Hartmann共振管及超音速雾化喷嘴

采用基于Roe解法的有限体积法，对Hartmann共振管中的气体流场进行了数值模拟，研究了当喷嘴轴线处存在针型激励器的情况下流场的振动情况，数值计算的结果与理论和相关的实验结果符合得较好．计算结果表明移除或引入激励器，将会使Hartmann共振管的共振模式发生转换．通过对超音速雾化喷嘴流场的数值模拟，研究了其中Hartmann共振腔和二级共振腔共同作用下的振动现象以及各物理参数对振动的影响，并对喷嘴中气流从亚音速向超音速的转变机理进行了研究．     

双激励超音速气体雾化喷嘴共振特性的数值研究

超音速气体雾化(ultra-sonic gas atomization,USGA) 喷嘴是实现喷射雾化的重要装置,它能够产生脉动的超音速气流,获得较小的平均粒径和集中的粒径分布.在USGA喷嘴的共振管端部引入了主动的激励信号,组成双激励式超音速气体雾化器,并对超音速气体雾化器内部Hartmann腔体气体流场在无激励/有激励情况下所产生的气体振动特性进行了数值研究.结果表明在主动激励器的作用下,超音速气体雾化器内气流的振动效果如振幅和起振特性等都得到了有效的加强.研究发现超音速气体雾化器存在多个气体受激振动的共振频率,其对应于两类不同的共振模式,“Hartmann模式”和“全局模式”.双激励器信号的频率、激励幅度及相位差改变都能够有效地改变超音速气流的振动特性.研究同时阐明了Hartmann共振管和二次共振管在USGA喷嘴腔体内产生气体脉动时的联动特点.     

直管束流固耦合振动的数值模拟

为了研究反应堆结构中的诸如燃料棒、蒸汽发生器和其它换热器传热管束等的流体-结构交互作用问题,利用有限体积法离散大涡模拟(large eddy simulation, LES)的流体控制方程,用有限元方法求解结构动力学方程,并结合动网格技术,建立三维流体诱发振动的数值模型,模拟直管束中流体的流动及结构振动,实现计算结构动力学(computational structure dynamics, CSD)与计算流体力学(computational fluid dynamics, CFD)之间的联合仿真．首先,基于流固耦合方法对单管的流致振动特性进行了详细分析,得到了其动力学响应与流场特性;其次基于建立的传热管束流致振动计算模型,研究了两并列管、两串列管以及3×3正方形排列管束的流致振动行为．     

抛物化稳定性方程在可压缩边界层中应用的检验

用抛物化稳定性方程（PSE）,研究了可压缩边界层中扰动的演化,并与由直接数值模拟（DNS）所得进行比较．目的在检验PSE方法用于研究可压缩边界层中扰动演化的可靠性．结果显示,无论是亚音速还是超音速边界层,由PSE方法和由DNS方法所得结果都基本一致,而温度比速度吻合得更好．对超音速边界层,还计算了小扰动的中性曲线．与线性稳定性理论（LST）的结果相比,二者的关系和不可压边界层的情况相似．     

湍流边界层内准流向发卡涡生成的数值模拟

采用根据共振三波理论模型建立的初始准二维流场和直接数值模拟方法,对湍流边界层近壁区流向涡的生成进行了研究．计算得到了准流向发卡涡和次生准流向涡结构的生成过程及其主要特征,讨论了它们的产生机理．作为相干结构的主要特征,利用共振三波理论模型对流向涡结构生成与演化过程的研究为湍流边界层内相干结构的研究与流动控制提供了新的途径和思路．     

车桥系统的耦合振动

通过用正弦波形模拟桥面的不平和考虑移动车辆-桥梁间的相互作用,在Euler-Bernoulli梁理论的基础上建立了一种车桥系统的耦合振动模型．利用模态分析法和Runge-Kutta法对模型进行数值求解,获得了车桥系统耦合振动的动态响应和共振曲线．发现车桥耦合振动的共振曲线中存在两个共振区域,一个反映主共振而另一个反映次共振．讨论了桥面不平、桥梁振型和车辆间的相互作用对系统振动的影响．数值结果表明,这些参数对系统振动的影响很大,桥面不平和振型对车桥系统耦合振动的影响不能忽略,设计车速应该远离临界车速．     

膛口流场动力学过程数值研究

采用基于ALE方法的动网格及嵌入网格技术,运用有限体积方法,结合二阶精度Roe格式,对弹丸由高压气体驱动从静止状态加速至超音速,射出膛口到完全飞离初始流场的整个过程进行了数值模拟．根据数值结果,详细讨论了初始流场、火药燃气流场的形成与发展以及与弹丸的耦合和相互作用过程,揭示了在这一变化过程中激波与激波、激波与漩涡、激波与弹丸等的相互作用以及激波衍射、聚焦等对弹丸加速的影响．     

非线性转子-密封系统1∶2亚谐共振分岔研究

研究了转子-密封系统在气流激振力作用下的低频振动——1∶2亚谐共振现象．利用流体计算动力学（CFD）方法对转子-密封系统进行了流场模拟计算,辨识出适用于气流流场的Muszynska模型参数,并建立了转子-密封系统动力学方程．采用多尺度方法将系统进行3次截断,并得到系统响应．采用奇异性理论研究了系统的1∶2亚谐共振,进一步得到系统亚谐共振的分岔方程和转迁集,根据转迁集给出了在不同奇异性参数空间内的分岔图．同时,由分岔方程得到了亚谐共振非零解存在的条件．其分析结果对抑制转子-密封系统的亚谐振动有重要的工程意义．     

二维超音速边界层中三波共振和二次失稳机制的数值模拟研究

通过直接数值模拟的方法,探讨在超音速边界层的转捩问题中,是否存在和不可压缩流情况相似的产生亚谐波的机制．结果表明,三波共振和二次失稳这两种机制都存在．讨论了这两种机制在层流至湍流的转捩中的重要性是否的确很大的问题．     

突然扩张方管中三维湍流流动的数值模拟

本文运用SIMPLEC算法计算了突然扩张方管中的三维湍流流动,湍流模型采用k-ε模型。计算结果详细反映了突然扩张方管中三维湍流流场。从本文结果可以看出,由于突然扩张方管几何形状非轴对称,且尺寸有限,边壁对流场的作用是不可忽略的。以往文献中常见的二维突然扩张湍流的数值模拟结果与三维情况有较大差别,在靠近边壁的区域差别很大,因此对于突然扩张方管中湍流流动的数值模拟应用三维模拟。本文计算所得突然扩张截面后主回流区长度与实验结果接近。本文方法可为数值模拟突然扩张方管中湍流流场及各物理参数的分布提供有效工具。     

Oscillation of Confined Jets in Continuous Casting Mold Flow

In continuous slab casting, the liquid steel is introduced into the mould via a submergered entry nozzle. This nozzle usually has two opposed orifices on its side walls, generating two diametrically opposed turbulent jets that are declined about 20° to the horizontal axis. These jets interact with the surrounding walls of the mould, which leads to an unstable flow situation and a self induced oscillation of the jets. Although both mould and nozzle geometry have two perpendicular symmetry planes, the oscillations are asymmetric. The fluid flow inside the mold is calculated with a 3D finite volume solver using turbulence models based on Reynolds-averaging. The massflow of the jets and the mould extensions are varied, and the numerical results are partially compared with PIV-measurements at a 1:1 scaled watermodel of the mould. (© 2006 WILEY-VCH Verlag GmbH & Co. KGaA, Weinheim)     

伴有磁场和纳米固体颗粒时的Jeffery-Hamel流动解析研究——Adomian分解法

用一种强有力的解析方法,称为Adomian分解法(ADM),来研究磁场和纳米颗粒对Jeffery-Hamel流动的影响.将该问题模型的控制方程,即将传统的流体力学Navier-Stokes方程和Maxwell电磁方程,简化为非线性的常微分方程.该方法得到的结果与Runge-Kutta方法得到的数值结果相一致,结果用表格列出.不同α,Ha和Re数下的图形表明,本方法可以得到高精度的结果.首先对不同的Hartmann数和管壁倾角,研究喇叭形管道中的流场;最后在没有磁场作用时,研究纳米固体颗粒体积率的影响.     

Forms of Unsteady Flow in a 2-D Channel

The paper describes results of a numerical simulations of air flow in a turned off, 2D channel with the plain nozzle. Simulations are based on an earlier experiment, carried out by Dyban, Mazur and Epik (1971). In the featured channel it has been observed several bifurcation forms, depending on the flow velocity and geometry relations. Basing on the numerical simulations results, the integral characteristics of the flow areas has also been presented. (© 2005 WILEY-VCH Verlag GmbH & Co. KGaA, Weinheim)     

Assessment of turbulence modeling for gas flow in two-dimensional convergent–divergent rocket nozzle

In the present study, the turbulent gas flow dynamics in a two-dimensional convergent–divergent rocket nozzle is numerically predicted and the associated physical phenomena are investigated for various operating conditions. The nozzle is assumed to have impermeable and adiabatic walls with a flow straightener in the upstream side and is connected to a plenum surrounding the nozzle geometry and extended in the downstream direction. In this integrated component model, the inlet flow is assumed a two-dimensional, steady, compressible, turbulent and subsonic. The physics based mathematical model of the considered flow consists of conservation of mass, momentum and energy equations subject to appropriate boundary conditions as defined by the physical problem stated above. The system of the governing equations with turbulent effects is solved numerically using different turbulence models to demonstrate their numerical accuracy in predicting the characteristics of turbulent gas flow in such complex geometry. The performance of the different turbulence models adopted has been assessed by comparing the obtained results of the static wall pressure and the shock position with the available experimental and numerical data. The dimensionless shear stress at the nozzle wall and the separation point are also computed and the flow field is illustrated. The various implemented turbulence models have shown different behavior of the turbulent characteristics. However, the shear-stress transport (SST) k–ω model exhibits the best overall agreement with the experimental measurements. In general, the proposed numerical procedure applied in the present paper shows good capability in predicting the physical phenomena and the flow characteristics encountered in such kinds of complex turbulent flow.     

Numerical Simulation of the Flow over a Segment-Conical Body on the Basis of Reynolds Equations

Numerical simulation was used to study the 3D supersonic flow over a segment-conical body similar in shape to the ExoMars space vehicle. The nonmonotone behavior of the normal force acting on the body placed in a supersonic gas flow was analyzed depending on the angle of attack. The simulation was based on the numerical solution of the unsteady Reynolds-averaged Navier–Stokes equations with a two-parameter differential turbulence model. The solution of the problem was obtained using the in-house solver HSFlow with an efficient parallel algorithm intended for multiprocessor super computers.     

Study of Heat Flow through Highly Porous Heat Insulators

A comprehensive study is done to model flow of heat through heat insulators based on materials with high gas content such as solidified foams (e.g., eXtruded PolyStyrene foams, Expanded PolyStyrene foam), cellular glass, etc. The actual internal cell-like structure of such an insulator is replicated by regularly shaped gas pockets, which are separated from each other by thin rims of solid materials. The first model focuses on heat flow across the insulator caused by conduction and convection. Subsequently, the effect of radiation is also studied. Several numerical results are presented and computational results are compared with experimentally measured data.     

Flow of a conducting dusty gas past a flat plate

An exact solution is derived by Laplace-transform technique for the problem of the flow of a conducting dusty gas occupying a semi-infinite space in the presence of a transverse magnet field. It is assumed that the flow is independent of the distance parallel to the plate and that the mass concentration of dust is small. Formulas are derived in terms of a constant external impulsive velocity field for the velocity profiles of both the dust and the conducting gas only for values of Hartmann number greater than or equal to unity. For these values of the Hartmann number the skin friction is also obtained.     

三维横向流体诱发直管振动的数值模拟

基于有限体积法和有限元法,结合动网格控制技术,建立了横向流体作用下三维弹性直管流致振动计算的数值模型,实现了计算结构动力学与计算流体力学之间的联合仿真．首先,通过对刚性管的静止绕流计算,研究了网格离散方式和不同湍流模型对圆柱类结构静止绕流流场特征的影响和预测能力,得到了适用于双向耦合分析的CFD模型;其次,利用基于双向流固耦合方法的流致振动模型,计算并分析了流体力与结构位移间的相位关系,指出流体力与位移间的相位差是由流体力引起的,同时对双向耦合和单向耦合进行了比较分析;最后通过对直管流致振动的数值计算,联合管表面压力、尾流区时均速度、分离角等时均量,分析了尾流区的流场特征.     

Flow over a profile in a channel with dynamical effects

The work deals with a numerical solution of 2D inviscid incompressible flow over the profile NACA 0012 in a channel. The finite volume method in a form of cell‐centered scheme at quadrilateral C‐mesh is used. Governing system of equations is the system of Euler equations. Numerical results are partially compared with experimental data. Steady state solutions of the flow as well unsteady flows caused by prescribed oscillation of the profile were computed. The method of artificial compressibility and the time dependent method are used for computation of the steady state solution. (© 2004 WILEY‐VCH Verlag GmbH & Co. KGaA, Weinheim)     

Computed oscillations of a confined submerged liquid jet

The jet oscillation observed in thin slab continuous casting is studied numerically by modelling the flow of liquid injected through a submerged entry nozzle and into a cavity. The oscillation relies on the exchange of fluid between recirculation cells on each side of the jet via a cross-flow through the gap between the nozzle shaft and the broad face of the cavity wall. Features of the oscillating jet are investigated by varying the resistance to cross-flow. This resistance occurs naturally since the nozzle obstructs cross-flow. The predicted oscillation can be manipulated by altering the cross-flow (through the use of an effective resistance force in the model) or stopped altogether to form a static asymmetrical flow pattern. Flow calculations are performed using a transient, two-dimensional, turbulent, fluid flow model.