基于波传播算法的火焰不稳定性

基于波传播算法构造了多组分反应流的数值格式,利用CH4空气基元反应动力学模型,并采用分离算法,对CH4空气混合物中,入射激波与火焰的相互作用,以及反射激波与火焰的二次作用过程进行了数值模拟.根据计算结果,讨论了激波诱导火焰失稳的发展过程及其特点.结果表明,Helmholtz不稳定、RichtmyerMeshkov不稳定以及反应放热速率对火焰失稳过程有重要影响.计算结果与实验结果进行了比较,对数值方法的有效性进行了验证.     

激波聚焦反射的实验和数值研究

 采用高速摄影技术和数值模拟方法，对入射激波在两种不同形状的抛物形反射器表面聚焦和反射的过程进行了研究，得到了激波聚焦反射过程的波系结构的实验阴影照片和数值计算结果，两者符合得很好。对激波聚焦形成的气体动力学焦点的特性进行了分析，结果表明，入射激波在两种反射器反射后聚焦所形成的气体动力学焦点均是由三波点在轴心处的会聚所导致的，气体动力学焦点位于相应的反射器壁面的几何焦点附近。不同的反射器中，激波聚焦前后的波系结构也不同，对较浅的反射器，入射激波反射前在反射器壁面形成了弓形激波，反射之后需要相对较长的时间完成聚焦，形成聚焦反射激波之后弓形激波仍未相交；对较深的反射器，入射激波反射后在更短的时间内聚焦，聚焦时弓形激波已经相交，聚焦反射激波之后的流场波系结构更加复杂。     

入射和反射激波诱导重气泡变形和失稳的三维数值研究

 采用大涡模拟方法,对入射激波及其反射激波诱导球形重气泡的变形失稳过程进行了三维数值模拟,利用已有实验验证了计算模型的可靠性,重点考察了反射激波与已经失稳的气泡界面的再次作用,讨论了涡环的形成及其三维失稳的过程。研究结果显示：入射和反射激波与球形重气泡作用产生斜压效应,会在流场中产生旋转方向截然相反的多个涡环;反射激波诱导的涡环具有较小的强度,故更加容易失稳,甚至能完全形成具有流向涡量的复杂小尺度涡结构。     

超声速预混可燃气流的点火与燃烧

在激波风洞一激波管组合设备上开展了碳氢燃料超声速预混可燃气流的点火与燃烧实验研究。实验结果表明:利用激波对燃料进行预热,并以高温燃气作为引导火焰,可以有效缩短汽油空气超声速可燃混气的点火延迟时间,使之缩短到 0.2 ms以下。利用纹影照片对超声速燃烧流场结构作出了分析;研究了超声速预混可燃气流的温度以及当量比对超声速燃烧流场结构、点火与火焰传播特性的影响。     

可燃悬浮寺燃烧诱导激波可其加速过程研究

以铝粉为例，基于双流体模型，分别采用ＴＶＤ格式和ＭａｃＣｏｍａｃｋ格式计算气相和颗粒相流场，基于Ａｒｒｉｈｅｎｉｕｓ定律及管道壁面湍流ｋ－ε模型计算流场反应速度，对水平燃烧管内可燃悬浮粉尘在弱点火条件下激波的产生及加强过程进行了理论分析与数值模拟。研究发现，壁面湍流在火焰加速及燃烧诱导激波过程中起着关键作用，数值计算结果揭示了可燃悬浮粉尘云中压缩波到激波的转捩机制及气固两相流场参数的变化规律。计算     

高焓横向射流尾迹区掺混燃烧的数值特性

尾迹区作为横向射流流场的重要结构受到广泛关注,其掺混和燃烧特性对近壁面区域的流场特性有重要影响.文章在对仿真充分验证的基础上,采用Reynolds平均模拟方法对Ma=8飞行条件下高焓横向射流尾迹区中的掺混和燃烧特性进行了数值研究.探究了冷热流场尾迹区中的氢气掺混特性,冷态流场尾迹区中的激波结构对氢气分布产生一定影响,热态流场尾迹区中存在多种氢气掺混路径.V形回流区中的高浓度氢气对燃烧产生了一定的阻碍作用.定量测量了尾迹区中的火焰结构,尾迹区火焰的顶点位置随高度增加向下游线性移动,受射流主流影响,尾迹区火焰的展向宽度在距离壁面一定高度后开始增大.对冷热流场中的主要参数进行了对比,燃烧消耗了氢气使温度升高,但是尾迹区中的流动速度没有明显增加,燃烧放出的热量没有完全转化为流体的动能.      

不同重力下窄通道内薄材料表面的火焰传播

在常重力下模拟微重力燃烧对载人航天器的火灾安全具有重要意义.窄通道就是这样一种可以有效限制自然对流的模拟设施.但是,不同重力下火焰传播的相似性仍然是有待研究的问题.本文用实验和数值模拟的方法,比较了不同重力下有限空间内热薄材料表面的逆风传播火焰.不同重力下火焰形状和火焰传播速度的比较表明,1cm高的水平窄通道可以有效地限制自然对流,在常重力下用这种通道能够模拟微重力下相同几何尺寸的通道中的火焰传播.因此,在地面上首先利用水平窄通道,模拟相同环境中的微重力火焰传播,然后考虑通道尺寸变化对火焰传播的影响,有可能成为地面模拟其他尺寸的空间中的微重力燃烧的方法.     

隔板深度对激波聚焦起爆影响的数值模拟研究

考虑几何结构参数对激波聚焦触发爆轰波的复杂影响,对H2/Air预混气的环形射流激波聚焦起爆现象开展了数值模拟研究,详细分析了不同隔板深度条件下的激波聚焦过程、流场演化特征以及爆轰波参数变化规律。研究结果表明,凹腔内激波聚焦诱导的局部爆炸以及隔板前缘处射流形成"卷吸涡"是引起爆轰波触发的两个重要机制,而隔板深度是影响环形射流激波聚焦起爆性能的关键因素。随着隔板深度的增加,凹腔内激波聚焦的强度逐步增强,回传的能量损失有所减小,进而导致爆燃转爆轰的距离与时间显著缩短。此外,当隔板深度由1 mm逐渐增加至3 mm时,爆轰波自持传播稳定性呈现出先降低后升高的变化趋势,产生这一现象的主要原因是爆轰波强度与三波点运动的相互作用。     

激波与SF6球形气泡相互作用的数值研究

本文基于大涡模拟方法, 采用高阶精度格式对平面入射激波以及不同反射距离条件下的反射激波与SF₆重气泡相互作用过程进行了三维数值模拟. 数值结果清晰地显示了SF₆重气泡在激波作用下诱导Richtmyer-Meshkov不稳定性过程, 揭示了入射激波以及反射激波在气泡界面聚焦诱导射流的过程, 详细分析了不同反射距离条件下反射激波与SF₆重气泡作用过程及流场结构.     

激波和火焰相互作用的数值模拟

本文应用基元反应模型和NND格式,数值研究了充满可燃预混气的二维管道中,激波和火焰的相互作用过程.计算中氢氧混合物的化学反应考虑了9种组分20个反应式,讨论了激波作用于火焰时,火焰的变化以及缓燃转爆震(DDT)的过程,分析了不同激波马赫数对激波和火焰作用过程的影响.结果表明:激波与火焰作用能触发爆震波的产生,爆震波是由管壁上形成的爆震中心引发.     

Experimental observations of flame acceleration and transition to detonation following shock-flame interaction

Observations are presented from experiments where laminar flame bubbles were perturbed successively by incident and reflected shock waves. Significant flame acceleration was observed in many instances, with the flame closely coupled to the reflected shock wave. The coupled waves are interpreted using a generalized Hugoniot analysis. As the incident shock velocity increased, detonation emerged near the highly convolved reaction zone. Prior to detonation the external visual attributes of the combustion fronts appear identical to turbulent combustion. However, they cannot be due to classical isotropic turbulence. The overall conclusion is that the observed enhancement of combustion is driven by chemi-acoustic interactions and related gas-dynamic effects. An analysis of the prevailing thermodynamic states suggests that thermal auto-ignition chemistry could also play a significant role prior to the onset of detonation.     

Transition in the propagation mechanism during flame acceleration in porous media

The combustion of stoichiometric hydrogen-air at various initial pressures was investigated in a 7.62 cm square cross-section channel filled with 1.27 cm diameter beads. The flame time-of-arrival and pressure time history along the channel were obtained by ionization probes and piezoelectric pressure transducers. Flame acceleration was found to be very rapid, e.g. at an initial pressure of 45 kPa the flame achieves a velocity of over 600 m/s in roughly 0.3 m. It was determined that at this high speed a well defined planar shock wave precedes a thick reaction zone. It was also shown that there is a transition in the flame propagation mechanism, similar to that observed in an obstacle laden channel [G. Ciccarelli and C. Johansen, The role of shock-flame interactions on flame acceleration in an obstacle laden channel, Proc. 22nd International Colloquium on the Dynamics of Explosions and Reactive Systems, Minsk, 2009]. By varying the initial pressure of the mixture, changes in the axial location of the transition between combustion propagation regimes was also observed. A soot foil technique was used to identify the transition in the propagation mechanism, as well as to provide information concerning the local flow field around the beads and the overall average flow direction.     

猫眼谐振腔氦氖激光器理论分析

猫眼逆向器作为谐振腔镜与一个凹面镜构成猫眼激光谐振腔.精确计算了三种猫眼逆向器(即理想猫眼逆向器和两种存在误差的猫眼逆向器)的逆向平行反射性，并对应用这三种猫眼逆向器的谐振腔中高斯光束的各项参数进行了深入分析，得出结论：对于高斯光束，凸透镜的焦距、凹面镜曲率半径、凸透镜与凹面镜间距三者相等的猫眼逆向器为理想逆向器，其逆向平行反射性最好，此时猫眼谐振腔处于理想状态，基模模体积最大，远场发散角最小，稳定性最好；在猫眼谐振腔的设计中，要尽量减小猫眼逆向器中凸透镜的焦距，增大凹面输出镜的曲率半径；猫眼逆向器存在误差时谐振腔的各项性能将受到影响.为猫眼谐振腔激光器的设计提供了理论依据.     

Acoustic characteristics of pulse detonation engine with ellipsoidal reflector

Acoustic characteristics of a pulse detonation engine(PDE) with and without an ellipsoidal reflector are numerically and experimentally investigated. A two-dimensional(2 D) non-splitting unstructured triangular mesh Euler solver based on the space-time conservation element and solution element(CE/SE) method is employed to simulate the flow field of a PDE.The numerical results clearly demonstrate the external flow field of the PDE. The effect of an ellipsoidal reflector on the flow field characteristic near the PDE exit is investigated. The formation process of reflected shock wave and reflected jet shock are reported in detail. An acoustic measurement system is established for the PDE acoustic testing. The experimental results show that the ellipsoidal reflector changes the sound waveform and directivity of PDE sound. The reflected shock wave and reflected jet shock result in two more positive pressure peaks in the sound waveform. The ellipsoidal reflector changes the directivity of PDE sound from 20 to 0. It is found that the peak sound pressure level(PSPL) and overall sound pressure level(OASPL) each obtain an increment when the PDE is installed with a reflector. The maximum relative increase ratio of PSPL and OASPL are obtained at the focus point F2, whose values are 6.1% and 6.84% respectively. The results of the duration of the PDE sound indicate that the reflecting and focusing wave generated by the reflector result in the increment of A duration and B duration before and near focus point F2. Results show that the ellipsoidal reflector has a great influence on the acoustic characteristic of PDE sound. The research is helpful for understanding the influence of an ellipsoidal reflector on the formation and propagation process of PDE sound.     

Shock wave-inertial microbubble interaction: methodology, physical characterization, and bioeffect study

A method of generating in situ shock wave-inertial microbubble interaction by a modified electrohydraulic shock wave lithotripter is proposed and tested in vitro. An annular brass ellipsoidal reflector (thickness = 28 mm) that can be mounted on the aperture rim of a Dornier XL-1 lithotripter was designed and fabricated. This ring reflector shares the same foci with the XL-1 reflector, but is 15 mm short in major axis. Thus, a small portion of the spherical shock wave, generated by a spark discharge at the first focus (F1) of the reflector, is reflected and diffracted by the ring reflector, producing a weak shock wave approximately 8.5 microseconds in front of the lithotripter pulse. Based on the configuration of the ring reflector (different combinations of six identical segments), the peak negative pressure of the preceding weak shock wave at the second focus (F2) can be adjusted from -0.96 to -1.91 MPa, at an output voltage of 25 kV. The preceding shock wave induces inertial microbubbles, most of which expand to a maximum size of 100-200 microns, with a few expanding up to 400 microns before being collapsed in situ by the ensuing lithotripter pulse. Physical characterizations utilizing polyvinylidene difluoride (PVDF) membrane hydrophone, high-speed shadowgraph imaging, and passive cavitation detection have shown strong secondary shock wave emission immediately following the propagating lithotripter shock front, and microjet formation along the wave propagation direction. Using the modified reflector, injury to mouse lymphoid cells is significantly increased at high exposure (up to 50% with shock number > 100). With optimal pulse combination, the maximum efficiency of shock wave-induced membrane permeabilization can be enhanced substantially (up to 91%), achieved at a low exposure of 50 shocks. These results suggest that shock wave-inertial microbubble interaction may be used selectively to either enhance the efficiency of shock wave-mediated macromolecule delivery at low exposure or tissue destruction at high exposure.     

激波冲击火焰的流动拓扑研究

为深入研究激波冲击火焰现象的内在机制,采用二维带化学反应的Navier-Stokes方程对现象进行数值研究,通过对速度梯度张量特征方程的分析证明Okubo-Weiss函数适用于可压缩流动,并重点分析火焰区的流动拓扑特性.结果表明,波后火焰区内Okubo-Weiss函数积分量基本守恒,但在火焰区内部和表面具有截然不同的流动状态,且火焰发展基本不受流场可压缩性的影响;波后火焰区的流动拓扑分类主要以焦点和鞍点为主,意味着流场中变形占主导.     

Detonation simulations in supersonic flow under circumstances of injection and mixing

The unsteady, reactive Navier-Stokes equations with a detailed chemical mechanism of 11 species and 27 steps were employed to simulate the mixing, flame acceleration and deflagration-to-detonation transition (DDT) triggered by transverse jet obstacles. Results show that multiple transverse jet obstacles ejecting into the chamber can be used to activate DDT. But the occurrence of DDT is tremendously difficult in a non-uniform supersonic mixture so that it required several groups of transverse jets with increasing stagnation pressure. The jets introduce flow turbulence and produce oblique and bow shock waves even in an inhomogeneous supersonic mixture. The DDT is enhanced by multiple explosion points that are generated by the intense shock wave focusing of the leading flame front. It is found that the partial detonation front decouples into shock and flame, which is mainly caused by the fuel deficiency, nevertheless the decoupled shock wave is strong enough to reignite the mixture to detonation conditions. The resulting transverse wave leads to further mixing and burning of the downstream non-equilibrium chemical reaction, resulting in a high combustion temperature and intense flow instabilities. Additionally, the longitudinal and transverse gradients of the non-uniform supersonic mixture induce highly dynamic behaviors with sudden propagation speed increase and detonation front instabilities.     

Effect of a dielectric film on the characteristics of an open Fabry-Perot resonator cavity

It is demonstrated that placing a thin dielectric film inside the cavity of an open Fabry-Perot resonator, at an angle to its axis, will remove the polarizational degeneracy of the principal TEM_q00 oscillation modes. Upon excitation of such a resonator cavity by a plane wave, the reflected electromagnetic field is in general elliptically polarized. The shape of the resonance curve depends on the thickness of that film, on its orientation inside the cavity, on the conditions under which the cavity has been excited, and on the conditions under which the reflected signal appears in the receiver. Changing the polarization plane of the incident plane wave does not result in a smooth variation of the resonator Q factor.Translated from Izvestiya Vysshikh Uchebnykh Zavedenii, Radiofizika, Vol. 21, No. 11, pp. 1648–1652, November, 1978.