固体火箭发动机喷管两相流场与结构温度场一体化数值模拟与软件实现

为准确、高效地进行固体火箭发动机的喷管结构设计与性能分析,考虑两相流场和结构温度场之间的相互影响,采用有限差分方法求解二维轴对称两相欧拉方程组,进行喷管气体-颗粒两相无黏流动数值模拟;采用有限元法求解二维轴对称瞬态导热微分方程,进行喷管复合结构温度场数值模拟;根据面向对象编程思想,采用VC+ +以人机交互的工作方式实现喷管内型面和结构设计,并完成有限差分网格和有限元网格的自动划分和显示;通过数值模拟方法与面向对象软件设计方法的有效结合,实现二维轴对称喷管两相无黏流场和复合结构温度场的一体化数值模拟. 数值模拟结果表明,该方法有助于在统一的软件平台上充分利用计算机辅助技术完成喷管性能与结构的综合评估,可以用于固体火箭发动机喷管的工程设计.     

结构化多重网格粘性流场数值模拟

流体力学控制方程的数值求解过程中,当网格加密或者粘性效应强的时候,流场收敛非常缓慢.为了解决计算的效率问题,在结构网格的基础上采用多重网格技术,模拟了二维RAE2822超临界翼型的亚音速绕流及三维M6机翼跨音速流场,仿真结果表明,采用多重网格方法在二维,三维粘性流场的计算结果都与实验结果吻合良好,与不采用多重网格方法比较,在求解中获得了相当满意的加速收敛效果.还比较了两种不同循环方式:V循环,W循环的加速效率,为多重网格的工程应用奠下基础.     

连续热镀锌线气刀吹锌过程中锌波纹产生的大涡模拟

为寻求连续热镀锌线气刀吹锌过程中带钢上出现锌波纹的原因,采用大涡模拟（Large Eddy Simulation,LES）方法数值求解三维非稳态气刀射流湍流流场,并结合带钢表面的镀锌层厚度的零维预测模型研究锌波纹产生的机理．结果表明,在气刀射流冲击区域两侧有交替成对出现的漩涡,造成带钢表面的压强和切应力周期性波动分布,从而产生锌波纹．     

GPU通用计算在LBM方法中的应用

提出了一种结合GPU通用计算与计算流体力学中的LBM算法来模拟二维流场的方法.根据GPU通用计算和LBM方法的基本原理,利用OpenGL的离屏渲染技术FBO和Cg语言,基于LBM方法中的D2Q9模型对二维方腔流进行数值模拟,并设计出基于OpenGL的GPU通用计算的二维流场数值计算框架.实验结果表明,利用GPU模拟与CPU模拟流场的数值结果相当吻合,特别地,利用GPU进行数值模拟实验的速度是利用CPU的4倍左右.     

带炮口装置时某火炮膛口流场数值仿真

研究炮口装置能控制火药气体从膛口流出后的流动状态,可以改变身管受力及膛口流场射流结构分布状况,对火炮武器系统性能有重要影响。为研究某新型炮口装置性能及其对弹丸运动影响问题,提高精度,采用计算流体力学结合动网格技术,建立了包含炮口装置和运动弹丸的膛口流场数值仿真模型,利用轴对称Euler方程组和有限体积法(FVM),对带炮口装置的某火炮膛口流场进行了数值仿真。仿真结果反映了带炮口装置时膛口流场发展过程及射流结构的主要特征。根据数值仿真结果分析了膛口流场对弹丸受力状况及运动状态的影响。仿真结果表明某新型炮口装置对膛口流场结构有较大影响,并会影响弹丸出炮口后运动状态,从而影响火炮射击精度。     

脉冲防暴水炮近流场的数值模拟

为研究脉冲防暴水炮非稳态气液两相射流的雾化机理,采用一方程大涡模拟耦合有界压缩型VOF方法构建数值计算模型,对近流场进行数值模拟。从喷雾形态看,由数值模拟得到的气液两相界面分布图与近流场的高速摄影图像相符程度较高。对两者进行分析比较后发现,在近流场中高压气体膨胀为射流发展的主要动因。     

阻力伞流场数值模拟

运用非定常Navier-Stokes(N-S)方程有限体积算法及非结构动网格技术对X-37B飞行器着陆流场进行数值模拟,比较了飞行器在拖挂阻力伞和不拖挂阻力伞两种情况下的流场差异.模拟以混合网格有限体积方法为基础,控制体方程采用N-S方程组,流场计算空间离散采用格点格式,通量计算格式采用Roe,时间离散采用LU-SGS理论和二阶时间精度的双时间步长,湍流模型采用两方程SST湍流模型.动网格技术采用线性弹簧理论处理阻力伞在摆动时流场的变化.阻力伞模型采用中间带气孔的C-9圆锥型降落伞外形,但规模有所缩小,以便适应飞行器.模拟比较了两种情况下着陆流场的差别,并主要比较了两种情况下阻力的差别,从而证明飞行器在拖挂阻力伞的情况下更容易减速着陆.     

基于DMD方法的矩形断面涡振模态分析

为探究涡激振动下,矩形断面绕流场的模态演化规律及涡振发生机理,基于雷诺平均SST k-ω模型对宽高比为5∶1的矩形断面的涡激振动进行了二维数值模拟研究.通过CFD/CSD交错迭代求解,结合动网格技术实现了二维流固耦合计算,并与风洞试验结果进行对比分析,验证了数值计算的准确性.随后,对流场的瞬时状态进行可视化分析,以z方向涡量值为基本物理量,基于动力学模态分解(DMD)方法对其静态与涡振态流场模态进行了对比分析.结果表明：在涡振发展的不同阶段,主导流场的模态频率不同,主模态频率会由静态涡脱频率向结构固有频率转变,此主模态的转变表征了流固耦合的内在机制;与静态矩形相比,涡振态矩形由于运动诱导涡的存在,导致其前缘涡与尾缘涡的相位差减小,前缘涡与尾涡而合并时前缘涡占据主导,使得在尾缘脱落的Karman涡相关性减弱,形成了涡振锁频现象.     

基于非结构滑移网格技术的旋翼型无人机空气动力学并行数值模拟方法

在现代飞行器设计中,数值模拟方法以低成本、高效率和高灵活性等优点成为研究飞行器空气动力学的重要方法.在旋翼型无人机流场模拟中,由于旋翼与机身存在相互作用,为获得精确模拟结果需要对整个无人机的流场进行模拟,因此,有效地模拟旋翼与机身的相对运动是实现成功模拟的关键步骤,这使得此类模拟问题极具挑战性.文章设计了一套求解旋翼型无人机空气动力学数值模拟问题的基于非结构滑移网格技术的高可扩展并行计算方法.该方法对控制方程的离散,在空间方向采用非结构移动网格有限元方法,时间推进采用全隐式二阶向后差分格式,最后采用一种并行Newton-Krylov-Schwarz方法求解离散后的非线性方程组.作为应用,文章对一个真实旋翼型无人机模型在悬停状态下的外流场进行了数值模拟,获得了一些非常详细的流场信息.数值结果显示,算法在天河2号上使用4 096个处理器核时仍具有接近线性的并行加速比,这为下一步开展旋翼型无人机的高保真度快速模拟奠定了良好的基础.     

有冲击的受限通道内流场的数值仿真

采用数值模拟的方法对简化后的涡轮叶片冷气通道进行了数值模拟,着重研究端壁对有错排射流冲击的冷气通道的影响.结果表明:通道内的横流把射流推向下游并阻止其冲击到靶面,横流作用对通道下游流场有很大影响;射流的冲击反卷和诱导作用在射流两侧形成方向相反的漩涡,漩涡把靶面部分高速区卷到左右侧壁,甚至达到射流孔板附近,产生较大的速度梯度;上游横流作用使射流下游形成低速区,随着横流的发展低速区逐渐减小,并向射流孔板方向偏移.     

Application of Compact Schemes to Large Eddy Simulation of Turbulent Jets

We present 3-D large eddy simulation (LES) results for a turbulent Mach 0.9 isothermal round jet at a Reynolds number of 100,000 (based on jet nozzle exit conditions and nozzle diameter). Our LES code is part of a Computational Aeroacoustics (CAA) methodology that couples surface integral acoustics techniques such as Kirchhoff's method and the Ffowcs Williams– Hawkings method with LES for the far field noise estimation of turbulent jets. The LES code employs high-order accurate compact differencing together with implicit spatial filtering and state-of-the-art non-reflecting boundary conditions. A localized dynamic Smagorinsky subgrid-scale (SGS) model is used for representing the effects of the unresolved scales on the resolved scales. A computational grid consisting of 12 million points was used in the present simulation. Mean flow results obtained in our simulation are found to be in very good agreement with the available experimental data of jets at similar flow conditions. Furthermore, the near field data provided by the LES is coupled with the Ffowcs Williams–Hawkings method to compute the far field noise. Far field aeroacoustics results are also presented and comparisons are made with experimental measurements of jets at similar flow conditions. The aeroacoustics results are encouraging and suggest further investigation of the effects of inflow conditions on the jet acoustic field.     

Coupled solid (FVM)–fluid (DSMC) simulation of micro-nozzle with unstructured-grid

The flow field and temperature distributions of free molecular micro-electro-thermal resist jet (FMMR) were studied resorting to DSMC–FVM coupled method. Direct simulation Monte Carlo (DSMC) method is the most useful tool to simulate the flow field of FMMR and unstructured grid is suitable for the flow simulation in a complicated region with tilted wall surface. DSMC code based on unstructured grid system was developed and the result was compared with that of structured grid and analytical solution to validate the reliability of the developed code. The DSMC method was then used to simulate the fluid flow in the micro-nozzle (Kn > 0.01) and the temperature distribution in the nozzle wall was obtained by the finite volume method (FVM). The Dirichlet–Neumann method was used to couple the wall heat flux and temperature between flow field and solid area. The effect of different income pressure was studied in detail and the results showed that the temperature of solid area changed drastically at different income pressure, so the commonly-adopted method of pre-setting boundary temperature before simulation was unreasonable.     

Adaptive mesh refinement for chevron nozzle jet flows

In this paper an adaptive mesh generation procedure is presented for improving the resolution of the numerical simulation of a turbulent jet exhausting from a chevron nozzle. This procedure is based on the minimization of a variational integral whose integrand depends on the metric (also called the monitor function) induced by a curvilinear grid generated in the physical domain. Specifically, it leads to solving parabolic equations involving the monitor function, which is carefully designed to resolve the flow gradients, and which, in the present instance, is determined by the time-averaged axial velocity profile within the jet. This mesh redistribution strategy is incorporated into a flow computation code (that solves the compressible three-dimensional Navier-Stokes equations using a prefactored optimized fourth-order compact difference scheme for spatial derivatives and the Beam-Warming method for the time derivative on a multi-block overset grid) and is demonstrated to be efficient and effective.     

Unsteady viscous jet flow into stationary surroundings

The unsteady constant-property uniform pressure flow of a viscous laminar axisymmetric jet into stationary surroundings is analyzed with the aid of the boundary layer approximations and an integral method. Numerical solutions of the resulting non-linear system of equations are presented for the response of an initially steady jet to monotonic mass flow variations which are imposed at the initial axial station of the jet. Significant departures from quasi-steady behaviour arise for sufficiently large streamwise distances and/or rates of change of the boundary conditions. Among these effects are overshoots in mass and momentum flux, a dynamic effect on flow entrainment, and a tendency toward discontinous behavior. The influence of the kinematic viscosity on the transient flow is examined, and an estimate is made of the applicability of quasi-steady approximations in this problem.     

Study of jet precession, recirculation and vortex breakdown in turbulent swirling jets using LES

Large eddy simulations (LES) are used to investigate turbulent isothermal swirling flows with a strong emphasis on vortex breakdown, recirculation and instability behaviour. The Sydney swirl burner configuration is used for all simulated test cases from low to high swirl and Reynolds numbers. The governing equations for continuity and momentum are solved on a structured Cartesian grid, and a Smagorinsky eddy viscosity model with the localised dynamic procedure is used as the sub-grid scale turbulence model. The LES successfully predicts both the upstream first recirculation zone generated by the bluff body and the downstream vortex breakdown bubble. The frequency spectrum indicates the presence of low frequency oscillations and the existence of a central jet precession as observed in experiments. The LES calculations well captured the distinct precession frequencies. The results also highlight the precession mode of instability in the center jet and the oscillations of the central jet precession, which forms a precessing vortex core. The study further highlights the predictive capabilities of LES on unsteady oscillations of turbulent swirling flow fields and provides a good framework for complex instability investigations.     

Computation of a high Reynolds number jet and its radiated noise using large eddy simulation based on explicit filtering

An isothermal circular jet with a Mach number of M = 0.9 and a Reynolds number of Re_D = 4 × 10⁵ is computed by compressible large eddy simulation (LES). The LES is carried out using an explicit filtering to damp the scales discretized by less than four grid points without affecting the resolved large scales. The jet features are thus found not to appreciably depend on the filtering procedure. The flow development is also shown from simulations on different grids to be independent of the location of the grid boundaries. The flow and the sound field obtained directly by LES are compared to measurements of the literature. The acoustic radiation especially displays spectra and azimuthal correlation functions which behave according to the observation angle as expected for a high Reynolds number. Furthermore the two components of jet noise usually associated to large structures and to fine-scale turbulence, respectively, are apparently found.     

Starting jet flows in a three-dimensional channel with larynx-shaped constriction

A numerical model for the three-dimensional starting jet flow in a channel with a static larynx-shaped constriction is presented. Detailed resolution of this kind of jet flow is necessary in order to understand the complex coupling between flow and acoustics in the process of human phonation. The numerical model is based on the equation of continuity and the Navier–Stokes equations. The investigations are done with the open source CFD package OpenFOAM. Numerical simulations are performed for a square-sectioned channel geometry, which is constricted with a fixed shape conforming to the fully opened human glottis. Time-dependent inflow boundary conditions are applied in order to model transient glottal flow rates. The setup of the numerical simulations corresponds to the configuration of a model experiment in order to allow detailed validation. The numerical results are in good agreement with the experimental data, when the near-wall region in the glottal gap is adequately resolved by the numerical grid. The results illustrate the complex interactions between the jet flow and the surrounding vortices.     

Norm驱动的网格工作流状态机模型

动态的网格环境赋予了网格工作流新的特征。从而进一步增加了工作流程的不确定性和复杂性．提出了Norm驱动的网格工作流状态机模型——GridWSM,利用Norm丰富的语义表达能力和适于描述复杂系统的特征来描述网格工作流系统中任务的动态调度,并利用其推理功能来完善Norm描述、检验Norm的语义冲突,不仅确保了Norm描述的完备性,而且反映了工作流程的实时变化,为系统仿真提供了理论基础．模型的原型系统NormTools验证了网格排序流程的Norm描述,检查出所有的错误．     

Nonet-Cartesian Grid Method for Shock Flow Computations

A nonet-Cartesian grid method, based on anisotropic/isotropic refinement, is presented for solving the Euler equations in gas dynamic problems. Grids are generated automatically, by the recursive subdivision of a single cell into nine subcells for isotropic nonet-Cartesian grids and into three subcells independently in each direction for anisotropic nonet-Cartesian grids, encompassing the entire flow domain. The grid generation method is applied here to steady inviscid shock flow computation. A finite difference formulation for the Euler equation using nonet-Cartesian grids is used to treat complex two-dimensional configuration. Results using this approach are shown to be competitive with other methods. Further, it is demonstrated that this method provides a simple and accurate procedure for solving flow problems involving multielement airfoils.     

超高压微射流撞击壁面流动特性仿真研究

研究了超高压微射流撞击壁面动力特性优化控制问题,使微射流能最大限度地保持高压能量。为此提出一种集微射流、超高压技术和撞击流三者优势于一体的制备微乳液的新方法,针对超高压下微射流撞击壁面的流场基础研究数据缺乏的问题,分别用三种湍流模型:标准k-ε模型、RNG k-ε模型、Realizable模型对三个截面进行了计算,进行分析比较优缺点以及对超高压微射流撞击壁面流场的适用程度。仿真结果表明,高速射流的撞击会产生巨大破碎作用。通过对喷嘴出口到壁面的速度和动压的结果分析,最佳的距离能获得最大的碰撞能量,有效地解决了喷嘴出口到壁面距离的优化,以便得到更好的粉碎效果,为射流撞击动力学的研究提供了依据。