Numerical simulation of flow around square cylinder using different low-Reynolds number turbulence models

ABE-KONDOH-NAGANO,ABID,YANG-SHIH and LAUNDER-SHARMA low-Reynolds number turbulence models were applied to simulating unsteady turbulence flow around a square cylinder in different phases flow field and time-averaged unsteady flow field.Meanwhile,drag and lift coefficients of the four different low-Reynolds number turbulence models were analyzed.The simulated results of YANG-SHIH model are close to the large eddy simulation results and experimental results,and they are significantly better than those of ABE-KONDOH-NAGANO,ABID and LAUNDER-SHARMR models.The modification of the generation of turbulence kinetic energy is the key factor to a successful simulation for YANG-SHIH model,while the correction of the turbulence near the wall has minor influence on the simulation results.For ABE-KONDOH-NAGANO,ABID and LAUNDER-SHARMA models satisfactory simulation results cannot be obtained due to lack of the modification of the generation of turbulence kinetic energy.With the joint force of wall function and the turbulence models with the adoption of corrected swirl stream,flow around a square cylinder can be fully simulated with less grids by the near-wall.

Laminar-to-Turbulence Transition Revealed Through a Reynolds Number Equivalence

Flow transition from laminar to turbulent mode (and vice versa)—that is, the initiation of turbulence—is one of the most important research subjects in the history of engineering. Even for pipe flow, predicting the onset of turbulence requires sophisticated instrumentation and/or direct numerical simulation, based on observing the instantaneous flow structure formation and evolution. In this work, a local Reynolds number equivalence c (ratio of local inertia effect to viscous effect) is seen to conform to the Universal Law of the Wall, where c = 1 represents a quantitative balance between the abovementioned two effects. This coincides with the wall layer thickness (y+= 1, where y+ is the dimensionless distance from the wall surface defined in the Universal Law of the Wall). It is found that the characteristic of how the local derivative of c against the local velocity changes with increasing velocity determines the onset of turbulence. For pipe flow, c - 25, and for plate flow, c - 151.5. These findings suggest that a certain combination of c and velocity (nonlinearity) can qualify the source of turbulence (i.e., generate turbulent energy). Similarly, a re-evaluation of the previous findings reveals that only the geometrically narrow domain can act locally as the source of turbulence, with the rest of the flow field largely being left for transporting and dissipating. This understanding will have an impact on the future large-scale modeling of turbulence.

Effects of the Reynolds number on a scale-similarity model of Lagrangian velocity correlations in isotropic turbulent flows

A scale-similarity model of a two-point two-time Lagrangian velocity correlation(LVC) was originally developed for the relative dispersion of tracer particles in isotropic turbulent flows(HE, G. W., JIN, G. D., and ZHAO, X. Scale-similarity model for Lagrangian velocity correlations in isotropic and stationary turbulence. Physical Review E, 80, 066313(2009)). The model can be expressed as a two-point Eulerian space correlation and the dispersion velocity V. The dispersion velocity denotes the rate at which one moving particle departs from another fixed particle. This paper numerically validates the robustness of the scale-similarity model at high Taylor micro-scale Reynolds numbers up to 373, which are much higher than the original values(R_λ = 66, 102). The effect of the Reynolds number on the dispersion velocity in the scale-similarity model is carefully investigated. The results show that the scale-similarity model is more accurate at higher Reynolds numbers because the two-point Lagrangian velocity correlations with different initial spatial separations collapse into a universal form compared with a combination of the initial separation and the temporal separation via the dispersion velocity.Moreover, the dispersion velocity V normalized by the Kolmogorov velocity V_η ≡ η/τ_η in which η and τ_η are the Kolmogorov space and time scales, respectively, scales with the Reynolds number R_λ as V/V_η ∝ R_λ^(1.39) obtained from the numerical data.

Stochastic modeling of subgrid-scale effects on particle motion in forced isotropic turbulence

The subgrid-scale effects on particle motion were investigated in forced isotropic turbulence by DNS and priorLES methods.In the DNS field,the importance of Kolmogorov scaling to preferential accumulation was validated by comparing the radial distribution functions under various particle Stokes numbers.The prior-LES fields were generated by filtering the DNS data.The subgrid-scale Stokes number(StSGS)is a useful tool for determining the effects of subgrid-scale eddies on particle motion.The subgrid-scale eddies tend to accumulate particles with StSGSb 1 and disperse particles with 1 b StSGSb 10.For particles with StSGS?1,the effects of subgrid-scale eddies on particle motion can be neglected.In order to restore the subgrid-scale effects,the Langevin-type stochastic model with optimized parameters was adopted in this study.This model is effective for the particles with StSGS N 1 while has an adverse impact on the particles with StSGSb 1.The results show that the Langevin-type stochastic model tends to smooth the particle distribution in the isotropic turbulence.

Heat Transfer and Flow Characteristics Predictions with a Refined k-ε-f_u Turbulent Model in Impinging Jet

Local heat transfer and flow characteristics in a round turbulent impinging jet for Re≈23 000 is predicted numerically with the RANS approach and a k-ε-fu turbulence model. The heat transfer predictions and turbulence parameters are verified against the axis-symmetric free jet impingement measurements and compared with previous other turbulence models, and results show the k-ε-fu model has a good performance in predictions of the local wall heat transfer coefficient, and in agreement with measurements in mean velocity profiles at different radial positions as well. The numerical model is further used to examine the effect of the fully confined impingement jet on the local Nusselt number. Local Nusselt profiles in x and y-centerlines for the target plate over three separation distances are predicted. Compared with the experimental data, the numerical results are accurate in the central domain around the stagnation region and present a consistent structure distribution.

Second-order modeling of non-premixed turbulent methane-air combustion

The main purpose of this research is the second-order modeling of flow and turbulent heat flux in nonpremixed methane-air combustion.A turbulent stream of non-premixed combustion in a stoichiometric condition,is numerically analyzed through the Reynolds averaged Navier-Stokes(RANS) equations.For modeling radiation and combustion,the discrete ordinates(DO) and eddy dissipation concept model have been applied.The Reynolds stress transport model(RSM) also was used for turbulence modeling.For THF in the energy equation,the GGDH model and high order algebraic model of HOGGDH with simple eddy diffusivity model have been applied.Comparing the numerical results of the SED model(with the turbulent Prandtl 0.85) and the second-order heat flux models with available experimental data follows that applying the second-order models significantly led to the modification of predicting temperature distribution and species mass fraction distribution in the combustion chamber.Calculation of turbulent Prandtl number in the combustion chamber shows that the assumption of Pr_(t) of 0.85 is far from reality and Pr_(t) in different areas varies from 0.4 to 1.2.

On the Wind and Turbulence in the Lower Atmosphere above Complex Terrain

Numerical modeling and studies of the wind fields at the junction of three continents: over the complex terrains of the South-east Europe, Asia Minor, Middle East, Caucasus and over the Black, Caspian and Medi-terranean seas have been carried out for the first time. Traveling synoptic scale vortex wave generation and subsequent evolution of orographic vortices are discovered. Wind fields, spatial distribution of the coefficients of subgrid scale horizontal and vertical turbulence and the Richardson number are calculated. It is shown that the local relief, atmospheric hydrothermodynamics and air-proof tropopause facilitate the generation of β-mesoscale vortex and turbulence amplification in the vicinity of the atmospheric boundary layer and tropopause. Also turbulence parameters distribution in the troposphere has the same nature as in the stratosphere and mesosphere: turbulence coefficients, stratification of the vertical profiles of the Richardson number, thickness of the turbulent and laminar layers.

大雷诺数下对称翼型的转捩判断与规律研究

围绕翼型的转捩问题,以NACA0012、NACA0015、NACA0018三种不同厚度的对称翼型为研究对象,基于TSST湍流模型的数值模拟方法,提出基于湍流强度的转捩判断方法并研究在5种大雷诺数条件下翼型表面流动的转捩规律,以期为风力机叶片设计提供新的参考思路。研究表明,基于湍流强度的转捩判断方法是有效、可行的,使用翼型表面湍流强度曲线的阶跃现象观测转捩,可有效避免转捩前流动扰动带来的影响。同时利用湍流强度的变化情况可为风力机叶片设计寻找最佳设计参数。研究发现,增大攻角和雷诺数使得翼型上翼面转捩位置前移、下翼面转捩位置后移。此外,随着攻角的减小、雷诺数的增大、翼型表面厚度的增加,在翼型转捩前的流动逐渐稳定。

基于物理信息神经网络的气膜冷却湍流模型反演学习

由于气膜冷却问题中湍流的复杂特性,传统雷诺平均(RANS)方法会低估湍流的热扩散强度,导致冷却效果计算不准确。对此提出了一套基于物理信息神经网络(PINN)的湍流建模框架,基于RANS流场和大涡模拟(LES)温度场,建立了数据驱动的湍流普朗特数神经网络模型,在RANS求解器中嵌入该模型,可以动态调整湍流的热扩散强度,获得了与LES高度一致的温度场。结果表明:PINN是构建数据驱动湍流模型的良好方法,对于湍流普朗特数的建模可以有效提升RANS方法对温度预测的准确性。

棒束结构气冷换热的湍流模型适用性评价

高功率空间核电源采用棒束气冷堆具有质量轻等优势,其紧凑的栅格结构以及流动雷诺数(Re)较低的特点会影响堆芯的流动换热规律,采用CFD开展数值分析时需评价湍流模型的适用性。在气体工质棒束结构流动换热实验的基础上,利用ANSYS Fluent建立了试验段的数值模型,针对入口Re在688~2 986之间的实验工况,选择4种湍流模型开展了数值模拟,对比了加热棒包壳温度实验测量值与计算值。结果表明,4种湍流模型计算的棒温整体上均低于实验值,其中转捩SST模型结果与实验值最接近,整体平均偏差为-2.0%,较好地反映了横流等特征,可用于Re在2 000左右的棒束气冷堆芯热工水力数值计算。

Numerical simulation of stratified turbulent two-phase flow in aquatic environment

The two fluid model of stratified turbulent two phase flow in aquatic environment is developed in this paper. The motion of each phase is described by a unified multi fluid model in an Eulerian coordinate system. The laws of turbulent transportation for each phase, and the restriction of each other between the two phases are completely simulated. The complex two phase turbulence with strong buoyancy effects is selected to examine numerically. The extensive experimental data obtained in stratified flow are used here. Comparison of the results of numerical simulation with the experimental data is conducted. It has shown that the results of numerical simulation are satisfactory.

Numerical Simulation of Aspect Ratio Effect on Turbulent Annular Flows

The control of energy in various industrial applications passes by the comprehension of the phenomena of transfers especially in complex flows. The structure of the turbulent flow in the cavities in rotation depends on several parameters like the Reynolds number of rotation Ra and the aspect ratio of the cavity. The purpose of this work is to simulate numerically the effect of the aspect ratio on the level of turbulence in the annular steady flow with an incompressible fluid for three different configurations. In the first, the interior cylinder is fixed and the external is moving. The second configuration is the reverse. The third is the contra-rotating cylinders. For all these configurations, we varied the aspect ratio from 0.5 to 2.5. The numerical tool is based on a statistical model in a point using the closing of the second order of the transport equations of the Reynolds stresses （Reynolds Stress Model： RSM）. The results of our numerical simulation show that this geometrical parameter can be an interesting factor to increase the level of turbulence that is often required in several industrial applications where the economy and the control of energy are always required.

TPDF-ASOM复合湍流燃烧模型及其检验

先进航空发动机燃烧室设计要求对湍流火焰精确控制,现有模拟方法需提高精度和效率。输运概率密度函数(TPDF)湍流燃烧模型精度高,代数二阶矩(ASOM)湍流燃烧模型计算成本低,类比离散涡模拟思想,基于Da数将湍流燃烧场区分“高精度”和“低成本”2个区域,在输运方程框架下采用随机场TPDF(高精度)和ASOM(低成本)方法重构TPDF-ASOM复合湍流燃烧模型,以提高模拟的整体精度和效率。在大涡模拟(LES)-TPDF程序平台创建ASOM并进一步实现TPDF-ASOM复合湍流燃烧模型,用Flame D实验数据检验所建模型和方法。结果表明:所建模型的预测结果与实验值接近,而且能够兼顾精度和计算效率。

高速列车受电弓的低马赫数过渡式空腔射流降噪研究

受电弓及其空腔部位是高速列车主要的气动噪声源,降低这种噪声尤为重要。在以往的高速列车气动噪声研究中,对受电弓空腔部位的关注较少。针对高速列车受电弓及其空腔气动降噪问题,文中采用数值计算方法,研究简化的高速列车模型在350 km·h^(-1)下,受电弓空腔前缘射流降噪处理方式的流场特性和噪声传播规律。结果表明,在纯空腔前缘施加射流可以显著降低空腔内和受电弓附近的非定常流动,当射流速度为27 m·s^(-1)时,空腔后壁声源在空腔顶部和侧部辐射噪声的声压级降低最大值为5 dB,受电弓侧面监测点的噪声显著降低。文中研究为低马赫数下的过渡式空腔射流降噪研究提供了参考。

One neural network approach for the surrogate turbulence model in transonic flows

With the rapid development of artificial intelligence techniques such as neural networks,data-driven machine learning methods are popular in improving and constructing turbulence models.For high Reynolds number turbulence in aerodynamics,our previous work built a data-driven model applicable to subsonic airfoil flows with different free stream conditions.The results calculated by the proposed model are encouraging.In this work,we aim to model the turbulence of transonic wing flows with fully connected deep neural networks,where there is less research at present.The proposed model is driven by two flow cases of the ONERA(Office National d'Etudes et de Recherches Aerospatiales)wing and coupled with the Navier-Stokes equation solver.Four subcritical and transonic benchmark cases of different wings are used to evaluate the model performance.The iteration process is stable,and final convergence is achieved.The proposed model can be used to surrogate the traditional Reynolds averaged Navier-Stokes turbulence model.Compared with the data calculated by the Spallart-Allmaras model,the results show that the proposed model can be well generalized to the test cases.The mean relative error of the drag coefficient at different sections is below 4%for each case.This work demonstrates that modeling turbulence by data-driven methods is feasible and that our modeling pattern is effective.

Influence of Turbulence Schmidt Number on Exit Temperature Distribution of an Annular Gas Turbine Combustor using Flamelet Generated Manifold

The Reynolds analogy concept has been used in almost all turbulent reacting flow RANS(Reynoldsaveraged Navier–Stokes)simulations,where the turbulence scalar transfers in flow fields are calculated based on the modeled turbulence momentum transfer.This concept,applied to a lean premixed combustion system,was assessed in this paper in terms of exit temperature distribution.Because of the isotropic assumption involved in this analogy,the prediction in some flow condition,such as jet cross flow mixing,would be inaccurate.In this study,using Flamelet Generated Manifold as reaction model,some of the numerical results,obtained from an annular combustor configuration with the turbulent Schmidt number varying from 0.85 to 0.2,were presented and compared with a benchmark atmospheric test results.It was found that the Schmidt numberσt in mean mass fraction f transport equation had significant effect on dilution air mixing process.The mixing between dilution air and reaction products from the primary zone obviously improved asσt decreased on the combustor exit surface.Meanwhile,the sensitivity ofσt in three turbulence models including Realizable k-ε,SST(Shear Stress Transport)and RSM(Reynolds Stress Model)has been compared as well.Since the calculation method of eddy viscosity was different within these three models,RSM was proved to be less sensitive than another two models and can guarantee the best prediction of mixing process condition.On the other hand,the results of dilution air mixing were almost independent of Schmidt number Sct in progress variable c transport equation.This study suggested that for accurate prediction of combustor exit temperature distribution in steady state reacting flow simulation,the turbulent Schmidt number in steady state simulation should be modified to cater to dilution air mixing process.

Assessing aerodynamic loads on low-rise buildings considering Reynolds number and turbulence effects: a review

This paper presents an extensive review of existing techniques used in estimating design wind pressures considering Reynolds number and turbulence effects,as well as a case study of a reference building investigated experimentally.We shed light on the limitations of current aerodynamic testing techniques,provisions in design standards,and computational fluid dynamics(CFD)methods to predict wind-induced pressures.The paper highlights the reasons for obstructing the standardization of the wind tunnel method.Moreover,we introduce improved experimental and CFD techniques to tackle the identified challenges.CFD provides superior and efficient performance by employing wall-modeled large-eddy simulation(WMLES)and hybrid RANS-LES models.In addition,we tested a large-scale building model and compared the results with published small-scale data.The findings reinforce our hypothesis concerning the scaling issues and Reynolds number effects in aerodynamic testing.

内锥流量计流出系数预测方法研究

采用标准k-ε模型、RNG(Renormalization Group)k-ε模型、Realizablek-ε模型和Reynolds应力方程模型RSM(Reynolds Stress Model)对100 mm口径6种结构的内锥流量计内流场进行了数值模拟。在等效直径比β值为0.65的三种结构内锥流量计流出系数的仿真计算中,四种湍流模型计算结果与物理实验结果误差的平均值分别为4.19%,2.84%,2.88%和-0.822%;对β值为0.85的情况,各模型计算误差的平均值分别为11.8%,9.62%,9.30%和4.76%。研究结果表明,RSM模型在6种结构内锥流量计流出系数的预测中,计算精度较高,表现出了较好的性能,优于三种k-ε涡粘模型,更适于内锥流量计流场数值模拟与流出系数的预测。

液力缓速器变叶片数的三维数值模拟

将液力缓速器动静结合面定义为内部边界,解决了流体出入口在同一平面内的问题.利用Fluent软件对不同叶片数的液力缓速器的内流场进行数值模拟,计算采用雷诺时均方程和k-ε湍流模型,计算结果显示了液力缓速器不同叶片数下的速度分布、压力分布规律,并对流场内部流动进行了分析和研究.结果表明,随着叶片数的增加,进出口面速度的大小有先增大后减小趋势.轴面流道涡旋范围先增加后逐渐减小;而叶片吸力面的低压区逐渐扩大;叶片数为36时压力面的静压分布最均匀.

多层搅拌桨流动场的测量与数值模拟

应用商业计算流体力学软件CFX对搅拌槽内多层搅拌桨的流场进行了模拟 ,并与LDV测试结果进行了比较 .低Reynolds数k ε模型和代数应力模型流型吻合较好 ;标准k ε双方程模型和RNGk ε模型下层桨流场出现不同程度的扭曲 ,与实验测试结果不符 .速度分量的对比结果表明 ,低Reynolds数k ε模型和代数应力模型能较准确地模拟搅拌槽内的流动场 。