基于近场动力学数值方法的冰-吊舱推进器接触判断研究

吊舱推进器在极地船舶中的应用, 可避免冰区航行中转向、调头困难等操纵问题, 是极地船舶广泛采用的推进形式. 在冰-吊舱推进器切削过程中, 吊舱推进器受到了极端冰载荷的作用, 对吊舱推进器结构强度和极地船舶的安全性带来严重的危害. 为了研究不同操纵状态的吊舱推进器与冰切削时冰载荷的变化规律, 首先, 详细介绍了近场动力学方法研究物体断裂问题的理论基础, 分析该方法模拟冰材料的可行性. 基于近场动力学方法和面元法耦合推导了适用于冰破碎问题模拟的材料破坏准则和冰载荷计算方法. 其次, 提出了不同操纵状态的吊舱推进器与冰的接触判断方法, 建立了冰-吊舱推进器切削状态的数值计算模型, 实现了冰-吊舱推进器切削动态变化过程的数值仿真. 最后, 分析了吊舱推进器在直航、斜航以及操舵状态与冰切削时冰块破碎、螺旋桨和桨叶冰载荷以及吊舱单元整体扭矩的变化情况. 计算结果表明: 本文提出的不同操纵状态的吊舱推进器与冰切削时的接触判断方法能够真实地模拟冰-吊舱推进器的切削过程, 并能获得该过程中冰块的破坏现象和冰载荷变化特性, 可为冰区海洋结构冰载荷数值预报技术的发展、冰区吊舱推进器结构的优化设计和运营提供指导.      

自由面势流问题的域外奇点边界元法及其数值误差分析

讨论了域外奇点边界元法在自由面势流问题计算中的作用，并以连续及离散Fourier分析对该方法(就m阶面元的一般情况)进行数值误差分析，导出了计及面元阶数、奇点至自由面垂向距离、配置点移动、差分格式等因素影响的数值误差一般表达式。从理论上证明了自由面势流问题计算中采用域外奇点法可改善离散产生的数值色散误差并能结合配置点前移(向上游)等方法以数值满足辐射条件。     

回转体局部空泡绕流的非线性分析

基于面元法, 通过在回转体和空泡壁面放置源汇,对回转体定长局部空泡的绕流问题进行了分析和讨论,并提出了求解回转体局部空泡绕流“正问题”的方法。计算结果表明：所给出的方法具有快速收敛的特征,第1次迭代和最终收敛时空泡壁面切向速度的误差不超过5％;随着回转体面元总数N的增加,局部空泡的空泡数σ趋于稳定;通过比较可知,该方法得到的理论估算值与实测值的一致性较好。     

直接边界元法三维自由面兴波时域模拟

应用直接边界元法在时域中求解稳定航速运动的三维自由面兴波问题.基于格林定理,在所有边界面上划分网格,对边界积分方程进行数值离散,采用线性自由面边界条件,随时间步进更新自由面势.由于物体空间位置移动辐射条件不需要单独表述,迭代过程中自由面计算域保持不变.以割划水面NACA0024为例,计算模拟了自由面兴波稳定波形;提出了求解矩阵方程组奇异性的处理方法和解决割划问题的动网格技术.本文计算结果和有限体积法及有关试验结果对比表明,该方法是可靠的.     

自由面势流问题边界元法的数值色散误差

以连续及离散Fourier分析研究自由面势流问题边界元法的数值色散误差,并从理论上探讨有关计算中数值色散误差的改善问题.研究表明:对于该问题的数值色散误差而言,重要的在于以问题相应的离散算子考察计及各种数值手段后的总体色散误差,而非仅考虑该数值手段自身的数值色散误差大小.高阶面元、自由面域外奇点或适当的耦合方法是降低有关问题算子总体色散误差的较好选择.     

用间接边界元方法求解不可压缩孤立翼型绕流的一种库塔条件处理方法

本文对不可压二维翼型势流绕流的边界元法求解作了分析,在对基本方程与边界条件进行数值离散化时,将库塔条件代入基本方程。按本方法编制的计算机程序对若干算例进行了验算。结果表明,本文提出的方法是可靠的,该法计算简捷、方便,占用计算机内存少,具有实用意义。     

泵喷射推进器性能的变分有限元数值分析

由叶轮机械三元流动两类相对流面理论及相对应的变分原理，应用变分有限元数值计算方法，求解泵喷射推进器的水动力特性。文中通过实际算例，求得推进器上转子和定子的力矩值和推力值，并与实验相比较，两者基本吻合，符合设计要求。     

基于Boltzmann模型方程的气体运动论统一算法研究

模型方程出发,研究确立含流态控制参数可描述不同流 域气体流动特征的气体分子速度分布函数方程; 研究发展 气体运动论离散速度坐标法, 借助非定常时间分裂数值计算方法和NND差分格式, 结 合DSMC方法关于分子运动与碰撞去耦技术, 发展直接求解速度分布函数的气体运动论耦合 迭代数值格式; 研制可用于物理空间各点宏观流动取矩的离散速度数值积分方法, 由此提出 一套能有效模拟稀薄流到连续流不同流域气体流动问题统一算法. 通过对不同Knudsen数下 一维激波内流动、二维圆柱、三维球体绕流数值计算表明, 计算结果与有关实验数据及其它 途径研究结果(如DSMC模拟值、N-S数值解)吻合较好, 证实气体运动论统一算法求解各 流域气体流动问题的可行性. 尝试将统一算法进行HPF并行化程序设计, 基于对球体绕流及类 ``神舟'返回舱外形绕流问题进行HPF初步并行试算, 显示出统一算法具有很好的并 行可扩展 性, 可望建立起新型的能有效模拟各流域飞行器绕流HPF并行算法研究方向. 通过将气体运 动论统一算法推广应用于微槽道流动计算研究, 已初步发展起可靠模拟二维短微槽道流动数 值算法; 通过对Couette流、Poiseuille流、压力驱动的二维短槽道流数值模拟, 证实该 算法对微槽道气体流动问题具有较强的模拟能力, 可望发展起基于Boltzmann模型方程能可 靠模拟MEMS微流动问题气体运动论数值计算方法研究途径.     

一种改进的边界元法在弹性扭转问题中的应用

本文用一种改进的边界元法分析与计算了椭圆截面等直杆的扭转问题,并与正规的边界元法的解进行比较,其结果完全一致.然而,改进边界元法较正规边界元法需要准备的数据大大减少,计算时间更加缩短.因此,本文方法对求解 Poisson 方程问题是一种经济而行之有效的数值计算方法.     

基于面元法回转体定长局部空泡的绕流计算

基于面元法 ,通过在回转体和空泡壁面放置源汇 ,对回转体定长局部空泡的绕流问题进行计算和分析 ,并讨论了空泡尾部速度过渡闭合模型对绕流计算的影响。计算结果表明 :本文的方法具有快速收敛的特征 ,第 1次叠代和最终收敛时空泡壁面切向速度的误差不超过 5 % ;随着回转体面元总数N的增加 ,局部空泡的空泡数趋于稳定 ;当回转体线型一定时 ,空泡数将随着局部空泡长度的增大而减小     

Regular wave integral approach to the prediction of hydrodynamic performance of submerged spheroid

A free surface Green function method is employed in numerical simulations of hydrodynamic performance of a submerged spheroid in a fluid of infinite depth. The free surface Green function consists of the Rankine source potential and a singular wave integral. The singularity of the wave integral is removed with the use of the Havelock regular wave integral. The finite boundary element method is applied in the discretisation of the fluid motion problem so that the panel integral of the Rankine source potential is evaluated by the Hess–Smith formula and the panel integral of the regular wave integral is evaluated in a straightforward way due to the regularity nature. Present method’s results are in good agreement with earlier numerical results.     

在Cap-cyclide坐标中Wangerin函数Nmn(ν)的高精度数值计算

在Cap-cyclide坐标中,Wangerin函数Nnm(v)为特征值函数且解析式中包含第一类完全椭圆积分和Jacobi椭圆函数。为实现Wangerin函数Nnm(v)的高精度数值计算,首先利用迭代法对第一类完全椭圆积分进行数值计算,得到的数值解与理论值基本一致;其次利用Jacobi椭圆函数的恒等式实现其数值计算,数值解的有效数字达到了14位以上。基于此,分两个步骤实现Wangerin函数Nnm(v)的高精度数值计算。本文的结论为进一步探讨Wangerin函数的收敛性和稳定性问题提供基础,具有一定的工程实际价值。     

Numerical simulation of fully non-linear steady free surface flow

The fully non-linear free surface potential flow past a 2D non-lifting body is computed. The numerical method is based on the simple layer integral formulation; the non-linear solution is obtained by means of an iterative procedure. Under some hypotheses, viscosity effects at the free surface are considered. All the numerical results obtained have been tested against analytical solutions and experimental results.     

The prediction of 3D transonic flow in turbomachinery using a combined throughflow and blade-to-blade time marching method

A new throughflow calculation method using the time marching numerical technique is presented and compared with other prediction methods for a low hub: tip radius ratio transonic nozzle. It is shown that the accuracy of the method is limited primarily by the assumption of a camberline flow angle in the blade-to-blade plane.

A method which iterates between the meridional and blade-to-blade planes is also presented and it is shown that the predictions compare well with a full 3D theory for a twisted transonic nozzle with high casing flare. Blade surface pressures have been measured experimentally for this case using a transonic annular cascade and the agreement between theory and experiment is found to be good.

Despite the fact that the iterative method is an approximation to the full 3D method, due to the neglect of stream surface twist, it has the advantages that it uses less computer time and storage.     

Axially symmetric cavitation flow at small cavitation numbers

A method for computing the drag coefficient of a body in an axially symmetric, steady-state cavitation flow is presented. A ‘vortex ring’ distribution along the wetted body surface and along the cavity interface is assumed. Since the location of the cavitation interface is unknown a priori, an iterative procedure is used, where, for the first stage, an arbitrary cavitation interface is assumed. The flow field is then solved, and by an iterative process the location of the cavitation interface is corrected. Even though the flow field is governed by the linear Laplace equation, strong non-linearity resulting from the kinematic boundary conditions appears along the cavitation interface. An improved numerical scheme for solving the dual Fredholm integral equations is obtained by formulating high-order approximations to the singular integrals in order to reduce the matrix dimensions. Good agreement is found between the numerical results of the present work, experimental results and other solutions.     

Fluid flow in an arbitrary cascade on an axisymmetric stream surface in a variable thickness layer

A solution is given for the problem of flow past a cascade on an axisymmetric stream surface in a layer of variable thickness, which is a component part of the approximate solution of the three-dimensional problem for a three-dimensional cascade. Generalized analytic functions are used to obtain the integral equation for the potential function, which is solved via iteration method by reduction to a system of linear algebraic equations. An algorithm and a program for the Minsk-2 computer are formulated. The precision of the algorithm is evaluated and results are presented of the calculation of an example cascade.In the formulation of [1, 3] the problem of flow past a three-dimensional turbomachine cascade is reduced approximately to the joint solution of two-dimensional problems of the averaged axisymmetric flow and the flow on an axisymmetric stream surface in an elementary layer of variable thickness.In the following we solve the second problem for an arbitrary cascade with finite thickness rotating with constant angular velocity in ideal fluid flow: the solution is carried out on a Minsk-2 computer.Many studies have been devoted to this problem. A method for solving the direct problem for a cascade of flat plates in a hyperbolic layer was presented in [2]. Methods were developed in [1, 3] for constructing the flow for the case of a channel with variable thickness; these methods are approximately applicable for dense cascades but yield considerable error for small-load turbomachine cascades. The solution developed in [4], somewhat reminiscent of that of [2], is applicable for thin, slightly curved profiles in a layer with monotonically varying thickness. A solution has been given for a circular cascade for layers varying logarithmically [5] and linearly [6]. Approximate methods for slightly curved profiles in a monotonically varying layer with account for layer variability only in the discharge component were examined in [7–9]. A solution is given in [10] for an arbitrary layer by means of the relaxation method, which yields a roughly approximate flow pattern. The general solution of the problem by means of potential theory and the method of singularities presented in [11] is in error because of neglect of the crossflow through the skeletal line. The computer solution of [12] contains an unassessed error for the calculations in an arbitrary layer. The finite difference method is used in [13] to solve the differential equation of flow, which is illustrated by numerical examples for monotonie layers of axial turbomachines. The numerical solution of [13] is very complex.The solution presented below is found in the general formulation with respect to the geometric parameters of the cascade and the axisymmetric surface and also in terms of the layer thickness variation law.The numerical solution requires about 15 minutes of machine time on the Minsk-2 computer.     

A numerical method to solve the m‐terms of a submerged body with forward speed

To model mathematically the problem of a rigid body moving below the free surface, a control surface surrounding the body is introduced. The linear free surface condition of the steady waves created by the moving body is satisfied. To describe the fluid flow outside this surface a potential integral equation is constructed using the Kelvin wave Green function whereas inside the surface, a source integral equation is developed adopting a simple Green function. Source strengths are determined by matching the two integral equations through continuity conditions applied to velocity potential and its normal derivatives along the control surface. After solving for the induced fluid velocity on the body surface and the control surface, an integral equation is derived involving a mixed distribution of sources and dipoles using a simple Green function and one component of the fluid velocity. The normal derivatives of the fluid velocity on the body surface, namely the m‐terms, are then solved by this matching integral equation method (MIEM). Numerical results are presented for two elliptical sections moving at a prescribed Froude number and submerged depth and a sensitivity analysis undertaken to assess the influence of these parameters. Furthermore, comparisons are performed to analyse the impact of different assumptions adopted in the derivation of the m‐terms. It is found that the present method is easy to use in a panel method with satisfactory numerical precision. Copyright © 2002 John Wiley & Sons, Ltd.     

Vortex‐in‐cell method combined with a boundary element method for incompressible viscous flow analysis

In this study, an immersed boundary vortex‐in‐cell (VIC) method for simulating the incompressible flow external to two‐dimensional and three‐dimensional bodies is presented. The vorticity transport equation, which is the governing equation of the VIC method, is represented in a Lagrangian form and solved by the vortex blob representation of the flow field. In the present scheme, the treatment of convection and diffusion is based on the classical fractional step algorithm. The rotational component of the velocity is obtained by solving Poisson's equation using an FFT method on a regular Cartesian grid, and the solenoidal component is determined from solving an integral equation using the panel method for the convection term, and the diffusion term is implemented by a particle strength exchange scheme. Both the no‐slip and no‐through flow conditions associated with the surface boundary condition are satisfied by diffusing vortex sheet and distributing singularities on the body, respectively. The present method is distinguished from other methods by the use of the panel method for the enforcement of the no‐through flow condition. The panel method completes making use of the immersed boundary nature inherent in the VIC method and can be also adopted for the calculation of the pressure field. The overall process is parallelized using message passing interface to manage the extensive computational load in the three‐dimensional flow simulations. Copyright © 2011 John Wiley & Sons, Ltd.