复杂外形静动态混合网格生成技术研究新进展

网格生成技术是CFD复杂工程应用的重要环节, 网格质量的好坏直接影响计算结果的精准度, 因此其已成为CFD的重要研究领域.在张涵信院士的指导下, 作者自20世纪90年代初开始开展非结构网格、混合网格技术和相应的计算方法研究, 并逐步发展至动态混合网格技术及非定常计算方法.在张涵信院士80华诞之际, 对近年来作者及团队在网格生成技术及应用方面所取得的进展进行了简要的综述, 分别介绍了静动态混合网格生成、定常/非定常计算方法、网格技术的应用等方面的进展情况.最后, 就网格生成技术目前还存在的问题, 展望了未来的发展方向.作者谨以此文表达对张涵信院士25年来的培养、关怀和帮助的崇高敬意.      

温度体动网格模型中控制参数的研究

采用调整导热系数和源项分布的方式,对温度体动网格模型所生成的网格品质进行控制.温度体动网格模型将运动边界的位移虚拟为求解域的温度边界条件,以流体能量方程或固体导热方程作为控制方程,通过选取不同的导热系数或源项分布可以得到适合不同求解问题需要的温度分布,并将求解得到的网格节点的温度作为其动态位移量.采用温度体动网格模型计算平动、三维旋转运动、柔性体运动等流固耦合计算中可能涉及的动网格算例.结果表明,在计算效率和生成网格的品质方面,与已有的动态网格生成方法相比,具有较大的优势,可以有效解决流固耦合数值模拟中存在的动态网格生成难题.     

基于非结构变形网格的间断装配法原理

在激波捕捉法计算得到的流场基础上采用辨识算法得到初始间断位置, 从ALE方程出发, 考虑离散几何守恒律, 采用变形网格和网格重构技术解决计算过程中间断运动和变形, 新旧网格之间流场采用高精度信息传递方法保持时间精度, 建立了基于非结构动网格技术的间断装配方法.通过激波管问题的二维模拟, 模拟了初始间断分解为激波和接触间断激波遇到固壁反射后与接触间断相交的非定常流动过程, 对这种新方法的基本原理进行了介绍.      

平流层飞艇气动外形优化设计:螺旋桨的影响

建立综合螺旋桨影响的平流层飞艇气动外形优化设计平台.采用Hicks-Henne型函数法参数化艇身轮廓，发展IDW-TFI混合动网格技术实现变形网格高效生成；基于作用盘理论模拟螺旋桨，建立飞艇流场高效数值求解方法.以LOTTE飞艇作为初始外形，阻力系数最小为目标，飞艇体积作为约束条件，通过NLPQL算法寻优获得最佳艇身设计方案.优化后飞艇的尾部形状较平坦，艇身最大横截面位置前移，气动性能得到明显改善，其阻力系数相对于初始外形降低了26.88%.     

含有大位移动边界的复杂流场的数值模拟

含有运动弹丸的膛口流场是典型的大位移动边界问题,同时弹丸在出膛过程中,流场的结构也会发生变化,增加了流场的复杂程度.在对该流场的数值模拟中,将它分为两个区:弹丸运动区和普通流场区,它们之间用一个特殊的分区边界联系,同时运用网格局部重构技术处理弹丸运动造成的网格变形问题,并将对称轴定义为网格变形边界,使得弹丸在对称轴上运动过程中不会导致对称轴上的网格体积为负.从计算结果可以看出整个膛口波系结构变化过程和弹丸先加速后减速的过程,从而表明该动网格处理方法是成功的.     

一种非结构/结构多层混合网格方法及其应用

对于粘性绕流的数值模拟,在自适应直角网格基础上,结合三角形非结构网格和结构化网格,利用其各自的优势和特点,提出一种生成混合杂交网格的思路和方法.在物面附近生成适合粘性流计算的大长宽比结构化网格,在远场分布自适应直角网格,快速离散计算空间.对于复杂的多体问题,采用三角形网格来连接各体网格,并运用网格合并的方法,保证各网格之间的光滑过渡与连接,提高网格质量.针对一些二维、三维外形的绕流问题,在上述网格基础上,采用B-L代数湍流模型和中心有限体积法,完成Navier-Stokes和Euler方程数值模拟的对比计算,结果表明网格生成和流场计算是正确的.     

非结构网格的并行生成

研究了非结构网格的并行生成方法.改进了R.Lohner的"波阵面"区域分裂算法以使子网格及其边界更有益于网格并行生成,提出了边界并行优化策略,改善了边界的光滑性;完善了子区域内生成网格时接受新点及新单元的条件,在界面网格生成过程中提出只接受新单元而拒绝新点的策略,节省了机时.     

基于CFD/CSD的舵面控制气动弹性数值模拟方法

在动态网格上通过耦合求解流动控制方程和结构动力学方程, 发展了一种舵面控制下飞行器运动响应过程中气动弹性数值模拟研究方法.流动控制方程采用N-S方程, 结构动力学采用线性模态叠加方法, 其中流动控制方程空间离散采用基于非结构网格的有限体积方法, 对流通量采用计算HLLC格式, 非定常时间离散采用基于LU-SGS的双时间步长方法.模拟中, 气动运动和结构变形在双时间步长方法推进过程中采用改进松耦合方法, 气动网格与结构网格之间信息交换采用无限平板样条法实现, 飞行器的运动和变形采用基于重叠网格和Delaunay图映射变形网格相结合的方法进行处理.采用多个考核算例对发展的数值方法进行考核验证, 结果表明该方法可以高效精确模拟舵面开环控制下飞行器运动响应过程中的气动弹性特性.      

包含动边界的非定常流场动网格数值模拟

发展建立了用于多体分离等包含动边界的非定常流场数值模拟方法,建立了笛卡尔坐标系下边界以任意速度运动的控制体上的流动控制方程,结合几何守恒律确定网格速度,发展了基于结构网格的动网格方法,网格移动量采用加权插值方法得到.通过数值模拟二维翼型及三维机翼的强迫振荡非定常流场,表明该方法可以数值模拟包含动边界的非定常流场.     

非结构混合网格上的NS方程求解方法

提出了一套较为通用的,完全自动化的非结构混合网格生成方法.在物面粘性作用区,采用一种改进的推进层方法生成三棱柱形和金字塔形网格;在其他流动区域采用阵面推进方法生成四面体网格.采用一种改进精度的格心有限体积法对三维NS方程进行了求解,在加速收敛措施方面,提出了一种新的当地时间步长取定方法来减小质量较差的网格单元对流场计算稳定性和收敛速度的不利影响.以M6机翼和DLR/F4翼身组合体外形的粘性流场作为数值算例,验证了上述网格生成和流场求解方法的正确性和实用性.     

Provably stable overset grid methods for computational aeroacoustics

The simulation of sound generating flows in complex geometries requires accurate numerical methods that are non-dissipative and stable, and well-posed boundary conditions. A structured mesh approach is often desired for a higher-order discretization that better uses the provided grids, but at the expense of complex geometry capabilities relative to techniques for unstructured grids. One solution is to use an overset mesh-based discretization where locally structured meshes are globally assembled in an unstructured manner. This article discusses recent advancements in overset methods, also called Chimera methods, concerning boundary conditions, parallel methods for overset grid management, and stable and accurate interpolation between the grids. Several examples are given, some of which include moving grids.     

子母弹多体分离过程的非定常CFD/RBD数值仿真

为研究子母弹在抛撒时的干扰流场特性,选取多舱段子母弹为计算模型,基于课题组自主开发的非结构混合网格Reynolds平均Navier-Stokes方程求解程序HUNS3D,结合非结构嵌套网格技术,耦合六自由度刚体运动学方程,使用了改进的4阶Adams预估-校正法求解六自由度刚体运动方程.利用跨声速下典型外挂物分离作为验证算例,仿真结果与实验结果高度拟合,验证了求解器的精度.对锁定母弹自由度和释放母弹的自由度两种计算状态进行数值模拟.仿真结果表明:由于激波干涉作用,子弹与母弹之间有较强的耦合作用;释放母弹自由度后,子弹的气动力参数发生了较大变化.      

An improved penalty immersed boundary method for fluid–flexible body interaction

An improved penalty immersed boundary (pIB) method has been proposed for simulation of fluid–flexible body interaction problems. In the proposed method, the fluid motion is defined on the Eulerian domain, while the solid motion is described by the Lagrangian variables. To account for the interaction, the flexible body is assumed to be composed of two parts: massive material points and massless material points, which are assumed to be linked closely by a stiff spring with damping. The massive material points are subjected to the elastic force of solid deformation but do not interact with the fluid directly, while the massless material points interact with the fluid by moving with the local fluid velocity. The flow solver and the solid solver are coupled in this framework and are developed separately by different methods. The fractional step method is adopted to solve the incompressible fluid motion on a staggered Cartesian grid, while the finite element method is developed to simulate the solid motion using an unstructured triangular mesh. The interaction force is just the restoring force of the stiff spring with damping, and is spread from the Lagrangian coordinates to the Eulerian grids by a smoothed approximation of the Dirac delta function. In the numerical simulations, we first validate the solid solver by using a vibrating circular ring in vacuum, and a second-order spatial accuracy is observed. Then both two- and three-dimensional simulations of fluid–flexible body interaction are carried out, including a circular disk in a linear shear flow, an elastic circular disk moving through a constricted channel, a spherical capsule in a linear shear flow, and a windsock in a uniform flow. The spatial accuracy is shown to be between first-order and second-order for both the fluid velocities and the solid positions. Comparisons between the numerical results and the theoretical solutions are also presented.     

High-order compact finite-difference methods on general overset grids

This work investigates the coupling of a very high-order finite-difference algorithm for the solution of conservation laws on general curvilinear meshes with overset-grid techniques originally developed to address complex geometric configurations. The solver portion of the algorithm is based on Padé-type compact finite-differences of up to sixth-order, with up to 10th-order filters employed to remove spurious waves generated by grid non-uniformities, boundary conditions and flow non-linearities. The overset-grid approach is utilized as both a domain-decomposition paradigm for implementation of the algorithm on massively parallel machines and as a means for handling geometric complexity in the computational domain. Two key features have been implemented in the current work; the ability of the high-order algorithm to accommodate holes cut in grids by the overset-grid approach, and the use of high-order interpolation at non-coincident grid overlaps. Several high-order/high-accuracy interpolation methods were considered, and a high-order, explicit, non-optimized Lagrangian method was found to be the most accurate and robust for this application. Several two-dimensional benchmark problems were examined to validate the interpolation methods and the overall algorithm. These included grid-to-grid interpolation of analytic test functions, the inviscid convection of a vortex, laminar flow over single- and double-cylinder configurations, and the scattering of acoustic waves from one- and three-cylinder configurations. The employment of the overset-grid techniques, coupled with high-order interpolation at overset boundaries, was found to be an effective way of employing the high-order algorithm for more complex geometries than was previously possible.     

一种求解三维热辐射输运方程的整体预处理迭代方法及并行计算

为三维灰体热辐射输运方程的隐式离散纵标方法发展一个整体预处理迭代方法并研制并行程序。该方法采用组装线性代数方程组策略,同时求出所有离散方向上的辐射强度。借助预处理的Krylov子空间迭代法,避免复杂网格上扫描算法可能遇到的死锁问题,能够提高健壮性和计算效率。空间离散上采用一阶迎风有限体积格式。数值实验测试变形六面体网格上的收敛率、评估预处理迭代方法的性能并计算辐射和物质的耦合问题,给出三维弯管和黑腔问题的模拟结果,验证程序的正确性和方法的适应性。     

基于非结构网格的不可压流动耦合求解器

采用非结构化网格有限容积法求解了不可压N-S方程组,对流项采用GAMMA格式,扩散项采用二阶中心差分格式建立离散方程,用SOAR算法处理压力与速度的耦合关系,得到了一种求解不可压N-S方程的非结构网格耦合求解器。通过方腔顶盖驱动流、后台阶绕流以及方腔自然对流等几个典型的算例,考察了求解器的计算精度及收敛特性,并与SIMPLE算法进行了比较,结果表明该求解器是有效可行的。     

Thermomechanical modeling of regressing heterogeneous solid propellants

A numerical framework based on the generalized finite element method (GFEM) is developed to capture the coupled effects of thermomechanical deformations and thermal gradients on the regression rate of a heterogeneous solid propellant. The thermomechanical formulation is based on a multiplicative split of the deformation gradient and regression of the heterogeneous solid propellant is simulated using the level set method. A spatial mesh convergence study is performed on a non-regressing solid heterogeneous propellant system to examine the consistency of the coupled thermomechanical GFEM solver. The overall accuracy (spatial and temporal) of the coupled thermomechanical solver for regressing solid propellants is obtained from a periodic sandwich propellant configuration, where the effects of thermomechanical deformations on its regression rate is investigated. Finally, the effects of thermomechanical deformations in a regressing two-dimensional heterogeneous propellant pack are studied and time-average regression rates are reported.     

A fluid–structure interaction model of insect flight with flexible wings

We present a fluid–structure interactions (FSI) model of insect flapping flight with flexible wings. This FSI-based model is established by loosely coupling a finite element method (FEM)-based computational structural dynamic (CSD) model and a computational fluid dynamic (CFD)-based insect dynamic flight simulator. The CSD model is developed specifically for insect flapping flight, which is capable to model thin shell structures of insect flexible wings by taking into account the distribution and anisotropy in both wing morphology involving veins, membranes, fibers and density, and in wing material properties of Young’s modulus and Poisson’s ratios. The insect dynamic flight simulator that is based on a multi-block, overset grid, fortified Navier–Stokes solver is capable to integrate modeling of realistic wing-body morphology, realistic flapping-wing and body kinematics, and unsteady aerodynamics in flapping-wing flights. Validation of the FSI-based aerodynamics and structural dynamics in flexible wings is achieved through a set of benchmark tests and comparisons with measurements, which contain a heaving spanwise flexible wing, a heaving chordwise-flexible wing with a rigid teardrop element, and a realistic hawkmoth wing rotating in air. A FSI analysis of hawkmoth hovering with flapping flexible wings is then carried out and discussed with a specific focus on the in-flight deformation of the hawkmoth wings and hovering aerodynamic performances with the flexible and rigid wings. Our results demonstrate the feasibility of the present FSI model in accurately modeling and quantitatively evaluating flexible-wing aerodynamics of insect flapping flight in terms of the aerodynamic forces, the power consumption and the efficiency.     

Dynamic simulation of a tilting-disc valve with clearance in pulsatile channel flow

Abstract  

In this study, a fully coupled fluid–structure interaction (FSI) software system for a pulsatile flow across a moving tilting-disc valve with clearance is developed. Unsteady pulsatile flow coupled with induced valve motion has been examined in details. State-of-the-art computational fluid dynamics (CFD) methods are adopted in the present flow solver development. To account for nonstationary valve motion, the meshes surrounding the valve are generated and updated in each time-marching step using hybrid grid method. A single-degree-of-freedom rotational valve model is integrated simultaneously with the CFD adaptive time-stepping. It is found in the present study that, on both side of the occluder, strong shedding vortices occur and persist in the valve closing phase. These closure vortices show great influence on the prediction of the regurgitate flow characteristics and the subsequent valve opening dynamics as well. Based on the present software system, the results obtained from quasi-steady simulations performed at various instants of interest with prescribed valve motion are critically evaluated to assess whether simplified flow and valve conditions may lead to erroneous conclusions.