Rotational invariance in the three-dimensional lattice Boltzmann method is dependent on the choice of lattice

The lattice Boltzmann method has recently gained popularity as a tool for simulating complex fluid flows. It uses discrete sets of velocity vectors, or lattices, to create a reduced model of the molecular dynamics of a continuum fluid. While several lattices are believed to behave isotropically, there are reports of qualitatively incorrect results. However, thus far, the reason as to why a lack of isotropy occurs is not known. Based on the hypothesis that lower order lattices may not display rotational invariance, this study tests the isotropy of the D3Q15, D3Q19 and D3Q27 lattices by performing simulations at intermediate Reynolds numbers (50–500) and low Knudsen number (<0.0005) in an axisymmetrical geometry with a nozzle leading to a throat followed by a sudden expansion. The symmetry properties of the results were examined. It was found that at Re ? 250 the D3Q15 and D3Q19 lattices produced different results depending on the plane of the lattice with which the flow was aligned. Lattice planes with fewer than six velocity vectors consistently produced results which were qualitatively different from the planes with six or more velocity vectors. These errors were not observed at Re = 50 or when a D3Q27 lattice was used. They appeared to be independent of grid density, collision operator and Ma. This suggests that the lattices which contain these planes are not fully isotropic and therefore do not properly replicate the behavior of a real fluid in this particular situation, notably downstream from the expansion. Predictions made using these models in more complex geometries may therefore be affected by the orientation of the lattice. When using LBM in CFD simulation (including validation) this study highlights the need for caution to ensure that the solution obtained is independent of the lattice orientation throughout the domain.     

A new domain decomposition method with overlapping patches for ultrascale simulations: Application to biological flows

We address the failure in scalability of large-scale parallel simulations that are based on (semi-)implicit time-stepping and hence on the solution of linear systems on thousands of processors. We develop a general algorithmic framework based on domain decomposition that removes the scalability limitations and leads to optimal allocation of available computational resources. It is a non-intrusive approach as it does not require modification of existing codes. Specifically, we present here a two-stage domain decomposition method for the Navier–Stokes equations that combines features of discontinuous and continuous Galerkin formulations. At the first stage the domain is subdivided into overlapping patches and within each patch a C⁰ spectral element discretization (second stage) is employed. Solution within each patch is obtained separately by applying an efficient parallel solver. Proper inter-patch boundary conditions are developed to provide solution continuity, while a Multilevel Communicating Interface (MCI) is developed to provide efficient communication between the non-overlapping groups of processors of each patch. The overall strong scaling of the method depends on the number of patches and on the scalability of the standard solver within each patch. This dual path to scalability provides great flexibility in balancing accuracy with parallel efficiency. The accuracy of the method has been evaluated in solutions of steady and unsteady 3D flow problems including blood flow in the human intracranial arterial tree. Benchmarks on BlueGene/P, CRAY XT5 and Sun Constellation Linux Cluster have demonstrated good performance on up to 96,000 cores, solving up to 8.21B degrees of freedom in unsteady flow problem. The proposed method is general and can be potentially used with other discretization methods or in other applications.     

过冷沸腾非均相汽泡界面特性分析

本文针对过冷沸腾中汽泡顶部射流现象进行分析与模拟。建立汽泡界面模型,考虑蒸发凝结以及Marangoni效应。利用CFD软件Fluent6.0对模型进行计算分析,成功模拟得到泡顶射流流场。模拟结果无论是流场结构,还是流场强度,都与实验一致吻合,充分证明泡顶射流由Marangoni效应引起。     

Sliding mesh algorithm for CFD analysis of helicopter rotor–fuselage aerodynamics

The study of rotor–fuselage interactional aerodynamics is central to the design and performance analysis of helicopters. However, regardless of its significance, rotor–fuselage aerodynamics has so far been addressed by very few authors. This is mainly due to the difficulties associated with both experimental and computational techniques when such complex configurations, rich in flow physics, are considered. In view of the above, the objective of this study is to develop computational tools suitable for rotor–fuselage engineering analysis based on computational fluid dynamics (CFD). To account for the relative motion between the fuselage and the rotor blades, the concept of sliding meshes is introduced. A sliding surface forms a boundary between a CFD mesh around the fuselage and a rotor‐fixed CFD mesh which rotates to account for the movement of the rotor. The sliding surface allows communication between meshes. Meshes adjacent to the sliding surface do not necessarily have matching nodes or even the same number of cell faces. This poses a problem of interpolation, which should not introduce numerical artefacts in the solution and should have minimal effects on the overall solution quality. As an additional objective, the employed sliding mesh algorithms should have small CPU overhead. The sliding mesh methods developed for this work are demonstrated for both simple and complex cases with emphasis placed on the presentation of the inner workings of the developed algorithms. Copyright © 2008 John Wiley & Sons, Ltd.     

计算域对CFD模拟结果的影响

CFD数值模拟技术正迅速地成为学术研究和工程实际问题分析及设计中不可缺少的工具。然而由于计算机的限制,人们在进行数值计算时常常对所研究的问题进行简化,例如几何模型简化、物理模型简化、以及边界条件近似等,这些都会对计算结果带来一定的误差。本文将通过两个轴流压缩机的例子说明计算域和边界条件选取对数值模拟结果的影响。     

A taylor weak-statement algorithm for hyperbolic conservation laws

Finite element analysis, applied to computational fluid dynamics (CFD) problem classes, presents a formal procedure for establishing the ingredients of a discrete approximation numerical solution algorithm. A classical Galerkin weak-statement formulation, formed on a Taylor series extension of the conservation law system, is developed herein that embeds a set of parameters eligible for constraint according to specification of suitable norms. The derived family of Taylor weak statements is shown to contain, as special cases, over one dozen independently derived CFD algorithms published over the past several decades for the high speed flow problem class. A theoretical analysis is completed that facilitates direct qualitative comparisons. Numerical results for definitive linear and non-linear test problems permit direct quantitative performance comparisons.     

Analysis of droplet behavior in a de-oiling hydrocyclone

A mechanical separation process in a de-oiling hydrocyclone is described in which disperse oil droplets are separated from a continuous water phase. This separation process is influenced by droplet breakage and coalescence. Based on experimental data and simulation results in a stirred tank, a modified breakage model, which can be applied to droplet breakage in the de-oiling hydrocyclone, is developed. Then, a simulation model is developed coupling the numerical solution of the flow field in the hydrocyclone based on computational fluid dynamics (CFD) with population balances. The homogenous discrete method and the inhomogeneous discrete method are applied for solving the population balance model (PBM). The investigations show that the numerical results obtained by the simulation model coupled with the modified PBM using the inhomogeneous discrete method are in good accordance with experimental data under a high flow rate. According to this simulation model, the effect of three different inlet designs on the separation efficiency of the de-oiling hydrocyclone has been discussed. The results indicate that the separation efficiency of the de-oiling hydrocyclone can be improved with an appropriate inlet design.     

连续螺旋折流板蒸发器壳侧流动换热数值模拟研究

本文对相同几何尺寸的连续螺旋折流板蒸发器与传统弓形折流板蒸发器进行对比性的数值模拟研究,结果表明:在相同壳侧体积流量和折流板数条件下,连续螺旋折流板蒸发器的传热因子和摩擦因子约是弓形折流板的1/3和1/4;当以换热因子和摩擦因子比值评价蒸发器综合性能时,连续螺旋折流板蒸发器比弓形折流板蒸发器提高57%;当最小流通截面流...     

内锥式流量计数值模拟及优化设计

多相流过程参数的准确测量在石油化工与冶金工业等工业过程中十分重要。内锥式流量计作为一种新型差压流量计在多相流测量中逐渐受到关注,它能在较短的直管段条件下对流体实现准确的测量,但其结构尚存在优化的空间,需进行深入研究。本文对传统内锥式流量计做结构变形和优化研究,利用计算流体力学(CFD)方法对DN50 mm水平管道中内锥变形体的流场进行数值模拟,分析在不同结构参数下锥体的水力特性以优化结构。数值仿真结果表明,综合内锥式流量计在取压点、永久压损及测量精确度等因素,优化后的结构可以显著降低永久压损,提高测量重复性和精确度。     

Numerical investigation of hypersonic step-flows

Hypersonic aerospace vehicles are exposed to extreme flight conditions with heavy contour loads during their mission. Especially at ridges and sharp corners, the wall heat flux and pressure may cause serious damage to the body. Sometimes, the surface material cannot resist the high loading and fails completely. In this work the laminar hypersonic flow over forward and backward facing steps is investigated by CFD techniques and the results are compared with experimental data. The selected flow conditions correspond to cold hypersonic flow according to the availability of experimental data. The Navier-Stokes equations in the high temperature gas approximation of a thermally perfect gas in local equilibrium serve as the model for the physical problem. A multiblock finite-volume method is used to discretize consistently all spatial derivatives appearing in the balance equations. A second order in space Godunov-type method is utilized for the non-diffusive part of the governing equations whereas centered differences are used for the diffusive part. Time integration is performed by a second order implicit scheme. In each time step, the resulting nonlinear system of equations is solved by Newton's method employing a relaxation scheme based on conjugate gradients for the linear equation system. The results obtained permit a close insight into the physics of the flow problems under consideration and by this provide valuable information for construction concepts of hypersonic vehicles. Besides a careful comparison of the numerical results with experimental data, numerical aspects like the grid influence are addressed. Received 9 November 1998 / Accepted 2 December 1999