边界条件对径向湍流射流的影响的计算研究

本文对径向湍流自由射流作了计算，研究了边界条件的不同取法对计算结果的影响，与文献发表的计算结果和实验结果作了比较，再次证明上游湍流结构的边界条件对射流的渐近扩张速率及雷诺应力等流场参数有明显的影响．     

湍流应力输运方程中Π_(ij)和ε_(ij)的模型在旋转流动中的应用研究

基于本文作者先前提出的构筑湍流应力输运方程中速度压力关联项Πij和耗散项εij的模型的一般途径[Proc．ofICFM－III,BITPress,1998],本文推出了它的一个可用于三维流动的简化形式,计算了一个有旋绕的轴对称突扩管道内部流动．由于加入了湍流结构的上游边界条件,新模型对平均流场和Reynolds应力分量的预测比基本的微分应力模型（BRSM）有明显的改进．本文还对在手头没有真实的边界条件可用时,在各种常见的情况下如何加入湍流结构的边界条件作了初步的讨论．     

气冷涡轮环形叶栅三维流场的实验与数值研究

采用4种不同的湍流模型对叶片表面带小孔射流的环形涡轮叶栅内部流场进行数值计算,并与热线实验测量结果进行了对比.结果表明,由于射流尾迹的影响,在射流附近靠近壁面处产生二次流,二次流随着射流下游距离的增大逐渐减弱.比较不同湍流模型的计算结果发现,采用κ-ε模型在射流尾迹区域和与主流掺混区域的计算结果与实验吻合较好,B-L模型在近壁面的速度计算结果偏大,其对尾迹区域二次流的捕捉也较差.     

对湍流结构边界条件敏感的微分湍流应力模型K—ε LADSM

文献中有实验证明内部流动对其上游来流湍流量的边界条件有很强的依赖性，但标准的微分应力模型DSM对湍流应力的边界条件不敏感，因而无法反映这个实验事实，本文发现其主要原因在于Φij,2的快速各向同性化模型．为此本文提出了一个对湍流结构的非各向同性的边界条件敏感的微分应力模型K-ξLADSM．计算了（平面的和轴对称的）突扩通道流动，与实验作了多方面的比较，发现DSM确实比ASM和EVM有所优越处，LADSM又比DSM有明显改进     

三维超声速射流火焰的直接模拟研究

本文使用了直接模拟（DNS）程序计算了三维超声速湍流射流火焰。首先介绍了本程序使用到的计算方法,包括热物性参数和输运参数的计算、反应机理、边界条件、离散方法。然后,本文使用该方法计算了马赫数为1.2的三维超声速H₂-AIR湍流射流火焰,描述了火焰的整作结构。最后,本文对火焰底部的稳燃的机理—自燃进行了分析和论证。     

应用三维LDA对同向射流煤粉预燃室流场的研究

应用三维LDA对同向射流模型燃烧室的流场进行测量,对结果进行了分析。应用k-ε湍流模型进行了数值计算,计算结果与实验结果在定性上是一致的。     

带中心体的燃烧室流场的数值计算

本文研究应用涡量流函数法和k-ε双方程湍流模型对于带中心体的燃烧室中的等温流场进行了数值计算,着重研究了两股同心湍流射流相互作用对于燃烧室中的流型的影响。数值计算结果揭示了一些有趣现象,计算结果比较接近现有的实验数据。     

PIV对射流煤粉火焰流场特性的分析

为研究湍流煤粉射流进入高温环境后的流动及混合特性,采用PIV测量平流射流煤粉燃烧器中心射流区域的流场特性。通过对不同示踪粒子特性的分析,选定SiC表征气相流场,选定煤粉表征煤粉射流流场。实验结果表明;煤粉具有较好的散射特性,因而采用PIV可获得合理的煤粉颗粒流场;相同射流速度下,冷态射流比热态有更强的湍流脉动特征,主要原因是热态条件下气流黏度增加2~3倍,显著降低射流Re。     

槽道流POD重构及湍流动能耗散率分析

采用二维粒子图像测速仪（2DPIV）对槽道内涡波流场进行实验研究,用POD技术对2DPIV瞬态速度矢量场进行主导模态重构,得到槽道内的平均流速和湍流动能分布;采用大涡PIV方法对湍流动能耗散率分布进行计算.结果表明：重构流场表征了原始流场的主导结构,剔除了噪声等干扰信息;大涡PIV方法能有效地估算动能耗散率的分布;湍流动能在壁面附近较小,在接近槽道中心区域湍流动能越来越大,呈现出射流的特征;动能耗散率的峰值出现在壁面附近和槽道中心区域,动能耗散率随着远离壁面程度的增加先降低后逐渐增加直至达到峰值.     

喷管出口处初始湍流结构对自由射流渐近扩张速率的影响

喷管出口处初始湍流结构对自由射流渐近扩张速率的影响吕盘明（中国科技大学热科学和能源工程系合肥２３００２６）关键词自由射流；边界条件；湍流模型；湍流结构１引言关于标准的ｋ－εＥＶＭ（涡粘性模型）的通用性有三个最最典型的疑难例子（或者说是佯谬）在很多文献...     

空心旋转液体射流初始阶段运动规律的研究

应用质量守恒定律和动量守恒定律,建立了描述空心旋转液体射流初始阶段运动的非线 性常微分方程组;该方程组可以用数值方法方便地求解。理论计算结果与实验拍摄到的射流照片吻 合很好。本结果表示射流受挑动失稳破碎成液滴前的最基本运动状态,是进一步从理论上研究空心 旋转射流破碎雾化机理的基础。     

Structure conditioned velocity statistics in a high pressure swirl flame

A piloted, partially premixed, liquid-fueled swirl burner is operated at high pressure (1 MPa). High-speed (6 KHz) stereoscopic PIV is used to investigate the characteristics of the stagnation line separating the pilot jet and the central recirculation zone (CRZ) with varying pilot-main ratio and global equivalence ratio. The mean curvature of the stagnation line displayed a large spatial scale pattern that was present for all operating conditions. All three components of velocity, in-plane shear, and swirling strength are conditioned upon the instantaneous stagnation line. Mean distributions of the velocity normal to the stagnation line show that velocity is oriented towards the CRZ when the stagnation line is found nearer the centerline of the combustor. The conditioned out-of-plane velocity (w) shows a distinct concentration of large mean and fluctuation RMS values towards the center of the measurement domain. Varying fuel flow does not significantly change this spatial structure, only the magnitudes of the w statistics. The in-plane shear stress was the largest for the pilot biased condition as a stronger shear layer develops. For the leanest flame, large fluctuation RMS values of shear stress were confined to a region where the pilot jet begins to interact more heavily with the main jet. Operating with less pilot fuel flow enhanced the mean conditional swirling strength indicating that the pilot shear layer was shedding more intense eddies. Disregarding spatial relations, a scatter plot of w, shear stress, and swirling strength displayed trends between the variables. The largest swirling strength values coincide with highest magnitude shear stresses and the widest range of w. These conditioned statistics highlight how certain aspects of the combustor flow field are invariant with fuel distribution. This is desirable for aeropropulsive combustors that must maintain stable ignition from a range of conditions from landing/take-off to cruise.     

旋转射流冲击换热液晶显示实验研究

采用热色液晶测温技术对以二氧化碳为工质的稳态射流冲击换热和管内插入扭转带方式的旋转射流冲击换热进行了实验研究。与普通射流相比,旋转射流导致驻点附近区域的换热趋于均匀化。其换热系数在大于某一半径之后高于普通射流,但在驻点附近相对较低。旋转射流对换热的此种影响随雷诺数的增大而减弱。     

Stability characteristics and flowfields of turbulent non-premixed swirling flames

A simple, yet representative, burner geometry is used for the investigation of highly swirling turbulent unconfined, non-premixed, flames of natural gas. The burner configuration comprises a ceramic faced bluff-body with a central fuel jet. The bluff-body is surrounded by an annulus that delivers a swirling primary flow of air. The entire burner assembly is housed in a wind tunnel providing a secondary co-flowing stream of air. This hybrid bluff-body/swirl burner configuration stabilizes complex turbulent flames not unlike those found in practical combustors, yet is amenable to modelling because of its well-defined boundary conditions. Full stability characteristics including blow-off limits and comprehensive maps of flame shapes are presented for swirling flames of three different fuel mixtures: compressed natural gas (CNG), CNG–air (1:2 by volume) and CNG–H₂ (1:1 by volume).

It is found that with increased fuel flow, flame blow-off mode may change with swirl number, S_g. At low swirl, the flame remains stable at the base but blows off in the neck region further downstream. At higher swirl numbers, the flames peel off completely from the burner's base. Swirling CNG–air flames are distinct in that they only undergo base blow-off. In the low range of swirl number, increasing S_g causes limited improvement in the blow-off limits of the flames investigated and (for a few cases) can even lead to some deterioration over a small intermediate range of S_g. It is only above a certain threshold of swirl that significant improvements in blow-off limits appear. Six flames are selected for further detailed flowfield and composition measurements and these differ in the combination of swirl number, primary axial velocity through the annulus, U_s, and bulk fuel jet velocity, U_j. Only velocity field measurements are presented in this paper. A number of flow features are resolved in these flames, which resemble those already associated with non-reacting swirling flows of equivalent swirl obtained with the present burner configuration. Additionally, asymmetric flowfields inherent to some flames are revealed where the fluidic centreline of the flow (defined in the two-dimensional (U–W velocity pair) velocity field by the ?ω? = 0 tangential velocity contour), meanders strongly on either side of the geometric centreline downstream by about one bluff-body diameter. Flow structures revealed by the velocity data are correlated to flame shapes to yield a better understanding of how the velocity field influences the flames physical characteristics.     

Control of spray spot in cold spray technology. Part 1. Gas dynamic aspects

This paper presents a study of supersonic jets formed by approaches that are new for cold spray technique: the main flow is swirled, the nozzles with permeable profiles and with exit slots on the supersonic section are engineered. The flow swirling achieved in the nozzle prechamber retains downstream to substrate surface. The system of vortices created within the permeable nozzles changes the shock wave features of the overexpanded jet and the geometry of the bow shock wave ahead of the substrate surface. These new features of flow may affect particle motion and particlesubstrate interaction under the conditions of cold spray process; this offers tools for obtaining the necessary shape of a spray spot.     

Large eddy simulations of a triangular jet and its counterpart through a chamber

A free triangular jet(TJ1) and its counterpart initially passing a short circular chamber(TJ2) are numerically modeled using large eddy simulation(LES). This paper compares the near-field characteristics of the two jets in detail. To enable some necessary experimental validations, the LES conditions of TJ1 and TJ2 are taken to be identical to those measured by Xu et al.(Sci. China Phys. 56 1176(2013)) and England et al.(Exp. Fluids. 48 69(2010)), respectively. The LES predictions are found to agree well with those measurements. It is demonstrated that a strong swirl occurs near the chamber inlet plane for the TJ2 flow. At the center of the swirl, there is a cluster of three sink foci, where each focus is aligned midway between the original triangular apexes. In the vortex skeleton constructed from the time-averaged flow field, the vortices arising from the foci are helically twisted around the core of the jet. As the flow passes through the chamber, the foci merge to form a closed-loop "bifurcation line", which separates the inward swirling flow and the outward oscillating jet. This global oscillation is regarded as a source node near the centerline of the chamber. If the chamber is removed for a"free" jet, i.e., TJ1, a cluster of three pairs of counter-rotating foci is produced and the net swirl circulation is zero, so the overall oscillation of the jet does not occur.     

Formation of zones of an inverse energy cascade in an axisymmetric jet

The results of investigation into the mechanism of formation of an inverse turbulence energy cascade in an axially symmetric submerged jet based on numerical modeling by the large eddy simulation. The flow structure is calculated using two models of subgrid turbulence in a broad range of Reynolds numbers with the imposed external harmonic low-amplitude perturbation and swirling. Calculations showed that upon imposing swirling, the effect of formation of the inverse cascade is suppressed, while upon imposing the external low-amplitude harmonic perturbations corresponding to the frequency of highest perceptivity, it is enhanced. We can assume that the regions with the inverse turbulence energy flow are formed there where the dynamics of large quasi-2D structures is determined by the mechanisms of combining eddies and involvement processes, while the tension mechanism of vortex tubes is suppressed. It is shown that the balance of these mechanisms can be controlled by means of imposition of low-amplitude harmonic perturbations.     

DNS study of swirling intensity effect on flow pattern of a circular jet

Abstract  

The figures show the 3D flow pattern of a circular jet with different swirling intensity. Reynolds number is approximately 4300 computed based on the nozzle diameter (d), jet velocity (U), and air fluid property at 1 atm and 300 K. The overall computational domain is set to be 4 × 4 × 12 d in spanwise, height, and streamwise direction. The governing equations are the fully compressible Navier–Stokes equations, firstly differenced by eighth-order explicit scheme and then advanced temporarily by using the fourth-order explicit Runge–Kutta method. 3D characteristics non-reflecting boundary condition including transverse source contribution is imposed on all other boundaries except the inflow boundary handled by assigning fixed profiles of temperature and velocity. To ensure the simulation resolution, here over 16 million grids are employed in sum, combined with a handful of grids located at buffer zones of outflow boundaries. To correctly represent the vortex in the flow field, velocity gradient tensor invariant Q is used here. And ψ refers to the swirling intensity defined as the ratio of tangential momentum to axis momentum. As shown in velocity profile, the flow pattern of the jet changes from a close mode to a totally open mode as ψ increases from 0.4 to 1.5. Accordingly, the recirculation zone gradually moves upstream and backflow velocity is enlarged as well. It is inteseting to found that the obvious drops of the momentums in two shown directions always occur at the same position downstream, no matter how large the ψ value is. Therefore, a momentum compensatory mechanism is expected to exist in the vortex-abundant zone. With the increase of ψ value, the increased strain rate in tangential direction can induce vortex more quickly, intensifying the entrainment and velocity-attenuation, which can be observed in Q value profile.     

Experimental investigations of detonation initiation by hot jets in supersonic premixed flows

<正>A new method to initiate and sustain the detonation in supersonic flow is investigated.The reaction activity of coming flow may influence the result of detonation initiation.When a hot jet initiates a detonation wave successfully, there may exist two types of detonations.If the detonation velocity is greater than the velocity of coming flow,there will be a normal detonation here.Because of the influence of boundary layer separation,the upstream detonation velocity is much greater than the Chapman-Jouguet(CJ) detonation velocity.On the other hand,if the detonation velocity is less than the velocity of coming flow,an oblique detonation wave(ODW) will form.The ODW needs a continuous hot jet to sustain itself.If the jet pressure is lower than a certain value,the ODW will decouple.In contrast,the normal detonation wave can sustain itself without the hot jet.