Study of the Spectral Difference Numerical Dissipation for Turbulent Flows Using Unstructured Grids

In this paper, the numerical dissipation properties of the Spectral Difference (SD) method are studied in the context of vortex dominated flows and wall-bounded turbulence, using uniform and distorted grids. First, the validity of using the SD numerical dissipation as the only source of subgrid dissipation (the so-called Implicit-LES approach) is assessed on regular grids using various polynomial degrees (namely, p = 3, p = 4, p = 5) for the Taylor-Green vortex flow configuration at R e = 5 000. It is shown that the levels of numerical dissipation greatly depend on the order of accuracy chosen and, in turn, lead to an incorrect estimation of the viscous dissipation levels. The influence of grid distortion on the numerical dissipation is then assessed in the context of finite Reynolds number freely-decaying and wall-bounded turbulence. Tests involving different amplitudes of distortion show that highly skewed grids lead to the presence of small-scale, noisy structures, emphasizing the need of explicit subgrid modeling or regularization procedures when considering coarse, high-order SD computations on unstructured grids. Under-resolved, high-order computations of the turbulent channel flow at R e _τ = 1000 using highly-skewed grids are considered as well and present a qualitatively similar agreement to results obtained on a regular grid.     

Modified Multidimensional Dissipation Scheme on Unstructured Meshes for High-speed Compressible Flow Analysis

A Roe's flux-difference splitting scheme, combining with the entropy fix method according to Van Leer et al., and the H-correction entropy fix method by Pandolfi and D'Ambrosio, is proposed. The presented scheme eliminates unphysical flow behaviors such as a spurious bump of the carbuncle phenomenon that occurs on the bow shock from flow over a blunt body, and the expansion shock generated from flow over a forward facing step. The proposed scheme is further extended to obtain high-order spatial and temporal solution accuracy. The scheme is, in addition, combined with an adaptive meshing technique that generates unstructured triangular meshes to resemble the flow phenomena for reducing computational effort. The entire procedure is evaluated by solving several benchmarks as well as complex steady-state and transient high-speed compressible flow problems.     

Evaluation of the Spectral Element Dynamic Model for Large-Eddy Simulation on Unstructured,Deformed Meshes

In this paper, the Spectral-Element Dynamic Model (SEDM), suited for Large-Eddy Simulation (LES) using Discontinuous Finite Element Methods (DFEM), is assessed using unstructured meshes. Five test cases of increasing complexity are considered, namely, the Taylor-Green vortex at Re =?5000, the turbulent channel flow at Re_τ =?587, the circular cylinder in cross-flow at Re_D =?3900, the square cylinder in cross-flow at Re_D =?22400 and the channel with periodic constrictions at Re_h =?10595. Various discretization parameters such as the grid spacing, polynomial degree and numerical flux are assessed and very accurate results are reported in all cases. This consistency in the results demonstrates the versatility of the SEDM approach and its ability to gage the actual resolution and quality of the mesh and, accordingly, to introduce an amount of sub-grid dissipation which is adapted to the spatial discretization considered.     

基于高次广义柔度灵敏度的结构损伤识别

柔度矩阵可以由结构的低价模态近似计算获得,因此被广泛用于结构的模型修正和损伤识别中.由普通柔度派生而来的广义柔度,可以由低价模态数据更加精确的获得,且随着广义柔度次数的增高其精度越高,往往只需要第一或二阶模态数据即可获得很准确的高次广义柔度.因此,广义柔度灵敏度方法自提出以来受到广泛关注.论文详细研究了基于高次广义柔度灵敏度的损伤识别计算方法,研究中发现,利用广义柔度灵敏度进行损伤识别计算时,并非越高次的广义柔度其识别结果越准确,随着广义柔度次数的增加,损伤识别结果精度呈现出先提高但随后显著降低的趋势.究其原因在于,虽然随着广义柔度次数的增加,广义柔度本身的精度更高,但与之相应的灵敏度方程组系数矩阵的条件数却也显著增大了,即方程组的病态性反而更加严重了,这导致了基于高次广义柔度计算所得的损伤参数的精度反而不如低次广义柔度的情况.因此,论文的研究表明,工程中利用广义柔度进行模型修正或损伤识别时,一般采用一次广义柔度或二次广义柔度即可,且计算中为了克服方程组的病态性和数据噪声的不利影响,论文提出了一种反馈奇异值截断法,能够明显提高计算精度,获得较准确的识别结果.     

High-order LES of turbulent heat transfer in a rotor–stator cavity

The present work examines the turbulent flow in an enclosed rotor–stator system subjected to heat transfer effects. Besides their fundamental importance as three-dimensional prototype flows, such flows arise in many industrial applications but also in many geophysical and astrophysical settings. Large eddy simulations (LES) are here performed using a spectral vanishing viscosity technique. The LES results have already been favorably compared to velocity measurements in the isothermal case (Séverac, E., Poncet, S., Serre, E., Chauve, M.P., 2007. Large eddy simulation and measurements of turbulent enclosed rotor–stator flows. Phys. Fluids, 19, 085113) for a large range of Reynolds numbers 10⁵Re=Ωb²/ν10⁶, in an annular cavity of large aspect ratio G=(b-a)/H=5 and weak curvature parameter R_m=(b-a)/(b+a)=1.8 (a,b the inner and outer radii of the rotor and H the interdisk spacing). The purpose of this paper is to extend these previous results in the non-isothermal case using the Boussinesq approximation to take into account the buoyancy effects. Thus, the effects of thermal convection have been examined for a turbulent flow Re=10⁶ of air in the same rotor–stator system for Rayleigh numbers up to Ra=10⁸. These LES results provide accurate, instantaneous quantities which are of interest in understanding the physics of turbulent flows and heat transfers in an interdisk cavity. Even at high Rayleigh numbers, the structure of the iso-values of the instantaneous normal temperature gradient at the disk surfaces resembles the one of the iso-values of the tangential velocity with large spiral arms along the rotor and more thin structures along the stator. The averaged results show small effects of density variation on the mean and turbulent fields. The turbulent Prandtl number is a decreasing function of the distance to the wall with 1.4 close to the disks and about 0.3 in the outer layers. The local Nusselt number is found to be proportional to the local Reynolds number to the power 0.7. The evolution of the averaged Bolgiano length scale L_B with the Rayleigh number indicates that temperature fluctuations may have a large influence on the dynamics only at the largest scales of the system for Ra10⁷, since L_B remains lower than the thermal boundary layer thicknesses.     

Higher-order Upwind Distribution-formula Scheme for Structured and Unstructured Adaptive Flow Solvers

The development of inviscid and viscous flow solvers for both structured and unstructured meshes is presented in this paper. The solution method is the distribution-formula scheme. This is an explicit, cell-vertex, finite volume method which is essentially second-order accurate in both space and time. The Euler and Navier-Stokes equations are integrated over each finite volume cell to determine the change in flow properties (e.g. density) for the cell. Distribution formulas are then used to distribute such changes to the surrounding vertices. Increments in each vertex (which is a calculation point) thus consist of contributions from the surrounding cells. The original discretization technique involves central differencing and is simple, robust and computationally efficient. In this work, starting with inviscid flow simulations using the original scheme on structured grids, improvements are subsequently made to the scheme by replacing the central differencing portion with MUSCL type higher-order upwind differencing. Numerical investigations with the improved scheme are performed using inviscid flow simulations on structured grids. Upon establishing improved accuracy, stability and excellent shock capturing properties, further extension to viscous flow computations on unstructured adaptive meshes is implemented. Results are presented for laminar, viscous flow over a NACA 0012 airfoil.     

采用NND方法计算三维喷管气流场

本文运用NND显式差分格式,计算了三维喷管气流场。气流场计算的基本方程为一般贴体坐标系下三维守恒型的欧拉方程。采用了时间分裂法和Steger-Warming矢通量分裂技术。在喷管内沿周向的每个由轴线和壁面构成的子午面上根据泊松方程生成贴体网格。本文运用三维程序计算了轴对称JPL喷管,同时与实验结果和前人采用轴对称二维程序所计算的结果做了对比。最后,本文还计算了三维矢量喷管,计算结果与现有的实验结果一致。通过轴对称JPL喷管和三维矢量喷管的计算考核,表明建立的算法和编写的计算程序是正确的。文中提出了采用子午面形式的贴体网格时奇性轴的处理方法。计算结果表明在喷管壁面处,马赫数与压强的计算结果与实验值吻合较好,而在喷管轴线处,只有当网格较密时,才能得出与实验结果接近的计算结果。     

A Hybrid Domain Decomposition and Multigrid Method for the Acceleration of Compressible Viscous Flow Calculations on Unstructured Triangular Meshes

This paper is concerned with the formulation and the evaluation of a hybrid solution method that makes use of domain decomposition and multigrid principles for the calculation of two-dimensional compressible viscous flows on unstructured triangular meshes. More precisely, a non-overlapping additive domain decomposition method is used to coordinate concurrent subdomain solutions with a multigrid method. This hybrid method is developed in the context of a flow solver for the Navier-Stokes equations which is based on a combined finite element/finite volume formulation on unstructured triangular meshes. Time integration of the resulting semi-discrete equations is performed using a linearized backward Euler implicit scheme. As a result, each pseudo time step requires the solution of a sparse linear system. In this study, a non-overlapping domain decomposition algorithm is used for advancing the solution at each implicit time step. Algebraically, the Schwarz algorithm is equivalent to a Jacobi iteration on a linear system whose matrix has a block structure. A substructuring technique can be applied to this matrix in order to obtain a fully implicit scheme in terms of interface unknowns. In the present approach, the interface unknowns are numerical fluxes. The interface system is solved by means of a full GMRES method. Here, the local system solves that are induced by matrix-vector products with the interface operator, are performed using a multigrid by volume agglomeration method. The resulting hybrid domain decomposition and multigrid solver is applied to the computation of several steady flows around a geometry of NACA0012 airfoil.     

An Accurate Finite Difference Scheme for Boussinesq Equations

In this paper, a stable and accurate finite difference scheme using a space-staggered grid is proposed for solving the extended Boussinesq-type equations as derived by Nwogu [Journal of Waterway, Port Coastal and Ocean Engineering, ASCE, 119, (1993) 618–638]. The alternate direction iterative method combined with an efficient predictor–corrector scheme is adopted for the numerical solution of the governing differential equations. The proposed method is verified by two test cases where experimental data are available for comparison. The first case is wave focusing by bottom topography as studied by Whalin [The limit of applicability of linear wave refraction theory in a convergence zone. Res. Rep. H-71-3, U.S.Army Corps of Engrs. Waterways Expt. Station, Vicksburg (1971)]. The second case is wave runup around a circular cylinder as investigated experimentally by Isaacson (Journal of the Waterway, Port, Coastal and Ocean Division, ASCE, 104, (1978), 69–79). Numerical results agree very well with the corresponding experimental data in both cases.     

High-order Finite Difference and Finite Volume WENO Schemes and Discontinuous Galerkin Methods for CFD

In recent years, high order numerical methods have been widely used in computational fluid dynamics (CFD), to effectively resolve complex flow features using meshes which are reasonable for today's computers. In this paper, we review and compare three types of high order methods being used in CFD, namely the weighted essentially non-oscillatory (WENO) finite difference methods, the WENO finite volume methods, and the discontinuous Galerkin (DG) finite element methods. We summarize the main features of these methods, from a practical user's point of view, indicate their applicability and relative strength, and show a few selected numerical examples to demonstrate their performance on illustrative model CFD problems.     

Study of Flow and Mixing in a Generic GT Combustor Using LES

While the basic capability of large eddy simulation (LES) has been amply demonstrated on a number of relatively simple academic configurations, there is still a lack of works applying LES to practical systems also performing detailed quantitative comparisons based on experimental data. In this paper, we tend to approach the simulation of real gas turbine combustor step by step as we first present results of the isothermal LES of a generic gas turbine combustor rig. The available detailed measurements are used to thoroughly validate the LES results. Beyond a pure validation, the LES is used to analyze the influence of the precessing vortex core present in the studied configuration on the mixing of fuel and oxidizer, and possible implications for reacting conditions are discussed.     

Spectral Approximation for Wind Induced Structural Vibration Studies

Abstract. In this paper an efficient procedure for determining spectral moments of arbitrary order of the response of multi-degree-of-freedom (MDOF) linear systems under linearized pressure actions due to wind turbulence is presented. The procedure is initiated by decomposing the n variate incoherent wind field velocity into a sum of n independent totally coherent wind field velocities. Then, the use of a standard discretization procedure for approximating the frequency dependent eigenvalues and eigenvectors of the power spectral density (PSD) matrix leads to a polynomial representation of each component of the PSD matrix. Based on this representation, the spectral moments can be evaluated in a closed form without resorting to numerical quadrature. An illustrative example is included.Sommario. Viene presentata una tecnica utile a determinare i momenti spettrali di qualunque ordine della risposta di sistemi lineari a molti gradi di libertà soggetti all'azione del vento. A tale scopo il campo multivariato di velocità del vento viene decomposto nella somma di campi di velocità totalmente coerenti. A partire da ciò, l'uso di una procedura di discretizzazione per approssimare gli autovalori e gli autovettori della matrice densità spettrale di potenza del vento consente di potere valutare i momenti spettrali in forma chiusa, senza ricorrere all'integrazione numerica.     

Modelling of a Premixed Swirl-stabilized Flame Using a Turbulent Flame Speed Closure Model in LES

This paper proposes a combustion model based on a turbulent flame speed closure (TFC) technique for large eddy simulation (LES) of premixed flames. The model was originally developed for the RANS (Reynolds Averaged Navier Stokes equations) approach and was extended here to LES. The turbulent quantities needed for calculation of the turbulent flame speed are obtained at the sub grid level. This model was at first experienced via an test case and then applied to a typical industrial combustor with a swirl stabilized flame. The paper shows that the model is easy to apply and that the results are promising. Even typical frequencies of arising combustion instabilities can be captured. But, the use of compressible LES may also lead to unphysical pressure waves which have their origin in the numerical treatment of the boundary conditions.     

A Least-Squares Mixed Scheme for the Simulation of Two-Phase Flow in Porous Media on Unstructured Grids

A least-squares mixed formulation is developed for simulation of two-phase flow in porous media. Such problems arise in petroleum applications and ground-water flow. An adaptive strategy based on the element residual as an error indicator is developed in conjunction with unstructured remeshing and tested for the two-phase flow of oil and water. An element-by-element conjugate-gradient scheme (EBE-CG) is compared to a band solution algorithm.     

Calculation of Ship Sinkage and Trim Using a Finite Element Method and Unstructured Grids

An unstructured grid-based, parallel free-surface flow solver has been extended to account for sinkage and trim effects in the calculation of steady ship waves. The overall scheme of the solver combines a finite-element, equal-order, projection-type three-dimensional incompressible flow solver with a finite element, two-dimensional advection equation solver for the free surface equation. The sinkage and trim, wave profiles, and wave drag computed using the present approach are in good agreement with experimental measurements for two hull forms at a wide range of Froude numbers. Numerical predictions indicate significant differences between the wave drag for a ship fixed in at-rest position and free to sink and trim, in agreement with experimental observations.     

A Conservative Difference Scheme for Conservative Differential Equation with Periodic Boundary

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LES of the Sandia Flame D Using Laminar Flamelet Decomposition for Conditional Source-Term Estimation

A variation of the Laminar Flamelet Decomposition (LFD) method for the Conditional Source Term (CSE) model developed by Bushe and Steiner (Phys Fluids 15:1564–1575, 2003) is implemented into an existing LES code. In this approach, the set of basis functions, on which the decomposition is based, is reduced using the mixture fraction dissipation rate as external parameter for the selection. It was found that reducing the basis improves and stabilises the inversion, resulting in reasonably accurate approximation for the average conditional quantities. Some modifications have been introduced to improve the inversion process by reducing the number of flamelets. This modification is found to help stabilize the inversion and keep the dimension of the linear system small. The model is used to simulate the turbulent non-premixed piloted SANDIA Flame D. Reasonably good predictions for conditional and unconditional average variables were found for different planes and at centreline of the flow field. However, an over prediction of the consumption rate in the near field of the flame is found, which may be partially attributed to the use of the Steady Laminar Flamelets (SLF) as functions for the decomposition and the use of a constant boundary condition for the species mass fractions in solving the flamelets. The present simulation of a turbulent reacting jet is the first test of the LFD approach in a realistic scenario using only the temperature field to calculate the inversion. The model is found to be computationally inexpensive.     

Study of an MHD Flow of the Carreau Fluid Flow Over a Stretching Sheet with a Variable Thickness by Using an Implicit Finite Difference Scheme

The present analysis deals with a two-dimensional MHD flow of the Carreau fluid over a stretching sheet with a variable thickness. The governing partial differential equations are converted into an ordinary differential equation by using the similarity approach. The solution of the differential equation is calculated by using the Keller box method. The solution is studied for different values of the Hartmann number, Weissenberg number, wall thickness parameter, and power-law index. The skin friction coefficient is calculated. The present results are compared with available relevant data.     

随机结构静力反应概率密度演化方程的差分方法

随机结构分析的概率密度演化方法是分析随机结构静力反应的一种具有良好前景的方法。本文研究了求解随机结构静力反应概率密度演化方程的差分方法，分别探讨了单边差分格式和Lax-Wendroff格式的计算性态。二者均能满足概率相容性条件并且能够保证均值线性增长。以八层框架结构的静力随机反应为例，对两种差分格式的结果及精确解答进行了具体的比较分析。研究表明，两种差分格式均是收敛和稳定的，在不连续点处存在角点效应．单边差分格式能够保证概率非负性，而Lax-Wendroff格式具有往往更快的收敛速度。就变异系数而言，通常单边差分格式的变异系数随着区间离散数的增长而趋于稳定值，Lax-Wendroff格式则一开始就可得到恒定的值。