修正SPH方法在自由表面模拟中的应用

对传统光滑粒子动力学(SPH)方法进行修正,提出了一种密度初始化方法,同时采用一种新的固壁边界处理方法,模拟溃坝问题。通过液滴旋转和无透空块体溃坝问题的模拟验证了修正SPH方法的有效性和在自由表面模拟中的准确性,分析了密度初始化对流动的影响;数值结果表明,修正SPH方法提高了数值计算的精度和稳定性。最后应用修正SPH方法模拟了有透空块体和挡板紧挨水柱的溃坝现象,比较了有无透空块体两种情况下右端直墙上压力变化情况,结果表明,透空块体可使右端直墙上的压力减小,有无挡板、挡板位置和水柱长高比对溃坝现象有重要影响。     

基于摄动法的不确定性有限元模型修正方法研究

开展了考虑不确定性的有限元模型修正方法的研究。基于摄动法推导了待修正参数均值和协方差矩阵的迭代格式,其中协方差的迭代格式包括是否考虑试验数据与修正参数之间相关性的两种形式。在理论研究基础上开展数值仿真研究,实现了不确定性有限元模型修正的摄动法,并研究了试验数据样本数量对修正误差的影响。仿真结果表明,该方法适用于解决系统参数与试验数据存在不确定性的模型修正问题,试验样本数量对待修正参数标准差的修正精度影响较大;忽略试验模态参数与待修正参数不确定性之间的相关性,能够避免计算二阶灵敏度矩阵,在保证修正结果准确性的前提下减少计算量。     

融合相似性原理的涡轮叶型流场预测方法研究

计算流体力学(CFD)方法是涡轮叶片等设计阶段性能评估的重要手段.然而,基于CFD的数值仿真方法通常比较耗时,难以满足涡轮叶型设计阶段快速迭代的需求.为实现快速性能评估并克服纯数据驱动预测模型泛化能力不足的问题,受到物理增强的机器学习思路的启发,将相似性原理与深度学习模型相结合,提出了一种泛化能力强的涡轮叶型流场预测新方法.以涡轮叶片表面等熵马赫数分布预测为例,提出采用相似性原理对叶型几何变量和气动参数进行归一化,进而在归一化参数空间构建训练样本集与深度学习预测模型,由此建立统一的流场预测模型,对几何尺寸、边界条件差异较大的叶型气动性能进行评估.在完成模型训练后,对归一化条件下不同工况/不同形状叶型的流场、真实环境下不同工况/不同尺寸叶型的流场以及GE-E³低压涡轮不同截面叶型的流场进行预测,结果表明预测结果的分布曲线与CFD评估结果吻合良好,平均相对误差在1.0%左右,由此验证了所提出的融合相似性原理的流场预测模型的精度与泛化能力.     

一种基于加速度频响函数的动力学模型修正方法

提出了一种基于加速度频响函数的动力学模型修正方法,该方法应用试验测量和计算所得的加速度频响函数矩阵对动力学模型的刚度矩阵、质量矩阵、阻尼系数进行修正,使修正后模型的加速度频响函数与试验测量所得的相一致．该法具有明确的物理意义,数值算例检验了方法的有效性和精度．     

表面裂纹疲劳扩展的数值模拟

建立了一种无形状约束的模拟表面裂纹在线弹性断裂力学条件下疲劳扩展的数值方法,并研究了表面疲劳裂纹形状演化和裂纹尖端应力强度因子(SIF)的分布特征。该方法以三维有限单元技术和Paris疲劳裂纹扩展规律为基础,并在裂纹扩展增量计算中考虑了裂纹闭合影响。本文第一部分主要介绍模拟三维疲劳裂纹扩展的数值方法的理论背景和相关的技术细节。着重分析和讨论基于三维有限单元法计算裂纹SIF所涉及的几个主要问题:裂纹尖端单元网格密度对估算精度的影响;自由表面的影响及其修正方法;裂纹尖端非正交单元网格的影响及修正方法。     

结构动力模型修正技术的发展

在计算机技术飞速发展之前,为了了解航天器在极端载荷情况下的力学行为,通常采用足尺结构星试验的办法.结构星试验方法用于结构的分析和力学行为预测,存在着耗资较大和周期较长的不足.随着数值分析技术的发展,用有限元分析结合模型修正技术代替大型试验已经成为可能.本文评述了自上个世纪70年代末期以来结构动力模型修正技术的发展,包括早期直接对总体矩阵的修正技术,还有从90年代初期发展起来的对矩阵元素或设计参数进行修正的技术.总结了元素型修正方法中的迭代法、优化法以及摄动法,其中包括考虑了试验误差的统计算法和大型复杂结构修正的遗传算法.介绍了模型修正技术中的自由度匹配技术、灵敏度分析技术和对模型修正方法的有效性进行检验的一些经验标准,归纳了目前模型修正技术还需要解决的一些关键技术问题.      

多次透射公式飘移问题的控制方法

多次透射公式(multi-transmitting formula, MTF)是在近场波动数值模拟中一种广泛应用的人工边界条件, 具有形式简单、精度可控和通用性好的优点, 但高阶MTF与有限元方法相结合有时会出现飘移问题. 现有的几种MTF消飘方法往往会显著地影响边界精度, 为此本文提出一种新的消飘因子修正MTF格式, 能够在较高精度水平下实现对飘移问题的有效控制. 该方法保持MTF的一次透射项不变, 仅对各高次透射误差项进行修正, 从而大幅降低了因消飘因子造成的精度损失. 消飘因子设置格式确保在零频和零波数情形下能够满足GKS准则, 从理论上保证了消飘目标的实现. 进一步给出该方法的高阶统一形式, 并将传统的消飘因子修正MTF的方法归结为该统一形式的一个特例. 通过反射系数分析, 证明本文方法不仅具有精度优势, 而且消飘因子选取的适应性更强、取值范围更广. 数值算例表明, 本文的消飘因子对波动能量比较集中的法向和小角度透射波动的模拟精度影响很小, 在控制高阶MTF飘移问题和保持模拟精度方面, 均能够取得明显效果.      

弹性动力学高阶核无关快速多极边界元法

基于核无关的快速多极方法, 发展了一种弹性动力学问题的快速、高精度边界元分析方法. 采用基于二次曲面单元的Nystr?m 离散, 将边界积分方程转化为求和形式, 可以方便地进行加速计算;由于采用二次元, 边界元分析精度很高. 将一种新型快速多极方法用于Nystr?m 边界元法的加速计算, 该方法的数值实现简便、不依赖于积分方程基本解的表达式, 因此通用性很好;该方法还具有最优的计算量和存储量、精度高且可以控制. 结合Nystr?m 边界元系数矩阵和快速多极方法转换矩阵的特点, 提出一种大幅度降低边界元内存消耗的策略. 数值结果表明, 该方法无论在分析精度, 还是计算速度和内存消耗上, 都大大优于同类方法, 是一种快速、通用的工程弹性动力学问题大规模数值分析方法.      

A HIGH ORDER KERNEL INDEPENDENT FAST MULTIPOLE BOUNDARY ELEMENT METHOD FOR ELASTODYNAMICS

基于核无关的快速多极方法, 发展了一种弹性动力学问题的快速、高精度边界元分析方法. 采用基于二次曲面单元的Nyström 离散, 将边界积分方程转化为求和形式, 可以方便地进行加速计算;由于采用二次元, 边界元分析精度很高. 将一种新型快速多极方法用于Nyström 边界元法的加速计算, 该方法的数值实现简便、不依赖于积分方程基本解的表达式, 因此通用性很好;该方法还具有最优的计算量和存储量、精度高且可以控制. 结合Nyström 边界元系数矩阵和快速多极方法转换矩阵的特点, 提出一种大幅度降低边界元内存消耗的策略. 数值结果表明, 该方法无论在分析精度, 还是计算速度和内存消耗上, 都大大优于同类方法, 是一种快速、通用的工程弹性动力学问题大规模数值分析方法.     

先进风力发电机叶型设计

为了提高风力发电机的气动性能,基于SJTU－FOIL叶型选形平台,引入A．Jameson基于控制理论的优化设计方法,开发出一体化设计风机叶片叶型平台。通过对叶型的选形和成功的设计分析,结果显示该平台可为风机设计高效冲动式动叶片叶型提供可靠的技术支待。     

叶片榫头接触应力的求解研究

接触应力分析是不易检测、难于计算，但对于设计又是非常重要的一个难题。文中将实验检测技术与数值计算方法相结合，求解飞机发动机叶片榫头上的接触应力分布。基本思路是：1)用实验检测技术求出叶片榫头接触面上若干点的应力或应变值；2)通过给叶片根部接触面施加一定的约束条件，用数值计算法计算发动机叶片在离心力载荷作用下的全场应力分布，并进一步求出接触面上的接触应力分布；3)解除接触面上的约束条件，代之以计算获得的接触载荷，计算叶片在离心力载荷以及接触载荷共同作用下的全场应力或应变分布，并比较计算结果与实验结果；4)修改约束条件或计算模型，重复上述操作，直至计算结果与实验结果比较一致。研究表明，本文提出的方法能够较准确地给出接触面的载荷分布，判断约束条件的合理性具有简单、易行的特点。由于接触应力的复杂性，本问题还有深入研究的必要。     

Three-Dimensional Calculations of the Flow Field around a Turbine Blade with Film Cooling Injection near the Leading Edge

Injection of coolant air from a showerhead injection system at the leading edge of a high pressure turbine blade is investigated using a fully implicit three-dimensional finite-volume method on multi-block grids. For various blowing rates, the calculation results for the velocity and pressure fields and turbulence intensity are compared with available experimental data. The present method yields excellent agreement with the experiments for the isentropic Mach number distributions on the blade surface. The standardk–ε turbulence model with wall functions is already capable of capturing the major details of the flow field including the injection-induced secondary-flow vortices, particularly so on the suction side. On the pressure side, however, the lateral jet spreading is under-predicted somewhat together with an exaggeration of the near-wall sink-flow vortices. On this side with convex walls, where turbulence anisotropy is appreciable according to the experiments, overall better predictions were obtained with the anisotropy correction of Bergeles et al. [23] promoting the Reynolds stress in the lateral direction. The correction has no beneficial effect on the suction side with concave walls where the turbulence anisotropy was observed to be much smaller. This revised version was published online in July 2006 with corrections to the Cover Date.     

Heat transfer study in rotating cascade using IR thermography and CFD analyses

This paper presents an experimental and CFD numerical study of convective heat transfer in a rotating cascade. Infrared thermography was used to measure surface temperature distribution on a rotating hollow blade, heated internally by secondary air. A CFD numerical model was made according to the actual test rig geometry and operating conditions. Tests were carried out in an iposonic flow regime at relatively low fluid temperatures, with the rotational and Reynolds numbers varied and hot-to-cool air mass flow ratio kept constant. Experimental and numerical results for the blade pressure side are compared in terms of surface temperature 2D distribution and Nusselt number one-dimensional distribution along the blade midspan, providing a reasonable agreement.     

多级轴流压气机叶栅内三维紊流流场的数值模拟

对多级轴流压气机叶栅内三维紊流流场进行数值模拟,采用高精度高分辨率的三阶ENN格式以保证对激波的捕捉和对紊流特征的正确模拟,利用LU-SGS隐式解法提高了计算速度,从而构成了一种既准确又高效的多级跨声速轴流压气机紊流流动数值求解系统。重点研究了动静网格的交接方法及相应的动静交接面处理模型。计算了某带进口导叶的三级轴流压气机,计算结果与实验数据吻合较好。     

Investigation of horizontal-axis wind turbine (HAWT) blade threedimensional rotational effect based on field experiments

Field experiments are performed on a two-bladed 33 kW horizontal-axis wind turbine (HAWT). The pressures are measured with 191 pressure sensors positioned around the surfaces of seven spanwise section airfoils on one of the two blades. Three-dimensional (3D) and two-dimensional (2D) numerical simulations are performed, respectively, on the rotor and the seven airfoils of the blade. The results are compared with the experimental results of the pressure distribution on the seven airfoils and the lift coefficients. The 3D rotational effect on the blade aerodynamic characteristics is then studied with a numerical approach. Finally, some conclusions are drawn as follows. From the tip to the root of the blade, the experimental differential pressure of the blade section airfoil increases at first and then decreases gradually. The calculated 3D result of the pressure distribution on the blade surface is closer to that of the experiment than the 2D result. The 3D rotational effect has a significant impact on the blade surface flow and the aerodynamic load, leading to an increase of the differential pressure on the airfoils and their lift coefficient than that with the 2D one because of the stall delay. The influence of the 3D rotational effect on the wind turbine blade especially takes place on the sections with flow separation.     

Numerical Simulation of the 3D Laminar Viscous Flow on a Horizontal-axis Wind Turbine Blade

The aim of this paper is to describe the methodology followed in order to determine the viscous effects of a uniform wind on the blades of small horizontal-axis wind turbines that rotate at a constant angular speed. The numerical calculation of the development of the three-dimensional boundary layer on the surface of the blades is carried out under laminar conditions and considering flow rotation, airfoil curvature and blade twist effects. The adopted geometry for the twisted blades is given by cambered thin blade sections conformed by circular are airfoils with constant chords. The blade is working under stationary conditions at a given tip speed ratio, so that an extensive laminar boundary layer without flow separation is expected. The boundary layer growth is determined on a non-orthogonal curvilinear coordinate system related to the geometry of the blade surface. Since the thickness of the boundary layer grows from the leading edge of the blade and also from the tip to the blade root, a domain transformation is proposed in order to solve the discretized equations in a regular computational 3D domain. The non-linear system of partial differential coupled equations that governs the boundary layer development is numerically solved applying a finite difference technique using the Krause zig-zag scheme. The resulting coupled equations of motion are linearized, leading to a tridiagonal system of equations that is iteratively solved for the velocity components inside the viscous layer applying the Thomas algorithm, procedure that allows the subsequent numerical determination of the shear stress distribution on the blade surface.     

Numerical simulation of blade coating with short dwell and roll application coaters

Paper and board are often coated at high speeds with a mineral-based aqueous suspension in order to improve their printing properties. This suspension is usually called coating colour. The flow behaviour of the coating colour in the cavity of the short dwell coater (SDC) and in the vicinity of the blade tip when paper is coated with a stiff blade has been analysed using the finite element method. The models used to simulate the flow incorporated free surfaces and shear-thinning colours. The Newtonian case was in some cases also included in the modelling. The viscosity level and the shear-thinning character of the coating colour had a significant influence on the flow in the SDC cavity, although the overall behaviour was to a large extent governed by the speed of the coater. The pressure distribution along the paper surface in the SDC cavity was also analysed.In agreement with earlier reported results, increasing the machine speed raised the pressure level in the colour close to the blade tip. The rheological properties of the coating colour also affected the flow field and the pressure distribution in this region; e.g. it was found here that a colour with a high viscosity level at low shear rates developed a high pressure level close to the blade tip. The most interesting result revealed by the analysis was that changes in the configuration close to the blade tip (converging flow between the blade tip and the paper and compression of the substrate under the blade tip) and boundary conditions at the blade tip surface had a very significant effect on the pressure distribution. The predictions of the numerical simulation were to some extent compared with experience from practical coating trials.     

用鲁棒Riemann求解器和运动重叠网格计算旋翼粘性绕流

发展了一种基于鲁棒Riemann求解器和运动重叠网格技术计算直升机悬停旋翼流场的方法。基于惯性坐标系,悬停旋翼流场是非定常流场,控制方程为可压缩Reynolds平均Navier-Stoke方程,其对流项采用Roe近似Reimann求解器离散,使用改进的五阶加权基本无振荡格式进行高阶重构,非定常时间推进采用含牛顿型LUSGS子迭代的全隐式双时间步方法。为实施旋转运动和便于捕捉尾迹,计算采用运动重叠网格技术。计算得到的桨叶表面压力分布及桨尖涡涡核位置都与实验结果吻合较好。数值结果表明:所发展方法对桨尖涡具有较高的分辨率,对激波具有较好的捕捉能力,该方法可进一步推广到前飞旋翼粘性绕流的计算。     

An improved immersed boundary‐lattice Boltzmann method based on force correction technique

In this paper, an improved immersed boundary‐lattice Boltzmann method based on the force correction technique is presented for fluid‐structure interaction problems including the moving boundary interfaces. By introducing a force correction coefficient, the non‐slip boundary conditions are much better enforced compared with the conventional immersed boundary‐lattice Boltzmann methods. In addition, the implicit and iterative calculations are avoided; thus, the computational cost is reduced dramatically. Several numerical experiments are carried out to test the efficiency of the method. It is found that the method has the second‐order accuracy, and the non‐slip boundary conditions are enforced indeed. The numerical results also show that the present method is a suitable tool for fluid‐structure interaction problems involving complex moving boundaries.     

Wet/dry areas method for interfacial (free surface) flow

In this paper, a new numerical method is developed for two‐dimensional interfacial (free surface) flows, based on the control volume method and conservative integral form of the Navier–Stokes equations with a standard staggered grid. The new method deploys two continuity equations, the continuity equation of the mass conservation for better convergence of the implicit scheme and the continuity equation of the volume conservation for the equation of pressure correction. The convection terms (the total momentum flux) on the surfaces of control volume are accurately calculated from the wet area exposed to the water, and the dry area exposed to the air. The numerical results produced by the new numerical method agree very well with the analytical solution, experimental images and experimentally measured velocity. Copyright © 2012 John Wiley & Sons, Ltd.