激光粉末床熔融成形腔内非稳态流场特性研究

目的 研究激光粉末床熔融(LPBF)中成形腔内保护气的流动规律,获得气流速度脉动和旋涡等流场非稳态特征及其变化规律。方法 利用热线测速计测量腔内的瞬时速度,研究保护气的速度分布及其脉动特性;基于数值模拟方法探究腔内气流形成的旋涡情况,分析涡的分布及其旋转速度;利用烟雾示踪方法对保护气流场进行可视化处理,分析气流的运动过程。结果 腔内气流经历了射流扩散、上下波动、大涡流、汇流等复杂运动过程,气流速度随时间的变化呈明显脉动特征,且气流脉动幅度受位置影响较大,进出风口的平面流速最大可达2.4 m/s,最小为0.25 m/s。同时,气速随平面高度的增大而逐渐减小;腔内存在以纵向大尺度旋涡为主、若干小尺度旋涡共同作用的涡流,由腔内边壁至中心,涡流切向速度呈先上升后下降的趋势,且随入口气速的增大而增大,在切向速度急剧降低的腔体角落、透镜等区域,易形成流动“死区”,导致烟尘颗粒聚集且难以排出,影响构件的高质量成形制造。结论 保护气在LPBF成形腔内形成了复杂的非稳态流动,并以剧烈的速度脉动和多尺度的涡流为典型特征,而针对非恒定的层流、成形腔结构的优化设计仍需进行更深入的研究。     

流体管网非稳态数学模型及水泵的启停过程分析

介绍了流体管网非稳态流动的数学模型，模型将节点流量平衡方程及回路压力平衡方程中的流量和压力参数均表示为时间的函数，可以模拟流体管网系统中非稳态下任意时刻、任意位置的分支流量。最后给出了水泵启／停的计算机模拟算例，并画出了其随时间变化的动态曲线，可为实际工程运行管理提供参考依据，为流体管网非稳态参数模拟提供了有效简便的方法。     

非稳态雷暴冲击风场的瞬态数值模拟

冲击射流是雷暴冲击风场研究中最常用的模拟方法。大部分物理试验和数值模拟都是假定射流速度入口风速不随时间变化,而实际雷暴冲击风的下沉气流速度都是随时间连续变化的。在雷暴冲击风的全生命周期内一般会经历逐渐增大到最大值后再逐渐减小的过程。对于重要的工程结构抗风设计而言,得到雷暴冲击风全生命周期的风速时程信息十分有必要。基于冲击射流三维足尺模型模拟雷暴冲击风风场,在入口处引入一个更符合雷暴冲击风实际演化过程的衰减函数,采用大涡模拟数值分析获得了雷暴冲击风的非稳态风场,并得到其随时间衰减的瞬态演化过程。结果表明,该模拟方法可以较好地再现雷暴冲击风场的非稳态过程,为进一步讨论非稳态雷暴冲击风场中的结构风荷载特性奠定了基础。     

热声系统内交变流动特性的数值模拟

对热声系统中交变流动的声场与流场分布进行了数值模拟,得到了热声谐振管和回热器(板叠)内的压力和速度分布及二者之间的相位关系.数值模拟表明:在谐振管内,在模拟的边界条件下,径向速度分布出现"环形效应",流动分为核心区的完全湍流流动和湍流边界层内的粘性流动;对于水力半径和粘性渗透层深度相当的热声板叠,其内速度分布逐步出现"环形效应",流动介于层流和湍流的过渡区,为过渡态流动,在流道的大部分区域压力和速度振荡的相位差趋向于π/2;对于水力半径和粘性渗透层深度之比较小的热声回热器,其内交变流动的流动特性与稳态流动的相似,速度的径向分布为抛物线形,类似于定常流动的层流速度分布.     

一种非稳态油膜力模型下刚性转子的分岔和混沌特性

从一个由三个函数确定的非稳态油膜力的非线性模型出发,以短轴承支撑的刚性Ｊｅｆｆｃｏｔｔ转子系统作为研究对象,采用短轴承油膜力的解析表达式和数值模拟的方法研究了系统的分岔和混沌特性,并将模拟结果与稳态油膜力模型的模拟结果作了比较,证明了该非线性模型的合理性。     

一种非稳态油膜力模型下转子系统的碰摩分岔分析

采用新的短轴承非稳态油膜力公式和非稳态油膜轴承－转子系统碰摩的刚性约束非光滑模型，通过数值模拟，得到了该系统随转动角频率及油膜特性参数变化发生碰摩的分岔和混沌特性，并与稳态油膜力模型进行比较，数值模拟结果表明，该系统会对临界转速附近的主共振区和超临界转速的油膜振荡区内分别存在碰摩现象，但当超临界转速足够高时碰摩会消失，此外，在高转速时增大油膜粘性可能防止碰摩产生，本文指出新的非稳态非线性油膜力模型呈现一些与以往稳态模型不同的特性，并具有工程实际意义。     

BEPCⅡ电流引线低温端温度非稳态变化理论计算

介绍一种计算电流引线低温端温度非稳态变化的理论计算方法,并将计算结果与大型CFD软件包Fluent6.0的模拟结果进行比较,两者符合良好.采用该方法分析了稳态时的氦气流量对非稳态电流引线冷端温升速度的影响.     

Spoke型超导腔非稳态降温过程模拟与热应力分析

Spoke型超导腔是一种用于中低β加速段的新型超导腔加速结构.使用数值计算方法研究了Spoke型超导腔在非稳态降温过程中的温度分布情况和降温规律,并以此为基础计算了降温过程中的热应力分布情况及其变化规律.结果表明,在降温过程中由于流动不均匀导致Spoke型超导腔温度分布产生了不均匀性,其不均匀程度在降温过程中呈现先迅速...     

微喷管内气体流动特性研究

研究旨在提高微型空间推进器和微型气体涡轮机等微器件的性能。采用硅微加工技术在硅片上制作出矩形截面三维收缩扩张微喷管,喉部宽度为16mm,深度为20mm,收缩比为1.6251。实验测量了不同进出口压比条件下微喷管内氮气流量特性。实验设定进出口压比范围为1.0~5.0,由此出口体积流量范围为0~0.2mL/s,出口截面特征雷诺数小于500。基于两种数值模拟方法(有限体积法和Boltzmann气体动力学方法)对微喷管内部流动特性进行了数值模拟。数值模拟结果与实验结果相吻合。数值模拟结果发现几点不同于宏观流动的异常现象随着压比的提高,声速截面逐渐偏离喉部,向下游区移动,并且下游区的流动不断加速。当压比达到5.0时,出口截面中心区域的马赫数达到1.26。沿程压力分布呈现非线性下降的趋势。这些现象主要是由于相比于常规尺度管道,微小尺度下表面效应引起的粘性附面层效应和三维效应更显著。     

GFRP拉挤成型工艺模拟优化

为了对GFRP (玻璃纤维增强塑料) 拉挤成型非稳态温度场与固化度进行数值模拟, 依据固化动力学和非稳态导热理论, 建立了温度场和固化度动力学模型。通过 DSC试验分析确定了模型中固化度动力学参数。利用有限元与有限差分相结合的方法, 建立温度场和固化度数值模型, 应用Euler-Cauch逐步迭代法实现计算机解耦。利用有限元软件FEPG编制拉挤固化模拟程序, 详细探讨了模具温度、拉挤速度、初始温度等拉挤工艺参数对模具内温度和固化度分布的影响。数值模拟值与FBG光栅测量值比较结果吻合, 能够对拉挤工艺参数制定提供有用的信息, 以指导拉挤工艺制定。      

Flows of inelastic non-Newtonian fluids through arrays of aligned cylinders. Part 1. Creeping flows

Numerical simulations are presented for flows of inelastic non-Newtonian fluids through periodic arrays of aligned cylinders, for cases in which fluid inertia can be neglected. The truncated power-law fluid model is used to define the relationship between the viscous stress and the rate-of-strain tensor. The flow is shown to be dominated by shear effects, not extension. Numerical simulation results are presented for the drag coefficient of the cylinders and the velocity variance components, and are compared against asymptotically valid analytical results. Square and hexagonal arrays are considered, both for crossflow in the plane perpendicular to the alignment vector of the cylinders (flows along the axes of the array as well as off-axis flows), and for flow along the cylinders. It is shown that the observed strong dependence of the drag coefficient on the power-law index (through which the stress tensor is related to the rate-of-strain tensor) can be described at all solid area fractions by scaling the drag on a cylinder with appropriate velocity and length scales. The velocity variance components show only a weak dependence on the power-law index. The results for steady-state drag and velocity variances are used in an approximate theory for flows accelerated from rest. The numerical simulation data for unsteady flows agree very well with the approximate theory.     

叶栅内非定常不可压流动的数值模拟

基于SMAC(SimplifiedMarkerandCell)方法推导出直接求解二维非定常、不可压N-S方程的隐式数值方法。求解的基本方程是任意曲线坐标系中以逆变速度为变量的N-S方程和椭圆型的压力Poisson方程。采用该方法,对二维叶栅非定常分离流场进行了数值模拟,叶栅表面压力的计算结果与试验结果相比比较吻合,从而验证了这种方法的可靠性。同时对叶栅非定常流场的流场结构和流动机理做了初步的探讨。在均匀来流和定常边界条件下,叶栅内部流动表现出强烈的非定常性;在小冲角和高雷诺数时,叶栅尾部产生类似卡门涡街的周期性流动。     

三维空间曲面结构风荷载的数值模拟

本文运用计算流体动力学技术,基于FLUENT 流体动力学数值模拟平台,采用雷诺平均法和大涡模拟技术,对球壳、柱面、悬链面、菱形马鞍面及椭圆双曲抛物面五类结构进行了定常、非定常流场的模拟计算。使用自回归模型的线性滤波法生成了脉动风速的时间序列,该脉动风速的时间序列很好地满足了预先设定的脉动风速谱和空间相关性要求,进而将其代入到实际计算的边界条件当中。将五类空间曲面结构表面风压的模拟计算结果与风洞试验结果定量比较：稳态计算得到的平均风压数据与风洞试验结果吻合理想,非稳态计算得到的脉动风压数据与试验结果差别稍大,其中正高斯曲面模拟精度高于负高斯曲面。     

Simulation of micro flows with moving boundaries using high-order upwind FV method on unstructured grids

 Numerical methods are presented for the simulation of steady and unsteady micro gas flows with moving boundaries found in micro scale fluidic devices. Both steady and unsteady flows are calculated by using an implicit real-time discretization and a dual-time stepping scheme implemented in a high-order upwind finite-volume unstructured-grid Navier–Stokes solver. For moving boundary problems, a new dynamic mesh method has been developed which is shown to be robust in handling large mesh deformation. Micro-scale flows studied with the methods developed include flow in micro channels, unsteady flow around a micro cylinder in oscillation and transport processes in micro pumps. The simulation is based on the continuum fluid model (the compressible Navier–Stokes equations) with slip boundary conditions implemented in the context of unstructured grids as the micro flows studied are all in the slip flow regime. Results are presented to validate the methods and demonstrate their applications to the analysis and design of micro fluidic devices. The implicit dual-time stepping scheme is found to be robust and efficient in dealing with both steady and unsteady micro flows. The unstructured-grid solver proves to be very flexible in dealing with complex geometries such as micro pumps. This is the first known report on the use of finite-volume unstructured grid solver for studying micro flows based on the slip boundary condition with moving boundaries.     

Numerical simulation of the separated fluid flows at large Reynolds numbers

The variety of flow regimes (steady separated, periodically separated-‘Karman vortex street’, unsteady turbulent) and their characteristic peculiarities (separation and reattachment points, secondary separation, boundary layer, instability of the shear mixing layer, etc.) require the construction of effective numerical methods, which will be able to simulate adequately the considered flows. MERANGE ? SMIF–a splitting method for physical factors of incompressible fluids¹-is used for calculations of the steady and unsteady fluid flows past a circular cylinder in a wide range of Reynolds numbers (10° < Re < lo6). The finite-difference scheme for this method is of second order accuracy in the space variables, has minimal numerical viscosity and is also monotonic. Use of the Navier-Stokes equations with the corresponding transformation of Cartesian co-ordinates allows the calculations to be made by one algorithm both in a boundary layer and out of it. The method allows calculations at Re = ∞ cc and simulation of d‘Alembert’s paradox. Some results on the classical problem of the flow around a circular cylinder for a wide range of Reynolds numbers are discussed. The crisis of the total drag coefficient and the sharp rise of the Strouhal number are simulated numerically (without any turbulence models) for the critical Reynolds numbers (Re ≈ 4 × 10⁵), and are in a good agreement with experimental data.     

On a similarity solution in the theory of unsteady marginal separation

The present paper deals with initial value problems associated with the high Reynolds number asymptotic theory of unsteady, marginally separated boundary layer flows. In particular, the subsonic planar flow case is treated. Special emphasis is placed on solutions which blow up within finite time. As is well-known, steady solutions of the underlying equations only exist up to a critical value of the crucial parameter which controls the conditions leading to localized boundary layer separation. Our numerical analysis shows that any blow-up solution finally approaches a unique structure, entirely independently of the choice of initial data, sub- or super-critical flow conditions, and, if present at all, the type of forcing. Further support for the existence of a self-similar, unique blow-up structure is gained from asymptotic analysis.     

Prediction of incidence effects on oscillating airfoil aerodynamics by a locally analytical method

A complete mathematical model is formulated to analyse the effects of mean flow incidence angle on the unsteady aerodynamics of an oscillating airfoil in an incompressible flow field. A velocity potential formulation is utilized. The steady flow is independent of the unsteady flow field. However, the unsteady flow is coupled to the steady flow field through the boundary conditions on the oscillating airfoil. The numerical solution technique for both the steady and unsteady flow fields is based on a locally analytical method. In this method, analytical solutions are incorporated into the numerical technique, with the discrete algebraic equations which represent the differential flow field equations obtained from analytic solutions in individual local computational grid elements. This flow model and locally analytic numerical solution method are then verified through the excellent correlation obtained with the Theodorsen oscillating flat plate and Sears transverse gust classical solutions. The effects of mean flow incidence on the steady and oscillating airfoil aerodynamics are then investigated.     

Boundary element analysis of wave-current interaction around a large structure

A numerical approach for wave-current interaction around a large structure is investigated, based on potential flow theory, linear waves and small current velocity approximation. The velocity potential in a wave-current coexisting field is separated into a steady current potential and an unsteady wave potential. The boundary element method was then employed to compute the unsteady wave potential with effects of both a uniform current and a large body taken into consideration. It is demonstrated that the steady current potential can be expressed as the sum of a uniform current and a steady disturbance due to the presence of the object. The variation of current velocity in the vicinity of the object is then calculated by using a surface vorticity boundary integral meethod. Boundary element analysis is also used for the numerical solutions of the surface vorticity method. Substituting both unsteady wave potential and current velocity into the first-order dynamic surface boundary condition, the water surface elevation around a large structure in a wave-current coexisting field can then be obtained. Comparisons of numerical predictions with experimental results ar also made; qualitative good agreements are obtained.     

Viscous vortex core generation

Summary The unsteady flow of a viscous incompressible fluid between two porous co-axial circular cylinders is analysed when the outer cylinder is impulsively set into rotation. When there is radial inflow, vorticity is transferred from an unsteady boundary layer initially over the outer cylinder to a steady boundary layer over the inner cylinder.With 1 Figure     

建筑表面风压的三维数值模拟

本文采用数值模拟方法预测由近地三维流动风引起的建筑物的表面风压。文中运用一种扩展的ｋ－ε紊流封闭模型，导得了稳态流动风的统一形式的控制微分方程。采用控制容积法对微分方程作了离散，ＳＩＭＰＬＥＣ压力校正迭代算法实现了非线性离散化方程的求解。实例计算与分析比较表明，本文的模拟方法改善了对建筑物侧风面和顶面风压值的预测