Lattice Boltzmann Flux Solver:An Efficient Approach for Numerical Simulation of Fluid Flows

A lattice Boltzmann flux solver(LBFS)is presented for simulation of fluid flows.Like the conventional computational fluid dynamics(CFD)solvers,the new solver also applies the finite volume method to discretize the governing differential equations,but the numerical flux at the cell interface is not evaluated by the smooth function approximation or Riemann solvers.Instead,it is evaluated from local solution of lattice Boltzmann equation(LBE)at cell interface.Two versions of LBFS are presented in this paper.One is to locally apply one-dimensional compressible lattice Boltzmann(LB)model along the normal direction to the cell interface for simulation of compressible inviscid flows with shock waves.The other is to locally apply multi-dimensional LB model at cell interface for simulation of incompressible viscous and inviscid flows.The present solver removes the drawbacks of conventional lattice Boltzmann method(LBM)such as limitation to uniform mesh,tie-up of mesh spacing and time interval,limitation to viscous flows.Numerical examples show that the present solver can be well applied to simulate fluid flows with non-uniform mesh and curved boundary.

High-precision nonisothermal transient wellbore drift flow model suitable for the full flow pattern domain and full dip range

A reliable multiphase flow simulator is an important tool to improve wellbore integrity and production decision-making.To develop a multiphase flow model with high adaptability and high accuracy,we first build a multiphase flow database with 3561 groups of data and developed a drift closure relationship with stable continuity and high adaptability.Second,a high-order numerical scheme with strong fault capture ability is constructed by effectively combining MUSCL technology,van Albada slope limiter and AUSMV numerical scheme.Finally,the energy equation is coupled into the AUSMV numerical scheme of the drift flow model in the form of finite difference.A transient non-isothermal wellbore multiphase flow model with wide applicability is formed by integrating the three technologies,and the effects of various factors on the calculation accuracy are studied.The accuracy of the simulator is verified by comparing the measurement results with the blowout experiment of a full-scale experimental well.

高焓流动中的可压缩颗粒两相流并行求解器:数值方法及其验证

在极端力学环境下可压缩点力颗粒两相流理论方程的基础上,提出一种基于动态链表数组的并行颗粒求解器,使其与可压缩流体求解器耦合。与基于欧拉坐标系的携带流体相不同,基于拉格朗日坐标系的求解器采用动态链表数组对弥散颗粒相进行内存分配,可以解决因使用全局数组解决拉格朗日/欧拉坐标系转换带来的弥散颗粒群内存利用率低和计算效率低下问题。最后对多物理效应的可压缩颗粒两相流求解器进行验证,并在马赫数渐进趋于零的情况下,对两个不可压缩槽道颗粒湍流标模进行验证。

客运需求局部缩减条件下列车开行方案调整研究

因疫情或其他特定事件导致局部客运需求缩减时,铁路各OD之间客流规模均发生相应变化。如何保证铁路运输生产连续性来调整列车开行方案是铁路运营企业面临的难题。归纳了应对不同客运需求缩减场景的列车开行方案调整策略,包括列车停运、列车编组调整、列车运行区段调整、列车停站办理客运作业调整及关联售票调整。以此为基础,构建列车开行方案调整模型,对列车停运、列车停站不办理客运作业和列车编组调整综合决策,其中列车停运考虑整交路以实现决策在实际中的适用性。通过算例证明了模型的有效性,在实际线路案例中的结果显示,通过优化列车开行方案运力配置,调整后结果在供需匹配的基础上可以控制运营成本,减少需求缩减带来的损失。

Transversal effects of high order numerical schemes for compressible fluid flows

Finite volume schemes for the two-dimensional(2D) wave system are taken to demonstrate the role of the genuine dimensionality of Lax-Wendroff flow solvers for compressible fluid flows. When the finite volume schemes are applied, the transversal variation relative to the computational cell interfaces is neglected, and only the normal numerical flux is used, thanks to the Gauss-Green formula. In order to offset such defects, the Lax-Wendroff flow solvers or the generalized Riemann problem(GRP) solvers are adopted by substituting the time evolution of flows into the spatial variation. The numerical results show that even with the same convergence rate, the error by the GRP2D solver is almost one ninth of that by the multistage Runge-Kutta(RK) method.

Harten-Lax-van Leer-contact(HLLC)approximation Riemann solver with elastic waves for one-dimensional elastic-plastic problems

A Harten-Lax-van Leer-contact （HLLC） approximate Riemann solver is built with elastic waves （HLLCE） for one-dimensional elastic-plastic flows with a hypo- elastic constitutive model and the von Mises＇ yielding criterion. Based on the HLLCE, a third-order cell-centered Lagrangian scheme is built for one-dimensional elastic-plastic problems. A number of numerical experiments are carried out. The numerical results show that the proposed third-order scheme achieves the desired order of accuracy. The third-order scheme is used to the numerical solution of the problems with elastic shock waves and elastic rarefaction waves. The numerical results are compared with a reference solution and the results obtained by other authors. The comparison shows that the pre- sented high-order scheme is convergent, stable, and essentially non-oscillatory. Moreover, the HLLCE is more efficient than the two-rarefaction Riemann solver with elastic waves （TRRSE）

Analysis of Unsteady Flow over Offshore Wind Turbines in Combination with Different types of Foundations

Environmental effects have an important influence on Offshore Wind Turbine (OWT) power generation efficiency and the structural stability of such turbines. In this study, we use an in-house Boundary Element (BEM)-panMARE code-to simulate the unsteady flow behavior of a full OWT with various combinations of aerodynamic and hydrodynamic loads in the time domain. This code is implemented to simulate potential flows for different applications and is based on a three-dimensional first-order panel method. Three different OWT configurations consisting of a generic 5 MW NREL rotor with three different types of foundations (Monopile, Tripod, and Jacket) are investigated. These three configurations are analyzed using the RANSE solver which is carried out using ANSYS CFX for validating the corresponding results. The simulations are performed under the same environmental atmospheric wind shear and rotor angular velocity, and the wave properties are wave height of 4 m and wave period of 7.16 s. In the present work, wave environmental effects were investigated firstly for the two solvers, and good agreement is achieved. Moreover, pressure distribution in each OWT case is presented, including detailed information about local flow fields. The time history of the forces at inflow direction and its moments around the mudline at each OWT part are presented in a dimensionless form with respect to the mean value of the last three loads and the moment amplitudes obtained from the BEM code, where the contribution of rotor force is lower in the tripod case and higher in the jacket case and the calculated hydrodynamic load that effect on jacket foundation type is lower than other two cases.

A computational study on robust prediction of transition point over NACA0012 aerofoil surfaces from laminar to turbulent flows

Flow transition from laminar to turbulent is prerequisite to decide whereabouts to apply surface flow control techniques. This appears missing in a number of works in which the control effects were merely investigated without getting insight into alteration of transition position. The aim of this study is to capture the correct position of transition over NACA0012 aerofoil at different angles of attack. Firstly, an implicit, time marching, high resolution total variation diminishing （TVD） scheme was developed to solve the governing Navier-Stokes equations for compressible fluid flows around aerofoil sections to obtain velocity profiles around the aerofoil surfaces. Secondly, the linear instability solver based on the Orr-Sommerfeld equations and the eg methods were developed to calculate the onset of transition over the aerofoil surfaces. For the low subsonic Mach number of 0.16, the accuracy of the compressible solutions was assessed by some available experimental results of low speed incompressible flows. In all cases, transition positions were accurately predicted which shows applicability and superiority of the present work to be extended for higher Mach number compressible flows. Here, transition prediction methodology is described and the results of this analysis without active flow control or separation are presented.

DIFFERENCE SCHEME FOR TWO-PHASE FLOW

A numerical method for two-phase flow with hydrodynamics behavior was considered. The nonconservative hyperbolic governing equations proposed by Saurel and Gallout were adopted. Dissipative effects were neglected but they could be included in the model without major difficulties. Based on the opinion proposed by Abgrall that “a two phase system, uniform in velocity and pressure at t=0 will be uniform on the same variable during its temporal evolution", a simple accurate and fully Eulerian numerical method was presented for the simulation of multiphase compressible flows in hydrodynamic regime. The numerical method relies on Godunov-type scheme, with HLLC and Lax-Friedrichs type approximate Riemann solvers for the resolution of conservation equations, and nonconservative equation. Speed relaxation and pressure relaxation processes were introduced to account for the interaction between the phases. Test problem was presented in one space dimension which illustrated that our scheme is accurate, stable and oscillation free.

基于自主开发求解器的蒸汽发生器二次侧流场分析

针对蒸汽发生器二次侧复杂流动传热现象,基于iconCFD开发了新的物理模型和求解器,采用多孔介质模型完成了对蒸汽发生器二次侧的流动和换热现象的数值模拟分析。计算模型中通过映射的方法实现了不同区域之间的数据的相互交换和更新,计算结果与ATHOS软件计算的结果相比对,通过比较一次侧出口温度、二次侧出口水蒸气质量流量和二次侧进口和出口处压力,此3项与ATHOS软件计算结果误差均小于1%,验证了新求解器的有效性和可靠性。

Modeling and Simulation of Real Gas Flow in a Pipeline

In this paper, a mathematical model that describes the flow of gas in a pipe is formulated. The model is simplified by making some assumptions. It is considered that the natural gas flowing in a long horizontal pipe, no heat source occurs inside the volume, transfer of heat due to heat conduction is dominated by heat exchange with the surrounding. The flow equations are coupled with equation of state. Different types of equations of state, ranging from the simple Ideal gas law to the more complex equation of state Benedict Webb Rubin Starling (BWRS), are considered. The flow equations are solved numerically using the Godunov scheme with Roe solver. Some numerical results are also presented.

流体拓扑优化的方法及应用综述

流体拓扑优化是一项突破性技术,在航空航天、汽车、电子芯片等领域均有广泛的应用前景,然而其所设计出的复杂结构难以通过传统制造技术加工成型等因素制约了它的推广应用。增材制造(3D打印)技术的发展为进一步拓展流体拓扑优化的应用和研究提供了有效途径,对实现相关工业装备的结构轻量化、动力学优化、安全性优化以及性能提升,落实国家“节能降耗、碳达峰碳中和”战略具有重要意义。借助文献计量工具VOSviewer对Web of Science数据库中流体拓扑优化相关文献进行了梳理和总结,全面系统阐述了流体拓扑优化的理论体系、求解方法、优化方法以及工程应用,并对相关问题进行了探讨。首先,与固体拓扑优化相比,流体拓扑优化涉及领域更广、流态特征更多样、数学模型更复杂,因而求解更困难、计算时间更长、计算资源需求更大,这是制约流体拓扑优化工程应用的主要因素。其次,较系统阐述了流体拓扑优化的3个环节和关键技术:拓扑设计变量表述方法、CFD模型及求解方法、拓扑优化模型及求解方法,并分析了现有技术的特点和应用场景,同时,对流体拓扑优化的电子芯片热沉、飞机汽车、换热器等几个应用场景进行了简述。最后,对流体拓扑优化的发展趋势进行了预测和总结,建议进一步加大湍流、共轭传热、流-固-热耦合、流-固-热-质耦合等方面的多学科拓扑优化研究;拓展基于多目标函数的拓扑优化研究;进一步加强与人工智能的深度结合,开发更加稳健成熟的智能CFD求解器、智能优化求解器以及智能流体拓扑优化软件。

利用规划求解拟合水位流量关系曲线探讨

控制条件稳定的测站水位流量关系也保持稳定,通常采用单一曲线法推求流量。利用Excel规划求解功能,建立指数函数模型,拟合水位流量关系曲线,通过检验分析,拟合结果满足水文资料整编规范要求。此方法易操作上手,能够提高工作效率和拟合精度,具有推广应用价值。

亚跨超 CFD 软件平台研制

亚跨超ＣＦＤ软件平台研制课题的宗旨是综合国内外计算流体动力学的最新研究成果，用计算机软件技术的新发展，建立一个面向对象的计算流体动力学的研究开发环境，加快计算流体动力学最新成果向工程应用的转换速度。本文介绍初级版本的研究进展和研究成果，主要由数值网格生成技术、流场解算器、面向对象的界面设计等三部分组成。

基于改进k-ω SST模型的风力机尾流数值模拟

基于双方程k-ω SST模型提出两种改进湍流模型,采用丹麦科技大学的自编求解器EllipSys3D结合致动盘方法,对单台风力机尾流流场进行数值模拟。该文将SST-sust模型引入到风力机尾流的数值研究中,为了更进一步增大预测到的湍流强度和提高尾流恢复速度,提出SST-Csust模型和SST-Dsust模型,它们是在SST-sust模型的基础上分别调整湍流模型的封闭常系数、修正ω方程的耗散项。通过与理论、实验以及LES模型进行对比分析,结果表明该文提出的改进模型在尾流区速度分布和湍流强度分布的预测方面可取得较好的应用效果。

基于遗传算法的高超声速进气道自动优化设计

高超声速进气道的优化设计对于改善进气道的性能,进而提高发动机整体飞行效率具有重要意义。利用FLUENT/MATLAB协同仿真技术,通过CFD对进气道模型进行高维分析,结合多机并行运算发挥遗传算法全局寻优的能力,提出了一种基于遗传算法和CFD仿真的高效、高精度的高超声速进气道自动优化设计方法,试图构建一种高超声速进气道自动优化设计的快速原型仿真平台。通过对三楔面定收缩比进气道的多目标优化算例,初步验证了此方法的可行性与高效性,为开展多变量多目标的高超声速进气道优化设计创造了良好的条件。

基于计算流体力学的“虚拟飞行”技术及初步应用

以动态混合网格技术为基础,通过耦合求解刚体动力学方程、流体力学控制方程以及飞行控制律,建立了适用于飞行器"虚拟飞行"过程研究的一体化数值模拟技术.通过典型的外挂物投放算例对流体力学控制方程/动力学方程的耦合算法进行了测试,并对某导弹的姿态角控制过程、过载控制过程以及变马赫数条件下的控制过程进行了数值模拟,得到了与实验非常一致的结果.这些算例证明该一体化算法已经初步具备了针对复杂飞行器"数值虚拟飞行"的应用能力.

非平衡流解耦方法及其计算激波诱导燃烧的应用验证

介绍并发展了一种改进的化学非平衡流动解耦方法.将流动控制方程与化学反应生成源项解耦处理,组分对流项的矢通量分裂基于流动方程密度对流项的分裂形式给出.对流项采用五阶WENO格式求解,化学反应源项的刚性采用简化的隐式方法进行处理.将该方法应用于预混H2/O2和H2/Air激波诱导燃烧计算,得到的定常及非定常燃烧过程与实验观测相符,振荡频率与实验测量较吻合,结果表明该方法应用于多组分多步反应流计算是可行的.

基于遗传算法与近似模型的全局气动优化方法

开发了基于精英保留策略与小生境技术的求解有约束优化问题的改进遗传算法,并用一多峰值有约束函数对其寻优能力进行了测试。为了降低气动优化设计时间,提出了集成实验设计、三维粘性流场求解程序、二次多项式近似模型、改进遗传算法的具有全局寻优能力的三维气动优化设计体系。采用该方法对NASA Rotor37动叶片叶型进行了以绝热效率最大为目标的优化设计,优化后叶片绝热效率提高1.1%。该结果表明了本优化设计体系省时、高效的特点。

基于模拟退火算法与响应面模型的三维气动优化设计方法

提出了一套适用于高耗时三维气动设计问题的优化设计体系。其主要思想是采用改进拉丁超立方体试验设计选取样本点,应用自行开发的三维粘性流场求解程序进行流场计算建立数据库,采用二次响应面方法建立近似模型,再应用高效模拟退火算法进行全局寻优。以NASA rotor67为对象,在详细进行流场计算基础上采用所提出的优化体系对其进行了三维积叠优化设计。在对流量、效率加以严格约束的条件下,总压比可提高1.8%,对流场结构进行了分析。优化结果表明本优化方法省时,适于三维气动设计的特点。