展向行波状Lorentz力的波数对壁湍流控制的影响

展向行波状Lorentz力可以有效调制湍流近壁流动及减少壁面摩擦阻力。为了解行波波数在壁湍流控制中的影响,并进一步揭示该方法的减阻机理,本文利用Fourier-Chebyshev谱方法,通过直接数值模拟（DNS）,对槽道湍流的展向行波状Lorentz力控制和减阻问题进行了研究,讨论了展向波数kz对近壁流动及壁面阻力的影响。结果表明,当展向行波状Lorentz力诱导的流场被用来调制固有的近壁湍流流场时,固有流场和诱导流场同时受到调制。Lorentz力的展向波数对流场调制效果具有显著影响。通过波数的选择,引进新的涡结构,可以调制条带结构的展向间距与强度,影响近壁流体的湍流猝发活动,从而调制壁面摩擦阻力的大小。     

Prediction of turbulent diffusion flames with a four-equation turbulence model

For turbulent flame prediction a four-equation turbulence model consisting of the turbulent kinetic energy, the dissipation rate and the density-velocity correlations using unweighted statistics is suggested. The fluctuating concentrations are taken into account by using Spalding's (1971) equation for the variance of the mixture fraction f and by defining the probability density function of f as beta-function. The thermodynamic model for the combustion of H₂ with air assumes infinitely fast reaction in a global single step. Preliminary results are shown for the calculation of Kent and Bilger (1972) turbulent H₂-air diffusion flame. For this flame with fluctuating density the inclusion of the velocity-density correlations appears to be essential, because they have a strong effect especially on the development of the turbulent viscosity and the mean velocity and mass fraction profiles. Consequently the mean concentrations are in good agreement with the experimental results.     

Detonation engine fed by acetylene–oxygen mixture

The advantages of a constant volume combustion cycle as compared to constant pressure combustion in terms of thermodynamic efficiency has focused the search for advanced propulsion on detonation engines. Detonation of acetylene mixed with oxygen in various proportions is studied using mathematical modeling. Simplified kinetics of acetylene burning includes 11 reactions with 9 components. Deflagration to detonation transition (DDT) is obtained in a cylindrical tube with a section of obstacles modeling a Shchelkin spiral; the DDT takes place in this section for a wide range of initial mixture compositions. A modified ka-omega turbulence model is used to simulate flame acceleration in the Shchelkin spiral section of the system. The results of numerical simulations were compared with experiments, which had been performed in the same size detonation chamber and turbulent spiral ring section, and with theoretical data on the Chapman–Jouguet detonation parameters.     

Menter转捩模型在高超声速流动模拟中的改进及验证

通过压力梯度参数和湍流普朗特数的修正,对Menter等构造的低速经验关系式转捩模型进行了改进,将基于局部信息的Menter转捩模型用于高超声速流动转捩数值模拟。在多个高超声速尖锥转捩流动模拟中,对改进后模型的可靠性进行了检验,算例考核了不同壁面温度、来流湍流度、流向压力梯度等多种流动条件。结果表明,数值计算和风洞试验的壁面温度、温度恢复因子和热流等符合得较好,修正后模型较好地模拟了转捩起始位置和转捩区长度,在高超声速边界层转捩预测中具有一定潜力。     

An experimental study on the stability of jet diffusion flame

The stability behavior of jet diffusion flame developing in a coflowing high temperature air stream was studied experimentally, using city gas and hydrogen as fuel gases. The primary variables studied were temperature and velocity of the air stream. Two distinct types of stability limits were observed. The first is the blow-off of the rim-stabilized flame, which is familiar and has been studied by a number of investigators. The second is the break-off or extinction of the turbulent portion of the flame at the transition point from laminar to turbulent flow. The second limit is quite unfamiliar and is interesting in relation to the structure of turbulent diffusion flames. The important implications of the experimental findings concerning the stability and the structure of turbulent diffusion flames is discussed.     

The turbulent combustion of a propane-air mixture

This paper models the combustion of a turbulent homogeneous mixture of propane and air within a duct having a stationary one-dimensional mean flow. The Bray-Moss model is applied to the closure of the chemical production terms, using a probability density function (pdf) of the temperature which is chosen as the characteristic variable. Under the conditions chosen for the study, chemical kinetic factors are important and the conventional assumption, that heat release is controlled by turbulent mixing, is not valid. The chemical model of Edelman and Fortune for the combustion of hydrocarbons is used and simplifying assumptions are made which reduce the systems of unknowns to that of the temperature alone. This leads to the introduction of two chemical production terms which are defined respectively in a “delay zone”, where the heat release is modest, and a “combustion zone”. The required equations for the Favre-averaged temperature, turbulence kinetic energy and the mean square fluctuation of the temperature are solved numerically. In the delay zone, a comparison is made between a second order Borghi type closure and the pdf closure. Good agreement is found in the case of relatively small turbulence intensity. It is shown that the pdf formulation does not require the two zones to be spatially distinct. Differing chemical source terms can be discriminated instantaneously by the reaction progress variable and contributions to the average production terms appropriately apportioned by its pdf. Predictions are made of the profiles of mean temperature and mean square fluctuation under different initial turbulence levels.     

固体推进剂燃烧波温度分布测定

采用相对光强度法测定了双基推进剂、复合推进剂及NEPE（氧化剂为HNIW或HMX）推进剂的燃烧火焰温度分布。结果表明,用相对光强度法测得推进剂的最高燃烧火焰温度比热电偶法更接近推进剂的理论燃烧温度,测试压强越高,最高燃烧火焰温度与理论燃烧火焰温度的误差越小。     

Nonlinear analysis of hydrodynamic instability in laminar flames—II. Numerical experiments

We consider a nonstationary nonlinear integrodifferential equation describing the evolution of a disturbed plane flame front. The following two-dimensional problems are solved numerically: (i) The formation of a wrinkled noncellular laminar flame front under conditions of spontaneous hydrodynamic instability. (ii) The formation of a turbulent cellular flame front under conditions of spontaneous diffusional-thermal instability. (iii) The formation of a turbulent wrinkled-cellular flame front under conditions of spontaneous hydrodynamic and diffusional-thermal instability. We compute the flame front velocity in laminar and turbulent propagation.     

Calculation of ignition and combustion of a hydrogen jet in air with finite chemical reaction rates

A comparison between two analytical models of a free turbulent mixing of reacting streams with finite chemical reaction rates is presented and the results of calculations compared with experimental data. The substance is a mixture of the inert non-dissociated nitrogen and oxygen that dissociates and reacts with hydrogen.For the first model the local values of flow parameters along the streamlines were provided by the numerical solution of the conservation equations in the boundary layer form for a multicomponent mixture of perfect gases in the von Mises coordinate system. In the course of this analysis the problem was treated by dividing the flowfield into a large number of regions and by solving the Cauchy problem of the conservation equations for each region.The second analytical model was based on the ignition delay to describe the chemistry in the region of pre-ignition. The external air stream was heated by combustion and the influence of the water vapor and the intermediate species on the reaction kinetics in the mixing zone was numerically investigated.The results of calculation are compared with the experimental data with respect to the location of a visible flame edge under combustion of hydrogen jet in the co-current flow.     

再入飞行器脉动压力环境特性分析

文章通过数值求解球头单锥飞行器绕流流场结构,利用均方根脉动压力系数、功率谱密度和窄带空间相关系数3个统计参数分析飞行器湍流附面层脉动压力环境特性,为飞行器结构改进设计提供依据,并为飞行器环境条件加载位置、加载密度等参数的确定提供参考。研究结果表明,脉动压力强度沿流向逐渐减小,压力脉动能量主要集中在比湍流附面层脉动特征频率小的频域内;脉动压力空间相关性沿流向逐渐增强,其衰减能力随间隔距离的减小而增加,符合脉动压力的传播和衰减特征。     

Igniter jet dynamics in solid fuel ramjets

The dynamics of a two dimensional plane jet injected at the base of a step, parallel to the wall, in backward facing step flow geometry is numerically studied. The objective of this work is to gain insight into the dynamics of the igniter flow field in solid fuel ramjet motors. Solid fuel ramjets operate by ingestion of air and subsequent combustion with a solid fuel grain such as polyethylene. The system of governing equations is solved with a finite volume approach using a structured grid in which the AUSM⁺ scheme is used to calculate the convective fluxes. The Spalart and Allmaras turbulence model is used in these simulations. Experimental data have been used to validate the flow solver and turbulence model simulation results. The comparison of the numerical results and experimental data has validated the use of the adopted turbulence model for the study of this type of problem. A special attention is paid to the igniter jet exit location. It is shown that the wall jet igniter, issuing from the base of the step, drastically changes the structure of recirculating region of backward facing step flow and produces large and damaging shear stress on the fuel surface. Moving the igniter jet exit location to the top of the backward facing step changes the flow field favorably, by reducing the fuel surface shear stress by an order of magnitude and maintaining the recirculating region behind the step, which can provide proper residence time for the fuel–air mixture chemical reactions.     

Numerical investigation on hydrodynamics of gas-binary particles flows using a second-order-moment turbulent model

A binary-particles Reynolds stress equation is developed on the basis of single second-order-moment turbulence model. In this model, particle–particle two-phase fluctuation velocity correlation transportation is proposed to fully reflect their anisotropic characters, as well as each of particle interaction with gas phase is taken into account. Swirling gas-particle flow experiments data is used to validate this model simulation in term of the reduced codes of the mono-disperse particle gas-particle flows. Numerical simulations are performed for the gas-binary particles mixtures turbulent flows and results shows that the axial Reynolds stress in near wall regions is approximately 3.0 times greater than the tangential direction and the tangential Reynolds stress in central axial region is approximately 5.0 times greater than the axial direction. The Reynolds stress in the axial direction and tangential direction are redistributed due to binary particle–particle collision. The ratio kinetic to particles collision contributions in binary mixture system are varied with the different particle density and the diameter size compositions.     

On a distorted flame front as a hydrodynamic discontinuity

The radius of curvature of a steady distorted flame often turns out to be considerably larger than the width of the thermal structure of the flame. Thus, even under finite deformations of the flame, its structure remains quasi-one-dimensional. This property enables the propagation velocity of a distorted flame front (relative to the gas) to be determined explicitly as a function of the hydrodynamic field and the physico-chemical parameters of the gaseous mixture. With the aid of this relationship one can try to determine the shape of the front in a model which is external with respect to the flame structure and treats the flame as a density jump in an ideal incompressible fluid. As applications, we consider (1) the structure of a Bunsen cone, (2) the extinction of a flame in a divergent flow and (3) the propagation velocity of a corrugated flame.     

Influences of the turbulence model and the slot width on the transverse slot injection flow field in supersonic flows

Transverse slot injection scheme is very important for the mixing process between the air and the fuel in supersonic flows. The effect of the turbulence model and slot width on the transverse slot injection flow field has been investigated numerically based on the grid independency analysis, and the predicted results have been compared with the experimental data available in the open literature. The obtained results show that the grid scale makes only a slight difference to the wall pressure profiles for all jet-to-crossflow pressure ratios employed in this study, and the wall pressure profile with low jet-to-crossflow pressure ratio is predicted accurately by the RNG k–ε turbulence model, the SST k–ω turbulence model for the flow field with high jet-to-crossflow pressure ratio. High jet-to-crossflow pressure ratio can increase the jet penetration depth in supersonic flows, and the gradient of the length of the upstream separation region is larger than that of the height of the Mach surface. At the same time, when the jet-to-crossflow pressure ratio is maintained constant, the jet penetration depth increases with the increase of the slot width.     

RBCC燃烧室超声速反应混合层特性的大涡模拟

以飞行马赫数为4.5Ma的RBCC发动机典型工作状态为研究背景,采用大涡模拟研究了支板火箭射流和空气来流形成的超声速反应混合层的掺混燃烧过程,获得了燃烧室内详细的流场结构和流动特征,分析了强射流条件下超声速反应混合层的特性。结果表明由于速度梯度的存在,火箭射流进入燃烧室后与空气来流形成环形剪切层,剪切层内丰富的旋涡结构主导火箭射流和空气来流的掺混燃烧,随着湍流能量的串级输运,化学反应过程中释放的能量将被转化成细观尺度的湍流动能,大尺度旋涡将能量传递给小尺度旋涡并最终耗散,细小尺度的旋涡一方面能够促进燃烧反应物的掺混并强化燃烧过程,另一方面会给化学反应过程带来强烈的脉动,使得局部火焰淬灭,火焰结构表现出明显的非定常性。     

凹腔超声速燃烧室氢气燃烧流场数值模拟

对带长深比为10的凹腔结构的燃烧室二维氢燃烧流场进行数值模拟,燃料喷注方式采用凹腔上游喷注加辅加凹腔前壁、底壁、后壁喷注。采用三阶MUSCL格式求解二维含组分守恒N-S方程组,湍流模型采用剪切修正的RNGk-ε湍流模型,对喷氢燃烧工况进行了计算研究,并分别分析了凹腔中不同燃料喷注方式对燃烧特性的影响。结果表明：凹腔是火焰驻留的主要区域;凹腔上游喷注氢,可以使燃料在凹腔中混合燃烧,辅加凹腔中喷氢的三种方式对燃烧状况产生一定的影响。在凹腔前壁、底面辅加喷氢,没有增强凹腔的稳焰特性,对整个燃烧状态影响不大;在凹腔后壁喷氢,能够增加凹腔中的燃料含量,加强了回流效果,对燃烧状态影响较大。三种喷注方式都没有从根本上改变凹腔燃烧流场的特性。     

Monopropellant droplet decomposition for large activation energies

The quasi-steady decomposition of a monopropellant droplet in a quiescent atmosphere is analyzed, in the limit of large activation energy, for a gas phase decomposition reaction of the Arrhenius type.An analytical relation is obtained for the pre-exponential rate constant, or the Damköhler number, as a function of the droplet vaporization rate. The curve giving the vaporization rate in terms of the Damköhler number has, for low values of the temperature at infinity, an S shaped form which exhibits ignition-extinction characteristics.With increasing values of the droplet vaporization rate above the pure vaporization value we pass from a nearly frozen regime, under which ignition conditions occur due to the large temperature sensitivity of the reaction rate, to a complete decomposition regime, in which practically all the fuel is decomposed in a thin reactive-diffusion zone, separated from the droplet surface by a transport region of lower temperature. For sufficiently large Damköhler numbers, the thin reaction zone is located close to the droplet surface, so that the flame structure becomes planar: a linear relation between the droplet radius and time is obtained in this case. The non planar effects are responsible for the extinction of the flame at low Damköhler numbers and ambient temperatures below the adiabatic flame temperature. For sufficiently low values of the ambient temperature, an intermediate regime exists in which the enhancement of the vaporization rate is due only to the fraction of the vaporized fuel decomposed at a thin reaction zone, not far from the droplet, where the temperature reaches its maximum value; the remaining fuel is decomposed very far from the droplet.     

Radio wave propagation in the turbulent solar plasma using three satellites

The radio wave propagation in the solar-wind plasma was investigated before and after Mars-2, Mars-7 and Venera-10's superior conjunction. It was found that the moving turbulent solar-wind plasma produced the amplitude and frequency fluctuations and the spectral broadening of monochromatic radio waves. When the Sun-Earth-spacecraft angle decreases from 6° to (0.6) the bandwidth of spectral broadening increases from (0.3) Hz to 300 Hz. The region of 2.5–4° is specific since the bandwidth of spectral broadening is independent of Sun-Earth-spacecraft angle. The spectrum of frequency fluctuations could be represented by a power law with a spectral index of 0.7 ± 0.2. The temporal frequency spectra of the amplitude have two distinct regions. In the low-frequency region the spectral density is approximately constant. The high-frequency portion of the amplitude spectrum follows the power law with a spectral index of 2.8 ± 0.4. The turbulence characteristics of a solar-wind plasma are determined from the experimental data obtained. The three-dimensional wave-number spectrum of irregularities is found to be close to the Kolmogorov-Oboukhov spectrum.The solar-wind density fluctuations decline with heliocentric distance very steeply, but in the distance interval of 7 × 10⁶ – 12 × 10⁶ km, there is a region of enhanced turbulence which could be caused by shock waves.     

Three dimensional investigation of the shock train structure in a convergent–divergent nozzle

Three-dimensional computational fluid dynamics analyses have been employed to study the compressible and turbulent flow of the shock train in a convergent–divergent nozzle. The primary goal is to determine the behavior, location, and number of shocks. In this context, full multi-grid initialization, Reynolds stress turbulence model (RSM), and the grid adaption techniques in the Fluent software are utilized under the 3D investigation. The results showed that RSM solution matches with the experimental data suitably. The effects of applying heat generation sources and changing inlet flow total temperature have been investigated. Our simulations showed that changes in the heat generation rate and total temperature of the intake flow influence on the starting point of shock, shock strength, minimum pressure, as well as the maximum flow Mach number.