网栅后湍流流动沿流程衰减特性的实验研究

应用ＬＤＶ测试技术对垂直方管内三种不同栅距的网所形成的湍流流动做了详细测量,网栅栅距Ｍ分别为１４ｍｍ,１０ｍｍ,６ｍｍ实验给出了管内不同位置湍流流动的各种参数沿流动方向的衰减规律,并就三种网栅进行比较分析,以探讨这种网栅流动所具有共同规律和在不同栅距对湍流结构及脉动大小的不同特点,从而对这种网栅所形成的湍流流结构较为清晰的了解。     

附面层中马蹄形旋涡的实验研究

本文用烟流显示和热线方法研究附面层中马蹄形旋涡的形态、生成频率、配对和涡系之间的相互作用。     

沟槽面湍流边界层结构实验研究

应用激光测速技术和氢气泡流动显示技术对沟槽面湍流边界层特性及近壁区拟序结构特征进行了精细的测量和观察。实验结果表明：与光滑面湍流边界层相比,沟槽面端流边界层的黏性底层厚度、过渡层厚度及流速分布对数公式中的积分常数C均有所增大,说明采用的沟槽面具有减阻特性。此外,无量纲低速带条间距明显减小,最多减小20%,说明无量钢低速带条平均间距的缩短与湍流减阻密切联系。     

二维平板湍流边界层减阻研究

利用一套以位移传感器为主的弹性平衡装置,测量几种不同表面形状设计的平板在充分发展的二维湍流边界层中的减阻效果,并对其减阻机理进行研究。结果表明,大涡破碎器 LEBU(Large Eddy Break-up)和其它减阻装置的形状和布置对表面摩擦阻力有较大影响,在有些设计状态下的平板得到了净减阻。     

湍流边界层流场与噪声实验研究

在重力式水洞中进行了水翼及半翼湍流边界层流场与噪声的实验研究。测量了水翼及半翼边界层附近的湍流脉动速度场;测量了半翼翼型表面三点处的压力脉动及其辐射噪声,测量了水翼内部测点的噪声及外部辐射噪声,在不同流速、不同攻角、光滑和粗糙翼面的情况下都进行了测量分析。试验结果发现,上述因素对模型的边界层湍流速度场有显著影响,15度攻角时,翼面附近湍流强度要比0度时大得多,粗糙翼面附近的湍流强度比光滑的大,而湍流强度随来流速度的变化不大,u(来流）方向和v方向的湍流强度量级相当;一般地,翼面压力脉动、翼内部噪声及外部噪声都是随来流速度的增大而增大,随攻角的增大而增大,粗糙翼面时的结果要比光滑翼面的大。从压力脉动与噪声测量结果与相应的流场测量结果比较可知,可以从湍流区域的湍流强度来判断出声源强度的定性变化。     

钝体分离流动的实验研究

本文报告了楔形钝体分离流区域的湍流实验,提供了分离区内的时均速度、压力,湍流度和雷诺应力的分布,并对分离区的湍流特征进行了分析。实验表明,分离区内时均速度具有很大的横向梯度。湍流度和雷诺应力的分布曲线很相纵,它们在回流区变化较为平缓,而在混合区,当它们达到极大值之后,便以指数形式向(?)衰减。压力在回流区内变化也不大,但在混合区却具有明显的横向梯度。     

双柱双锥形液—流旋流分离管内流场的LDV诊断

本文采用ＴＳＩ二维ＬＤＶ系统,对一种双锥双柱形液－液旋流分离管内流场进行了全场范围的精细ＬＤＶ诊断,先后考试了处理量、压差比、溢流比和气芯等因素对旋流分离管内流场的影响,结果表明：该旋流分离管中下游区的切向速度呈较为明显的Ｒａｎｋｉｎｅ双涡结构,在上游位涡区中发现有未曾报道过的双峰分布现象;轴向速度由近轴处的上行流、近壁处的下行流以及介于两者之间的零速区组成,其中该零速区随旋流分离管截面的收缩而减     

雷诺数对湍流特性的影响

主要对近年来关于雷诺数（Ｒｅ）对湍流特性的影响的研究进行了回顾．研究表明除径向偏斜系数和平坦系数分布外,确实存在一个不受Ｒｅ数影响的区域,但对于不同的物理量这一区域的范围是不同的,即使是同一物理量不同研究者的结果亦不尽相同,显示了近壁区流动的复杂性和测量的困难,激光测速技术（ＬＤＶ）由于其具有测量精度高、不干扰流场、空间分辨率细等优点,近年来广泛地应用于对湍流,特别是对湍流近壁区流动特性及Ｒｅ数对湍流统计特性影响等的精细测量,随着ＬＤＶ自身及其它相关测试技术的进一步改进,ＬＤＶ在了解湍流产生机理、能量转换等方面发挥着越来越重要的作用．     

k-ωSST湍流模式三维激波分离流动修正

“激波?边界层分离”是航空气动领域的典型湍流非平衡流动问题, 准确模拟激波分离对于跨声速飞行器气动性能评估和优化设计具有重要意义. 然而传统涡黏性湍流模式中涡黏性系数的定义方式并不适用于非平衡流动, k-ω SST湍流模式为此引入的Bradshaw假设在应用于三维强逆压梯度和较大分离流动时反而限制了雷诺应力的生成, 导致包括k-ω SST在内的常用涡黏性湍流模式均无法对此类流动进行准确模拟. 同时, 现有的非线性雷诺应力本构关系也并不能有效提高模拟精度. 为此, 针对k-ω SST模式分别提出了基于Bradshaw假设和基于长度尺度的两种激波分离流动修正方法. 前者通过提高Bradshaw常数的方式放宽了对雷诺应力生成的限制, 后者则从湍流长度尺度概念出发, 利用混合长度理论、湍动能生成/耗散之比和一种新定义的长度尺度之比构造了ω方程耗散项修正函数, 提高了模式在三维激波分离流动中的建模长度尺度. 两种方法对ONERA M6机翼跨声速大攻角流动均能得到较雷诺应力模式更好的模拟结果. 进一步的雷诺应力分析表明, 三维激波分离流动中“主雷诺应力分量”的概念不再成立, 各雷诺应力分量大小接近. 网格收敛性分析、对其他攻角状态的验证以及湍流平板边界层壁面律验证进一步确认了所提出的两种修正方法的合理性、有效性和通用性.      

二维曲壁扩压器内湍流边界层分离的研究

本文应用二维双色四光束激光多普勒测速仪和压强探针样细地测量了二维非对称曲面扩张通道内的不可压湍流边界层分离流动，得到了时均速度和雷诺剪应力以及正反向间歇流动因子和静压分布。实验结果分析表明；湍流边界层分离时，沿边界层高度方向存在着明显的压强差。压强差的极小值对应于位移厚度曲率的极大值和瞬时间歇分离点。Ｂａｒｄｉｎａ对数尾迹律可以较好地描述瞬时间歇分离点之前的边界层速度分布，但无法描述分离的边界层速     

Application of the Dorodnitsyn finite element method to swirling boundary layer flow

The Dorodnitsyn finite element method for turbulent boundary layer flow with surface mass transfer is extended to include axisymmetric swirling internal boundary layer flow. Turbulence effects are represented by the two-layer eddy viscosity model of Cebeci and Smith¹ with extensions to allow for the effect of swirl. The method is applied to duct entry flow and a 10 degree included-angle conical diffuser, and produces results in close agreement with experimental measurements with only 11 grid points across the boundary layer. The introduction of swirl (w_e/u_e = 0.4) is found to have little effect on the axial skin friction in either a slightly favourable or adverse pressure gradient, but does cause an increase in the displacement area for an adverse pressure gradient. Surface mass transfer (blowing or suction) causes a substantial reduction (blowing) in axial skin friction and an increase in the displacement area. Both suction and the adverse pressure gradient have little influence on the circumferential velocity and shear stress components. Consequently in an adverse pressure gradient the flow direction adjacent to the wall is expected to approach the circumferential direction at some downstream location.     

激光测速频移量的选择准则

本文简要介绍了在激光测速中应用声光调制技术的原理,着重讨论了光-电子学混合式频移系统的频移设置关系和准则,并结合TSI激光测速系统进行了分析。     

A numerical technique for three-dimensional compressible boundary layers

The non-linear two-point boundary value problem for three-dimensional compressible boundary layers is solved through the application of a boundary value technique for a range of parameters characterizing the nature of stagnation point flows. The analytical boundary conditions, at infinity, are applied at the edge of the computational mesh with iterations on the size of the domain. The solutions obtained show excellent agreement with the established similarity solutions for three-dimensional flows. The present method has the potential advantage of yielding the wall values of f″_w, g″_w and θ′_w as a part of the solution, contrary to the previously used ‘shooting’ methods. The algorithm is computationally simple and numerically stable and extremely suitable for engineering design applications.     

Numerical simulation of swirling flow in diffusers

A reduced form of Navier–Stokes equations is developed which does not have the usual minimum axial step size restriction. The equations are able to predict accurately turbulent swirling flow in diffusers. An efficient single sweep implicit scheme is developed in conjunction with a variable grid size domain-conforming co-ordinate system. The present scheme indicates good agreement with experimental results for (1) turbulent pipe flow, (2) turbulent diffuser flow, (3) turbulent swirling diffuser flow. The strong coupling between the swirl and the axial velocity profiles outside of the boundary layer region is demonstrated.     

应用二维LDA系统研究连铸结晶器紊动流场特性

本文以重庆特殊钢厂引进日本四孔水口连铸结晶器为研究对象,用二维激光多普勒测速仪(二维 LDA)较详细地测定了该结晶器模型内的紊动流场,并对其流速分布规律及紊动特性进行了分析研究.文中还讨论了速度偏置误差问题,提出了是否进行偏置误差修正的判别条件.本文的成果对此类结晶器有关温度场、杂质分布及改进设计和工艺控制等后续课题的研究提供了重要的依据.     

Computation of high speed turbulent boundary-layer flows using the k–ϵ turbulence model

The applicability of a finite element-differential method to the computation of steady two-dimensional low-speed, transonic and supersonic turbulent boundary-layer flows is investigated. The turbulence model chosen for the Reynolds shear stress and turbulent heat flux is the K-? two-equation model. Calculations are extended up to the wall and the exact values of the dependent variables at the wall are used as boundary conditions. A number of transformations are carried out and the assumed solutions at a longitudinal station are represented by complete cubic spline functions. In essence, the method converts the governing partial differential equations into a system of ordinary differential equations by a weighted residuals method and invokes an ordinary differential equation solver for the numerical integration of the reduced initial-value problem. The results of the computations reveal that the method is highly accurate and efficient. Furthermore, the accuracy and applicability of the k-? turbulence model are examined by comparing results of the computations with experimental data. The agreement is very good.     

Influence of thermal boundary conditions on the dynamic behaviour of a rectangular single-phase natural circulation loop

Natural circulation of distilled water and FC43 has been experimentally investigated in a rectangular loop characterized by internal diameter of 30 mm and total length of 4.1 m. The aim of the present study is to analyse the influence of thermal boundary conditions on the flow regimes inside the pipes and on the stability of the system. The new aspect of the present research is the possibility of tuning the heat sink temperature in a range between −20 °C and +30 °C by means of a cryostat. This kind of analysis could be useful for the design of systems characterized by a wide range of environment temperatures, as for example for aerospatial applications. The other parameters investigated were the heat flux transferred to the fluid, which varied between 0.1 kW and 2.5 kW, and the thermo-physical properties of the working fluid. The system showed both stable and unstable behaviour. In particular, in the case of FC43 the loop was more unstable and it was characterized by higher velocities and frequencies compared to the case of distilled water.It was found that the stability threshold could be crossed by varying only the heat sink temperature, demonstrating the importance of this boundary condition on the dynamics of the system. Different flow regimes and fluid velocities were observed. In the case of steady-state flow, Vijayan’s correlation (Vijayan et al., 2000) was tested and found to give good agreement with experimental data. Linear stability analysis was made following the Vijayan’s model. In particular, the effect of heat sink temperature was considered in the dimensionless Stanton number based on the overall heat transfer coefficient at the heat sink. Finally, Ultrasound Pulsed Doppler Velocimeter (UPDV) was used on a natural circulation loop for the first time, and gave a preliminary validation of the traditional fluid velocity measurement method based on the frequency analysis.     

Turbulent separated reattached flow in a two-dimensional curved-wall diffuser

A turbulent separation-reattachment flow in a two-dimensional asymmetrical curved-wall diffuser is studied by a two-dimensional laser doppler velocimeter. The turbulent boundary layer separates on the lower curved wall under strong pressure gradient and then reattaches on a parallel channel. At the inlet of the diffuser, Reynolds number based on the diffuser height is 1.2×10⁵ and the velocity is 25.2m/s. The results of experiments are presented and analyzed in new defined streamline-aligned coordinates. The experiment shows that after Transitory Detachment Reynolds shear stress is negative in the near-wall backflow region. Their characteristics are approximately the same as in simple turbulent shear layers near the maximum Reynolds shear stress. A scale is formed using the maximum Reynolds shear stresses. It is found that a Reynolds shear stress similarity exists from separation to reattachment and the Schofield-Perry velocity law exists in the forward shear flow. Both profiles are used in the experimental work that leads to the design of a new eddy-viscosity model. The length scale is taken from that developed by Schofield and Perry. The composite velocity scale is formed by the maximum Reynolds shear stress and the Schofield-Perry velocity scale as well as the edge velocity of the boundary layer. The results of these experiments are presented in this paper.     

On the use of a two-layer model for large-eddy simulations of supersonic boundary layers with separation

The two-layer modeling approach has become one of the most promising and successful methodology for simulating turbulent boundary layers in the past ten years. In the present study, a mixed wall model for large-eddy simulations (LES) of high-speed flows is proposed which combine two approaches; the thin-Boundary Layer Equations (TBLE) model of Kawai and Larsson (1994) and the analytical wall-layer model of Duprat et al. (2011) for streamwise pressure gradients. The new hybrid model has been efficiently implemented into a three-dimensional compressible LES solver and validated against DNS of a spatially-evolving supersonic boundary layer (BL) under moderate and strong pressure gradients, before being employed for the prediction of nozzle flow separations at different flow conditions, ranging from weakly to highly over-expanded regimes. A good agreement is obtained in terms of mean and fluctuating quantities compared to the DNS results. Particularly, the current wall-modeled LES results are found to perfectly match the DNS data of supersonic BL with/out pressure gradient. It is also shown that the model can account for the effect of the large-scale turbulent motions of the outer layer, indicating a good interaction between the inner and the outer part of the wall layer. In terms of simulations costs and improvements of computing power, the obtained results highlight the capability of the current wall-modeling LES strategy in saving a considerable amount of computational time compared to the wall-resolved LES counterpart, allowing to push further the simulations limits. Furthermore, the application of these computationally low-costly LES simulations to nozzle flow separation allows to clearly identify the origin of the shock unsteadiness, and the existence of broadband and energetically-significant low-frequency oscillations (LFO) in the vicinity of the separation region.     

应用二维激光测速系统研究面流消能的紊动特性

本文应用二维激光测速系统对面流消能工下游典型流态的紊动特性进行了系统的试验研究,得到了不同来流条件下面流的时均流速、紊动强度及雷诺应力等沿主流与回流区的分布特征;计算并绘制了流线图,由此分析了淹没面流时底旋滚长度和佛劳德数的关系。对紊动能量的转换过程及耗散特征进行了计算分析,初步探明了消能机理。