化学反应对超音速混合层发展的影响

超音速混合层流动发展的研究对于了解超音速燃烧过程具有重要意义.基于耦合详细化学反应动力学机理的高精度数值模拟,分析了化学反应对超音速混合层发展过程的影响.主要分析了在两种燃烧状态下化学反应对混合层的演化过程和混合层厚度的影响,此外从涡动力学角度,分析了化学反应对混合层厚度的影响机理.     

超音速混合层稳定性分析及增强混合的研究

利用流动稳定性提高超音速混合层的混合效率,对于提高超音速流的高效混合是一个有效途径。研究结果表明,有展向曲率的三维混合层中,三维扰动的增长率很大,且法向的掺混能力也较强,可以有效地增强混合。对于高马赫数来流的超音速混合层,这一特性依然存在,这将有利于提高高超音速混合层的混合能力。     

低对流马赫数平面混合层的声波产生机理

为了详细揭示低对流马赫数下平面混合层的声波产生机理,基于高精度混合格式,对空间发展的平面混合层的流场结构及其声场特性进行了直接模拟.数值结果描述了对流马赫数为0.4时混合层失稳产生的涡串以及涡发展过程中所存在的各种声源,其中包括常规的单涡四极子声源、双涡以及多涡合并过程产生的四极子声源,另外,还发现因K-H不稳定引起混合层振动而产生的偶极子声源,声波以平面波的形式向周围传播.     

超声速边界层/混合层组合流动的稳定性分析

利用可压缩线性稳定性理论研究了超声速混合层考虑壁面影响流动时的失稳特性. 基本流场选取了具有不同速度特征的2 股均匀来流,进入存在上下壁面的流道中. 混合层与边界层的距离为1~3 个边界层厚度,其中壁面取为绝热壁. 分析了该流动在超声速情况下的稳定性特征,同时还讨论了不同波角下的三维扰动波的演化特点,并与二维扰动波进行了比较和分析. 研究结果表明,在此流动情况下,边界层流动和混合层流动的稳定性特征同时存在,并互有影响,其流动稳定性特征既有别于单纯的平板边界层,也有别于单纯的平面混合层,呈现出了新的稳定性特征.      

可压缩混合层流动近十年研究进展

从稳定性分析、实验研究和数值模拟3个方面回顾了过去近10年间关于可压缩混合层流动的研究.这些工作研究了可压缩性对混合层其它性质的影响,这些性质包括混合层增长率、不稳定模式、流场结构、平均速度和脉动速度、以及标志物的混合等.3种研究方法相互补充, 共同提供了认识可压缩混合层流动机制的大量信息.这些研究是湍流机理研究的重要组成部分,也是混合层流动在应用技术领域成功应用的前提.      

带展向曲率的超音速混合层中扰动演化的研究

超音速混合层的流动不稳定性较之亚音速或不可压的混合层大大减弱，为了提高混合效率， 通过数值模拟的方法分别研究了展向曲率、展向速度、来流马赫数等因素对混合效率所 起的作用. 计算结果表明：在给定展向速度的情况下，带有展向曲率的三维混合层，曲率越 大三维扰动增长率越大，而且法向的卷起范围也越大. 当展向曲率不为零时，展向速度的增 大也能有效地增强混合能力. 由流场中的高频扰动波产生的涡，在向下游发展过程中会有破 碎、拉伸，低频扰动波没有发现这一现象. 对于有展向曲率和展向速度的混合层，提高来流 马赫数时，流场中最不稳定扰动的增长率仍很大. 因此，这是一种提高混合层混合效率的新 途径.     

超声速平面混合层小激波的形成与演变

为了揭示超声速混合层中小激波形成机理及其与涡相互作用的演变过程,本文基于大涡模拟（LES）方法,结合五阶精度混合TCD／WENO格式,对超声速平面混合层在对流马赫数为Mc=0．65条件下的流场结构进行了数值模拟,数值结果详细描述了超声速混合层中小激波的形成过程。研究了小激波形成后,随涡运动而产生的变形、脱落及发展过程。同时,对混合层双涡合并过程中,小激波与相邻涡相互作用所产生的变形与演变过程进行了讨论。     

Recent progress and challenges in fundamental combustion research（燃烧基础研究的进展和挑战）

超过80%的世界的能源转换是由燃烧方法来实现的. 发展可利用替代燃料的清洁和高效的新型发动机是解决可持续能源发展的关键之一. 在燃烧研究领域,实现这一目标的挑战是要揭示从燃料分子到发动机的多尺度燃烧过程中化学反应和火焰动力学机理,发展高效,定量的数值模拟方法和开发新的燃烧技术. 本文从7个方面综述最近几年燃烧领域的基础燃烧研究的进展和挑战. 它们包括低温清洁燃烧的发动机技术,极限条件下的燃烧机理和现象,替代燃料和混合燃料模型,多尺度化学反应模拟方法,高压燃烧反应动力学,基础燃烧的实验方法,和先进测量技术. 本文首先介绍均值充量压缩点火（HCCI）,反应控制压缩点火（RCCI）以及增压燃烧等新型发动机的概念,评述燃料特性和低温燃烧反应过程对湍流燃烧和发动机的影响,讨论发展基础燃烧研究的必要性. 第二,综述燃料浓度分层燃烧,稀薄燃烧,冷炎燃烧,以及等离子体助燃等极限燃烧条件下的新的燃烧现象和火焰机制. 第三,以航空煤油和生物柴油为例来讨论建立模拟真实燃料和替代燃料的混合燃料模型的方法. 介绍活性基指数和输运加权的反应焓的概念并用来比较燃料的高温反应特性和评价燃料的分子结构对燃烧特性的影响. 第四,评述详细化学反应机理简化的方法. 介绍多时间尺度（MTS）的化学反应的模拟和动态关联性自适应机理简化（CO-DAC）的方法来提高详细化学反应机理的计算效率. 第五,讨论高压燃烧的火焰传播速度的实验测量结果以及高压燃烧化学反应机理所存在的问题,并分析高压燃烧的关键组分和反应路径. 第六,评述测量火焰速度和组分等基础燃烧实验方法和模型中的问题和误差来源. 介绍一些改进测量方法和提高测量精度的方法. 最后,介绍测量低温燃烧中的关键组分和自由基的测量方法和最新进展.      

混合层绕流圆柱旋涡脱落的数值研究

对平面混合层绕流圆柱时的旋涡脱落和流动结构进行了数值研究。方法是用一空间、时间三阶精度的有限差分格式解二维不可压Navier-Stokes方程和连续性方程。计算时雷诺数Re取为1000,混合层速度比Ra从0到1,混合层动量厚度θ由0.2到2。     

混合层流动拟序结构的大涡模拟

采用大涡模拟方法对空间发展的二维平面混合层进行了数值模拟 ,动量方程采用分步投影法求解 ,亚格子项采用标准Smagorinsky亚格子模式模拟 ,压力泊松方程采用修正的循环消去法快速求解 ,同时求解了标志物输运方程以实现数值流场显示。模拟结果给出了混合层流动的瞬态发展过程以及流动中拟序结构的发展演变过程 ,成功地模拟了混合层发展中的各种瞬态细节过程 ,如涡的卷起、增长 ,涡与涡之间的配对、合并过程 ,以及大涡破碎为小涡的级联过程 ,为各种以混合层流动为原型流动的射流、尾流等工业流动的控制和优化提供了理论基础。     

Effect of Streamline Curvature on Intensity of Streamwise Vortices in the Mixing Layer of Supersonic Jets

The structure of supersonic nonisobaric jets with Mach numbers M_a = 1 and 2 is considered experimentally to find the effect of streamline curvature on the evolution of streamwise vortices in the mixing layer. The spatial development of steady streamwise vortices in the mixing layer of supersonic jets is considered. A method for generation of steady streamwise vortices by applying microroughness elements of controlled size onto the inner surface of the nozzle is developed. Radial profiles and azimuthal variations of total pressure are obtained; the mixinglayer thickness and the curvature of streamlines in supersonic jets are determined. A significant effect of microroughness elements of prescribed shape located on the nozzle surface on the behavior of total pressure in the mixing layer of supersonic jets, as compared to natural disturbances, is obtained.     

Numerical simulation of supersonic reacting mixing layer

In this paper, the supersonic chemically reacting mixing layer is simulated with the third order ENN scheme, based on the Navier-Stokes equations, containing transport equations of all species. The numerical results show that the thickness of mixing layer increases gradually along the flow direction, and that the Kelvin-Helmholtz instabilities may not exist in mixing layer flows. The project supported by the National Natural Science Foundation of China     

Study of a Mixing Layer Formed by a Supersonic Main Stream of Air and a Co-Flowing Supersonic Helium Jet

The development of large-scale organised motions in a compressible mixing layer is studied experimentally using holographic interferometry, pressure and turbulence measurements. The mixing layer was formed behind the base of a parallel strut with a Mach 2 air main stream and a co-flowing two-dimensional slot jet (aspect ratio = 45) of helium at a Mach number of 1.2. The mixing layer exhibited highly organised vortical structures which were elongated and inclined approximately 45–50° to the flow direction. The mixing layer showed a linear growth and the mean velocity data indicated self-similar behaviour at sufficiently downstream distances. The results have shown that the thickness of the primary boundary layer has a strong influence on the growth and structure of the mixing layer. This revised version was published online in July 2006 with corrections to the Cover Date.     

超声速边界层/混合层组合流动的稳定性分析简

利用可压缩线性稳定性理论研究了超声速混合层考虑壁面影响流动时的失稳特性. 基本流场选取了具有不同速度特征的2 股均匀来流,进入存在上下壁面的流道中. 混合层与边界层的距离为1~3 个边界层厚度,其中壁面取为绝热壁. 分析了该流动在超声速情况下的稳定性特征,同时还讨论了不同波角下的三维扰动波的演化特点,并与二维扰动波进行了比较和分析. 研究结果表明,在此流动情况下,边界层流动和混合层流动的稳定性特征同时存在,并互有影响,其流动稳定性特征既有别于单纯的平板边界层,也有别于单纯的平面混合层,呈现出了新的稳定性特征.     

Mixing Measurements in a Supersonic Expansion-Ramp Combustor

This paper reports results on molecular mixing for injection via an expansion-ramp into a supersonic freestream with M ₁ = 1.5. This geometry produces a compressible turbulent shear layer between an upper, high-speed “air” stream and a lower, low-speed “fuel” stream, injected through an expansion-ramp at α = 30° to the high-speed freestream. Mass injection is chosen to force the shear layer to attach to the lower guide wall. This results in part of the flow being directed upstream, forming a recirculation zone. Employing the hypergolic hydrogen-fluorine chemical reaction and pairs of “flip” experiments, molecular mixing is quantified by measuring the resulting temperature rise. Initial experiments established the fast-chemistry limit for this flow in terms of a Damköhler number (Da). For Da ≥ 1.4, molecularly mixed fluid effectively reacts to completion. Parameters varied in these experiments were the measurement station location, the injection velocity of the (lower) “fuel” stream, the stoichiometry for the flip experiments, and the density ratio of the fuel and air streams. As expected, mixing increases with increasing distance from the injection surface. The mixed fluid fraction increases by 12% when changing the fuel-to-air stream density ratio from 1 to 0.2. Comparisons with measurements at subsonic (high-speed) “air” stream velocities show that the trend of decreasing mixing with increasing speed documented in free-shear layer flows is also encountered in these flows. The current geometry produces higher mixing levels than do free shear layers.     

Spanwise domain effects on the evolution of the plane turbulent mixing layer

Large Eddy Simulation is used to simulate a series of plane mixing layers. The influence of the spanwise domain on the development of the mixing layer, and the evolution of the coherent structures, are considered. The mixing layers originate from laminar conditions, and an idealised inflow condition is found to produce accurate flow predictions when the spanwise computational domain extent is sufficient to avoid confinement effects. Spanwise domain confinement of the flow occurs when the ratio of spanwise domain extent to local momentum thickness reaches a value of ten. Flow confinement results in changes to both the growth mechanism of the turbulent coherent structures, and the nature of the interactions that occur between them. The results demonstrate that simulations of the two-dimensional mixing layer flow requires a three-dimensional computational domain in order that the flow will evolve in a manner that is free from restraints imposed by the spanwise domain.     

混合层强化混合的数值研究

受 Ｗａｎｇ ＆ Ｆｉｅｄｌｅｒ（１９９７）的实验的启发，采用高阶精度的差分格式，通过数值模拟的方法，研究了二维混合层及限于两平板间的二维混合层（二维受限混合层）入口处加振动对提高混合层混合效率的作用．计算结果表明：对二维混合层，振动的频率越低，在混合层中产生的大尺度涡结构的尺度越大，在频率很低时，涡具有相似性；对限于两平板间的二维混合层，在一定的振动频率下，混合层中产生的涡较大而且破碎得也较好，这将有利于混合．这一结论与 Ｗａｎｇ ＆ Ｆｉｅｄｌｅｒ（１９９７）的实验观测到的结果是一致的．     

Numerical study on supersonic mixing and combustion with hydrogen injection upstream of a cavity flameholder

Characteristics of supersonic mixing and combustion with hydrogen injection upstream of a cavity flameholder are investigated numerically using hybrid RANS/LES (Reynolds-Averaged Navier–Stokes/Large-Eddy Simulation) method. Two types of inflow boundary layer are considered. One is a laminar-like boundary layer with inflow thickness of $\delta_{\inf } = 0.0$ and the other is a turbulent boundary layer with inflow thickness of $\delta_{\inf } = 2.5\,{\text{mm}}$ . The hybrid RANS/LES method acts as a DES (Detached Eddy Simulation) model for the laminar-like inflow condition and a wall-modeled LES for the turbulent inflow condition where the recycling/rescaling method is adopted. Although the turbulent inflow seems to have just minor influences on the supersonic cavity flow without fuel injection, its effects on the mixing and combustion processes are great. It is found that the unsteady turbulent structures in upstream incoming boundary layer interact with the injection jet, resulting in fluctuations of the upstream recirculation region and bow shock, and induce quick dispersion of the hydrogen fuel jet, which enhances the mixing as well as subsequent combustion.