assist store safe separation.The jet ensures that the store is continuously subjected to down head moment during separation,so as to ensure safe separation.The wind tunnel free drop test technique with lateral jet is established,which can ensure that there is no support interference in the motion process of the store and more truly simulate the motion of the store.The feasibility of the new separation scheme is proved by wind tunnel test.The test shows that the new scheme can also change the more dangerous state into a safe state.Through the analysis of the test data,the pitching moment coefficients of the store under different pressures in the high-pressure cylinder are obtained,and the effects of aircraft and cavity on the pitching moment of the store are obtained.The 3 stages of store passing through cavity shock wave are found.The results show that the lateral jet provides the store with continuous head down moment,and makes the store overcome the head up moment caused by the shock wave in front of the cavity,so as to ensure the safety of separation.

Frequency Analyses for Mechanism Research of Unsteady Flow Inside Three Dimensional Compressor Cascade

Numerical simulations are carried out for unsteady flow field of certain kind of 3D compressor cascade. Emphasis is laid on vortex shedding and frequency analysis in a compressor cascade. Numerical simulations using unsteady Reynolds-averaged viscous turbulent equations are carried out. The results show that the flows in separated areas and wake areas are characterized as periodic or quasi-periodic vortex shedding and the frequencies of vortex shedding vary with incidences and Mach number. At the same Mach number, the frequency of vortex shedding will decrease as the incidence increases. Yet, the frequency will increase as the Mach number increases at the same incidence. In the same computation case, the frequency of vortex shedding will vary along the span of blade. The frequency is smaller at the middle of the span than that at the hub.

NUMERICAL SOLUTION OF NAVIER-STOKES EQUATION OF UNSTEADY SEPARATED FLOWS DUE TO A SPOILER'S OSCILLATION

The finite difference method (FDM) is applied in the present paper to solve the unsteady NHS equations for incompressible fluids. ADI and SLOR methods are served for the vorticity equation and the Poisson equation for ψ respectively. The upwind scheme is used for the convective terms. The moving boundary conditions are specially treated, and the effects of outlet conditions on the flow field are abo examined. Numerical results obtained show that the spoiler's oscillation induces forming, growing and shedding of the vortices. The shedding frequency of vortices is equal to that of the spoiler's oscillation. The forced unsteady separated flows under the present investigation depend mainly on the reduced frequency. At low reduced frequency, the vortices shed from the spoiler interact weakly with each other, and move downstream at an almost uniform speed of 038 V∞. At high reduced frequency, the interaction between the adjacent vortices strengthens. They close up to and rotate around each other, and eventually, merge into one vortex.

Numerical simulation of unsteady interaction of centrifugal impeller with its diffuser using Lagrangian discrete vortex method

In this study, an advanced Lagrangian vortex- boundary element method is applied to simulate the unsteady impeller-diffuser interactions in a diffuser pump not only for design but also for off-design considerations. In velocity calculations based on the Biot-Savart law we do not have to grid large portions of the flow field and the calculation points are concentrated in the regions where vorticity is present. Lagrangian representation of the evolving vorticity field is well suited to moving boundaries. An integral pressure equation shows that the pressure distribution can be estimated directly from the instantaneous velocity and vorticity field. The numerical results are compared with the experimental data and the comparisons show that the method used in this study can provide us insight into the complicated unsteady impeller-diffuser interaction phenomena in a diffuser pump.

井下旋流分离管柱的振动特性研究

为研究旋流分离管柱在注入泵和采出泵两螺杆泵抽吸条件下的振动特性,对其进行模态分析和瞬态动力响应分析。结果表明,不同工况下,旋流分离管柱的固有频率有所不同;固定注入泵一端和固定采出泵一端相比,固定采出泵一端各阶固有频率较小;螺杆泵转动引起的激振力和内部流量变化都会导致管柱变形,其中螺杆泵转动对旋流分离管柱变形影响较大;相对于固定采出泵,固定注入泵条件下旋流分离管柱产生的振动位移更大,是旋流分离管柱自身结构和注入泵转速产生更大激振力综合作用导致的结果;控制两个螺杆泵工作状态的时间差,理想情况下可以控制旋流分离管柱的总变形。

级联式气-液旋流分离器流动特性数值研究

为探究级联式气-液旋流分离器流场特性,了解短路流这一特殊流型对其性能影响,采用雷诺应力模型和离散颗粒模型对气、液两相流动特征进行数值模拟,通过Q准则对涡流特征进行识别。研究结果表明,级联式气-液旋流分离器一级旋流管内流动特性与传统旋流分离器相似,增加二级旋流管使级联式气-液旋流分离器内形成了大量的局部二次涡流。当入口气速为7 m/s时,级联式气-液旋流分离器中一级旋流区内短路流流量高达入口流量的70.28%;增设二级旋流管对改善分离器性能具有重要作用,两级分离后级联式气-液旋流分离器对直径6μm以上的液滴能够实现完全分离。本研究为气-液旋流分离器的结构开发和级联式气-液旋流分离器的应用提供了思路和基础数据。

双吸泵作液力透平叶轮内非定常流动DMD分析

为了精确分析双吸泵作液力透平叶轮内的非定常流动特性,采用SST k-ω湍流模型在设计工况下进行数值模拟。对一个周期的非定常速度场进行动态模态分解(DMD),并结合Q准则,得到前4阶主要模态及其相应的时空信息。分析结果表明:DMD方法将叶轮内复杂的流场特征分解为动静干扰模态、基本模态和耗散模态。其中动静干扰模态占主导地位,频率为叶轮旋转频率,反映出叶轮内流动受静止部件干扰的流动特征,涡结构主要为点状涡和不连续的管状涡;基本模态频率为0Hz,反映出叶片流道几何特征引起的稳态流场特征,涡结构主要为连续的管状涡;3阶及4阶模态为耗散模态,反映出叶轮内流动受静止部件干扰,在叶片上产生的流动分离及不稳定涡结构脱落的特征,以片状涡和不连续的管状涡为主。在特定频率下DMD方法可以对叶轮流场结构进行分解,能够清楚地分析双吸泵作液力透平叶轮内复杂流场的非定常特性。

翼型流动分离的EnKF非稳态数据同化

为了改善RANS模型对流动分离现象的预测性能,针对NACA0012翼型绕流,采用基于非稳态计算的集合Kalman滤波(ensemble Kalman filter,EnKF)数据同化方法,结合粒子图像测速(particle image velocimetry,PIV)数据对SST湍流模型的模型常数进行了修正,对比分析了不同模型常数扰动幅度、不同集合样本数目下稳态数据同化和非稳态数据同化的预测结果差异。研究结果表明,相对于稳态计算,非稳态计算能够增强数值模拟的稳健性,从而可以在较大的扰动幅度下,改善RANS模型的初始预测分布。稳态数据同化在模型常数扰动幅度较大或者样本数目较少时存在明显缺陷,非稳态的数据同化具有更好的鲁棒性,能够在更大扰动幅度和更少样本数下得到最优的湍流模型常数,对流场的预测更加准确。

风力机翼型S809绕流流动特性的POD和DMD对比分析

失速时的流动分离现象对风力机叶片的气动性能有重要影响,S809作为典型水平轴风力机翼型,在临界失速攻角下气动性能会大幅降低。基于流动特征提取的非定常流场降阶模型(reduced-order model,ROM)是进一步深入了解非定常流动的重要手段。本文通过计算流体力学方法得到轻、深失速攻角下翼型的流动特征,对时变速度场进行本征正交分解(proper orthogonal decomposition,POD)和动态模态分解(dynamic mode decomposition,DMD)分析,得到轻、深失速下翼型的非定常流场信息(能量占比、模态频率等)。通过两种方法的对比,结果表明,POD和DMD方法能够准确捕捉流动过程中的非定常结构和升力主频相同的典型模态,但是POD方法由于基于能量特征,在捕捉模态时会忽略与升力主频相近但能量较小的流动结构,而基于频率特征的DMD方法能够准确获得场的演化信息(增长率、频率等)。本文研究有利于针对主频结构发展相应的流动控制方法,从而改善翼型流场情况,提高气动性能。

Turbine Blade Boundary Layer Separation Suppression via Synthetic Jet: an Experimental and Numerical Study

The present paper focuses on the analysis of a synthetic jet device (with a zero net massflow rate) on a separated boundary layer. Separation has been obtained on a flat plate installed within a converging-diverging test section specifically designed to attain a local velocity distribution typical of a high-lift LPT blade. Both experimental and numerical investigations have been carried out. Unsteady RANS results have been compared with experiments in terms of time-averaged velocity and turbulence intensity distributions. Two different Reynolds number cases have been investigated, namely Re = 200,000 and Re = 70,000, which characterize low-pressure turbine operating conditions during take-off/landing and cruise. A range of synthetic jet aerodynamic parameters (Strouhal number and blowing ratio) has been tested in order to analyze the features of control-separated boundary layer interaction for the aforementioned Reynolds numbers.

零间隙压气机失稳机理的全通道数值模拟研究

为了探究零间隙压气机流动失稳机理,采用全通道非定常数值模拟方法研究了一台零间隙斜流压气机转子的失稳机理,数值模拟过程中在转子出口施加了随时间动态变化的背压模拟压气机转子节流,非定常数值计算结果表明零间隙斜流压气机转子仍然表现为典型突尖流动失稳特征。通过详细地分析斜流压气机转子节流过程中不同阀系数对应的压气机内部流场结构,结果表明:尽管零间隙斜流压气机无叶顶泄漏特征,但随着对压气机节流,转子叶片尾缘率先出现流动分离,进一步节流,尾缘流动分离表现为一方面在周向范围加剧,另一方面分离点逐渐向上游移动,造成通道严重堵塞,最终引发相邻叶片通道尾缘回流和叶片前缘流动溢出进而诱发叶片通道内部出现径向涡结构,从而形成压气机突尖失速先兆。

STUDY ON FORCED SHEAR FLOW BY A OSCILLATING SPOILER

In the present paper,numerical solution of the two-dimensional unsteady Navier-Stokes equations is used to study the forced shear flow induced by a spoiler's periodical up and down oscillation on a flat plate.The paper studies the evolution of growing,shedding,merging and decaying of vortices due to the spoiler's oscillation,particularly the dependence of the forced shear flow on the re- duced frequency.Results show that the reduced frequency is a key factor in controlling the growing and the shedding of vortices in the shear layer.The instantaneous streamlines and the equi-vorticity con- tours,as well as the surface pressure distributions,have also been investigated.Numerical results agree well with corresponding experimental ones.The study is helpful for understanding the physical mecha- nism of shear flow control.

NATURE OF THE SURFACE HEAT TRANSFER FLUCTUATION IN A HYPERSONIC SEPARATED TURBULENT FLOW

This paper presents the results of an experimental study of the unsteady nature of a hypersonic sepa- rated turbulent flow.The nominal test conditions were a freestream Mach number of 7.8 and a unit Reynolds number of 3.5x10^7/m.The separated flow was generated using finite span forward facing steps.An array of flush mounted high spatial resolution and fast response platinum film resistance thermometers was used to make mul- ti-channel measurements of the fluctuating surface heat trtansfer within the separated flow.Conditional sampling ana- lysis of the signals shows that the root of separation shock wave consists of a series of compression wave extending over a streamwise length about one half of the incoming boundary layer thickness.The compression waves con- verge into a single leading shock beyond the boundary layer.The shock structure is unsteady and undergoes large-scale motion in the streamwise direction.The length scale of the motion is about 22 percent of the upstream influence length of the separation shock wave.There exists a wide band of frequency of oscillations of the shock system.Most of the frequencies are in the range of 1-3 kHz.The heat transfer fluctuates intermittently between the undisturbed level and the disturbed level within the range of motion of the separation shock wave.This inter mittent phenomenon is considered as the consequence of the large-scale shock system oscillations.Downstream of the range of shock wave motion there is a separated region where the flow experiences continuous compression and no intermittency phenomenon is observed.

TSTO级间分离气动特性数值仿真分析

两级入轨(TSTO)重复使用飞行器并联级间分离是一二级飞行器设计必须考虑的关键因素。采用国家数值风洞工程通用CFD软件NNW-FlowStar,基于各向异性非结构混合网格及重叠网格技术,研究了TSTO在侧滑角下的并联级间分离过程。软件通过自主改进的Roe熵修正方法、节点高斯梯度算法实现高超声速流场的精细模拟,运用“物面相交”准则实现多套网格间的并行挖洞。采用双时间步求解非定常分离过程,内迭代计算采用LU-SGS方法。文中首先采用WPFS投放标模验证了软件在常规分离投放方面的数值模拟精度;然后模拟获得TSTO组合体定常气动特性,分析了不同攻角下一二级的气动特性以及可能的安全分离状态;最后数值模拟了TSTO在负攻角、正侧滑角下的并联级间分离过程,与对应的CTS试验结果比较,两级质心位移的计算值和实验值随时间变化具有很好的一致性,偏航角及俯仰角在变化规律和量值上比较吻合,表明软件具备升力体并联级间分离类问题的数值模拟能力。

低雷诺数下翼型表面局部振动控制研究

数值模拟研究了Re=4×10^(4)时小迎角下表面局部振动激励对SD8020翼型气动特性的影响,从时均化和非定常流动两个方面分析了频率和幅值两个振动激励参数对于翼型分离和转捩特性的作用。结果表明,迎角2°和3°时局部振动激励能够有效对流场施加影响,促进层流分离泡结构的转变,改善翼型的气动性能。同时研究发现,振动频率在不同迎角下对翼型气动特性和流场结构的影响规律类似,频率f=32 Hz时气动性能提升最明显;而随着振动幅值的增加,层流分离泡长度减小且整体向前缘移动。进一步非定常分析表明,迎角2°和3°时流场在同一振动激励参数下表现出相似的非定常涡演化过程,弦向位置的压力脉动频率与振动激励频率一致,此时流场的非定常流动特征由振动激励主导。