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.     

富氧燃烧烟气喷淋脱水过程数值模拟

富氧燃烧系统中,脱硫后的高湿烟气需要经过脱水处理才能作为循环烟气利用,喷淋塔是一种常用的脱水设备。本文用CFD(Computational Fluid Dynamics)方法对喷淋塔的烟气脱水过程进行了三维建模模拟,得到了喷淋塔内的温湿度分布并用实验结果进行了验证。通过该模型分析了喷嘴的操作参数和运行特性对液滴平均运动时间和脱水效果的具体影响,讨论了数值模拟中出口烟气"过饱和"现象的成因,研究了不凝气组分对脱水过程的影响,为富氧燃烧脱水系统的设计提供了基础数据和理论方法。     

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     

Streakline visualization of the structures in the near wake of a circular cylinder in sinusoidally oscillating flow

A numerical investigation of three-dimensional sinusoidally oscillating flow around a circular cylinder was conducted to examine mushroom-type structures in the near wake that are manifestations of the Honji instability. The focus of this paper is to examine the flow structure through the analysis of the streaklines in the flow. Through the use of streakline visualizations and their correlation with vorticity in the flow field, the onset and development of the mushroom-type structures is followed. The parameter value range is 0.1<KC<2.0 and β=1035, 6815, and 9956. The streakline patterns in several axial planes are examined and used to describe the various mechanisms that sustain the mushroom-type structure during the oscillatory cycle.