含灰气体激波沿平壁传播时诱导的边界层流动*

本文研究合灰气体激波沿平直壁面传播过程中在壁面附近形成的层流边界层流动。我们依照双连续介质双向耦合模型处理含灰气体激波的波后流动及其诱导的边界层问题,控制方程采用有限差分方法数值求解,给出了激波下游两相流场特性并考虑了含灰气体激波的松弛结构对边界层流动的影响。     

稀相气固悬浮体越过沿平面匀速运动激波后的流动结构*

本文给出气固悬浮体中激波感生边界层的渐近数值分析,其中计及了作用于固体粒子的Saf-fman升力.研究结果表明粒子横越边界层的迁移导致了粒子轨道的交叉,因此对目前通用的含灰气体模型应做相应的修正.本文利用匹配渐近展开方法得到了匀速运动激波后方的两相侧壁边界层方程,详细描述了在Lagrange坐标下计算颗粒相流动参数的方法,并给出了粒子浓度很低情况下的数值结果.     

一维气液两相漂移模型的AUSMV算法研究

将AUSMV(advection upstream splitting method V)格式从计算气体动力学问题扩展至一维等温瞬态气液两相管流.阐述了采用AUSMV格式构建气液两相漂移模型数值通量的方法及边界单元的处理方法.采用Runge Kutta方法与经典的保单调MUSCL(monotone upstream centred schemes for conservation laws)方法结合Van Leer限制器,构建具有二阶时间和空间精度的数值计算方法.计算经典Zuber-Findlay激波管问题和复杂漂移关系变质量流动问题并与可靠的参考结果进行了对比.分析表明:AUSMV格式应用于气液两相流动漂移模型时计算效率高、精度高、耗散效应和色散效应小,低流速条件下能够精确地描述间断.     

粉尘气体中激波绕射的数值研究*

本文针对稀相气固两相体系,选取双流体耦合模型,综合运用算子分裂技术和高精度高分辨率数值方法,研究了激波在粉尘气体中沿90°拐角的绕射特性,揭示了固相颗粒及其物性改变对激波绕射特征和波后流场结构的影响.     

超声速气流中含灰气体点源流动特性

采用Lagrange方法，研究了超声速气流中含灰气体点源的流动特性，求得了对称轴附近激波层内的流动参数．计算数值模拟结果揭示了大惯性颗粒在激波层内沿着相互交叉的振荡轨迹运动，颗粒分布形成了高、低密度层交错出现的“多层结构”，而且粒子在轨迹包络线附近急剧聚集．     

多项式基函数法

提出一种新型的数值计算方法--基函数法.此方法直接在非结构网格上离散微分算子,采用基函数展开逼近真实函数,构造出了导数的中心格式和迎风格式,取二阶多项式为基函数,并采用通量分裂法及中心格式和迎风格式相结合的技术以消除激波附近的非物理波动,构造出数值求解无粘可压缩流动二阶多项式的基函数格式,通过多个二维无粘超音速和跨音速可压缩流动典型算例的数值计算表明,该方法是一种高精度的、对激波具有高分辨率的无波动新型数值计算方法,与网格自适应技术相结合可得到十分满意的结果.     

一维气液两相漂移模型全隐式AUSMV算法研究

气液两相漂移模型显式AUSMV（advection upstream splitting method combined with flux vector splitting method）算法的时间步长受限于CFL（Courant-Friedrichs-Lewy）条件，为了提高计算效率，建立了一种全隐式AUSMV算法求解气液两相漂移模型.采用AUSM格式结合FVS（flux vector splitting）格式构造连续方程和运动方程的对流项数值通量，AUSM格式构造压力项数值通量.离散控制方程是非线性方程组，采用六阶Newton(牛顿)法结合数值Jacobi矩阵求解.计算经典算例Zuber-Findlay激波管问题和复杂漂移关系变质量流动问题，结果分析表明:全隐式AUSMV算法，色散效应小，无数值震荡，计算精度高.在压力波波速高的条件下，可以显著提高计算效率，耗散效应小.     

两相流的相弛豫理论

本文从三个基本假设出发,提出了两相流的相弛豫理论.对气体-固体微粒两相系,从两相系Boltzmann运动论方程组出发,推导了相弛豫理论的基本方程组;并讨论了基本方程组的性质以及求解方法。分析计算了激波在气体-固体微粒混合物中传播的例子,阐明了强激波弛豫不符合标准指数弛豫律,而是一种动力学弛豫律。最后提出了试验确定固粒群弛豫速率的设想及途径。     

含悬浮固粒射流界面稳定性研究

利用气固两相耦合模型,理论推导出含悬浮固粒射流的稳定性方程,通过数值计算得到了两相射流稳定性特征曲线、固气扰动速度比值幅值曲线及固气相位差曲线,进而得到了关于固粒对流场中扰动增长和传播的影响及失稳过程中固粒扰动特性的结论。这些结论对于两相射流发展的认识和工程实际中实施对两相射流场的人工控制有重要意义。     

基于格子boltzmann方法固井环空介观微间隙气体窜槽研究

固井环空微间隙气体窜槽现象直接影响固井质量与油田生产,准确地描述固井环空微间隙气体窜槽的流动规律是有效控制气体窜槽的核心与"瓶颈"问题.从微观粒子运动角度出发,基于格子Boltzmann方法建立了固井环空微间隙气体粒子流动模型.选取大庆油田某区块计算模拟不同环空压差下微间隙内气体粒子流动速度分布规律,计算结果揭示了固井气窜气体粒子在微环间隙内流动的本质,为后续固井气窜问题的研究开辟新的思路.     

Conditions for shockless state of the vortex flow in two-dimensional laval nozzles : PMM vol. 37, n6, 1973, pp. 1040–1043

Conditions given in [1, 2] for the absence of shocks in the flow in the vicinity of the center of a nozzle for two-dimensional vortex-free flows of an ideal gas are generalized to the case of rotational flows. Both continuous flows and flows with shock waves are constructed.     

The flow of a supersonic ideal gas with “weak” and “strong” shocks over a wedge

The problem of the flow of a uniform supersonic ideal (inviscid and non-heat-conducting) gas over a wedge is considered. If the turning angle of the flow, which is equal to the angle of inclination of the generatrix of the wedge, is less than the maximum value, the problem has two solutions. In the solution with an oblique low-intensity (“weak”) shock, the uniform flow between the shock and the wedge is almost always supersonic. One exception is a small vicinity of the maximum turning angle. For an ideal gas this vicinity does not exceed a fraction of a degree at all Mach numbers. Behind a high-intensity (“strong”) shock, the flow of an ideal gas is always subsonic. “Weak” shocks are observed in all experiments with finite wedges. Some researchers attribute this preference to the “downstream” boundary conditions (“on the right at infinity” for a flow incident on the wedge from the left), and others attribute it to the instability (“Lyapunov” instability) of a flow with a strong shock when it flows over the wedge and to the stability of flow with a weak shock. The results presented below from calculations of the flows that occur for finite wedges within the two-dimensional unsteady Euler equations, when the parameters behind the strong shock are specified on the right-hand boundary, i.e., on the arc of a circle between the wedge and the shock, demonstrate the correctness of the conclusion of the first group of researchers and the incorrectness of the conclusion of the other group. In these calculations, after both small and fairly large perturbations, the flows investigated (which are, in fact, Lyapunov unstable!) return to the solution with a strong shock. In addition, the problem of steady flow over a wedge was regarded as the limit of the two-dimensional non-steady problems at infinite time. Simplification of one of them leads to the problem of the submerged over-expanded supersonic steady outflow. In the ideal gas model this problem is equivalent to flow over a wedge with both weak and strong shocks. All the solutions considered are stable.     

Approximate analytical solutions for strong shocks with variable energy

Approximate analytical solutions are obtained for self-similar flows behind strong shocks with variable energy deposition or withdrawal at the wavefront in a perfect gas at rest with constant initial density. Numerical solutions are also obtained and the approximate solutions agree with these solutions. The effect of the adiabatic index on the solutions is investigated. The dependence of shock density ratio on the parameter characterizing the energy of the flow is studied. It is observed that the rate of deposition of energy at the wavefront decreases with increase of the parameter that specifies the total energy of the flow.     

计算激波的高精度数值方法

在分析了数值解在激波附近产生非物理振荡的原因后,构造了一个三阶迎风紧致格式以及激波的捕捉技术,并且,提出一种称为准装配法的新的激波装配方法.一维流动的数值试验表明,新方法是非常令人满意的.     

Self-similar strong shocks in non-uniform atmosphere

The propagation of strong shocks in an atmosphere of variable density at rest is studied. The energy gain of the flow enveloped by the shock is assumed to be time-dependent. Analytical and numerical solutions of the similarity flows behind such shocks are obtained.     

A Roe-type scheme with low Mach number preconditioning for a two-phase compressible flow model with pressure relaxation

We describe two-phase compressible flows by a hyperbolic six-equation single-velocity two-phase flow model with stiff mechanical relaxation. In particular, we are interested in the simulation of liquid-gas mixtures such as cavitating flows. The model equations are numerically approximated via a fractional step algorithm, which alternates between the solution of the homogeneous hyperbolic portion of the system through Godunov-type finite volume schemes, and the solution of a system of ordinary differential equations that takes into account the pressure relaxation terms. When used in this algorithm, classical schemes such as Roe’s or HLLC prove to be very efficient to simulate the dynamics of transonic and supersonic flows. Unfortunately, these methods suffer from the well known difficulties of loss of accuracy and efficiency for low Mach number regimes encountered by upwind finite volume discretizations. This issue is particularly critical for liquid-gasmixtures due to the large and rapid variation in the flow of the acoustic impedance. To cure the problem of loss of accuracy at low Mach number, in this work we apply to our original Roe-type scheme for the two-phase flow model the Turkel’s preconditioning technique studied by Guillard–Viozat [Computers & Fluids, 28, 1999] for the Roe’s scheme for the classical Euler equations.We present numerical results for a two-dimensional liquid-gas channel flow test that show the effectiveness of the resulting Roe-Turkel method for the two-phase system.     

N-dimensional fractional Fokker-Planck equation and its solutions for anomalous radial two-phase flow in porous media

In this paper we present a time fractional Fokker-Planck equation (fFPE) for radial two-phase flow of liquid and gas in porous media. The fFPE of order α is solved for both two- and three-dimensional flow patterns using the Laplace transform method. The general solutions of the fFPE for both two- and three- dimensional flows are given as a convolution integral of the input and a kernel in the Laplace domain. Special solutions for a large value and a periodic boundary condition are also given in the time domain when the inverse Laplace transform can be found analytically. The fFPE for two-phase flow in porous media presented in this paper is the first report of its kind.     

The fluid-dynamic limit of the Broadwell model of the nonlinear Boltzmann equation in the presence of shocks

This paper studies the asymptotic equivalence of the Broadwell model of the nonlinear Boltzmann equation to its corresponding Euler equation of compressible gas dynamics in the limit of small mean free path ε. It is shown that the fluid dynamical approximation is valid even if there are shocks in the fluid flow, although there are thin shock layers in which the convergence does not hold. More precisely, by assuming that the fluid solution is piecewise smooth with a finite number of noninteracting shocks and suitably small oscillations, we can show that there exist solutions to the Broadwell equations such that the Broadwell solutions converge to the fluid dynamical solutions away from the shocks at a rate of order (ε) as the mean free path ε goes to zero. For the proof, we first construct a formal solution for the Broadwell equation by matching the truncated Hilbert expansion and shock layer expansion. Then the existence of Broadwell solutions and its convergence to the fluid dynamic solution is reduced to the stability analysis for the approximate solution. We use an energy method which makes full use of the inner structure of time dependent shock profiles for the Broadwell equations.