Influence of Obstacle-Produced Turbulence on Development of Premixed Flames

An investigation into influence of obstructions on premixed flame propagation has been carried out in a semi-open tube. It is found that there exists flame acceleration and rising overpressure along the path of flame due to obstacles. According to the magnitude of flame speeds, the propagation of flame in the tube can be classified into three regimes: the quenching, the choking and the detonation regimes. In premixed flames near the flammability limits, the flame is observed first to accelerate and then to quench itself after propagating past a certain number of obstacles. In the choking regime, the maximum flame speeds are somewhat below the combustion product sound speeds, and insensitive to the blockage ratio. In the more sensitive mixtures, the transition to detonation (DDT) occurs when the equivalence ratio increases. The transition is not observed for the less sensitive mixtures. The dependence of overpressure on blockage ratio is not monotonous. Furthermore, a numerical study of flame acceleration and overpressure with the unsteady compressible flow model is performed, and the agreement between the simulation and measurements is good.

Multiplex CARS measurements in supersonic H-2/air combustion

H-2 and O-2 multiplex coherent anti-stokes Raman spectroscopy (CARS) employing a single dye laser has been explored to simultaneously determine the temperature and concentrations of H-2 and O-2 in a hydrogen-fueled supersonic combustor. Systematic calibrations were performed through a well-characterized H-2/air premixed flat-flame burner. In particular, temperature measurement was accomplished using the intensity ratio of the H-2 S(5) and S(6) rotational lines, whereas extraction of the H-2 and O-2 concentrations was obtained from the H-2 S(6) and O-2 Q-branch, respectively. Details of the calibration procedure and data reduction are discussed. Quantification of the supersonic mixing and combustion characteristics applying the present technique has been demonstrated to be feasible. The associated detection limits as well as possible improvements are also identified.

Heat release rate measurement in turbulent flames

The dominant industrial approach for the reduction of NO x emissions in industrial gas turbines is the lean pre-mixed prevaporized concept. The main advantage of this concept is the lean operation of the combustion process; this decreases the heat release rate from the flame and results in a reduction in operating temperature. The direct measurement of heat release rates via simultaneous laser induced fluorescence of OH and CH 2O radicals using planar laser induced fluorescence. The product of the two images correlated with the forward production rate of the HCO radical, which in turn has correlated well with heat release rates from premixed hydrocarbon flames. The experimental methodology of the measurement of heat release rate and applications in different turbulent premixed flames were presented. This is an abstract of a paper presented at the 7th World Congress of Chemical Engineering (Glasgow, Scotland 7/10-14/2005).

Forcing of self-excited round jet diffusion flames

In this experimental and numerical study, two types of round jet are examined under acoustic forcing. The first is a non-reacting low density jet (density ratio 0.14). The second is a buoyant jet diffusion flame at a Reynolds number of 1100 (density ratio of unburnt fluids 0.5). Both jets have regions of strong absolute instability at their base and this causes them to exhibit strong self-excited bulging oscillations at welldefined natural frequencies. This study particularly focuses on the heat release of the jet diffusion flame, which oscillates at the same natural frequency as the bulging mode, due to the absolutely unstable shear layer just outside the flame. The jets are forced at several amplitudes around their natural frequencies. In the non-reacting jet, the frequency of the bulging oscillation locks into the forcing frequency relatively easily. In the jet diffusion flame, however, very large forcing amplitudes are required to make the heat release lock into the forcing frequency. Even at these high forcing amplitudes, the natural mode takes over again from the forced mode in the downstream region of the flow, where the perturbation is beginning to saturate non-linearly and where the heat release is high. This raises the possibility that, in a flame with large regions of absolute instability, the strong natural mode could saturate before the forced mode, weakening the coupling between heat release and incident pressure perturbations, hence weakening the feedback loop that causes combustion instability. © 2009 The Combustion Institute. Published by Elsevier Inc. All rights reserved.

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。

采用偏置射流预燃室稳定燃烧水煤浆的原理及应用研究

水煤浆作为经济型清洁燃料引起人们的长期关注。水煤浆偏置射流预燃室具有对浆种适应性强，稳燃性能好等特点。本文对偏置射流预燃室稳定燃烧水煤浆的原理进行了探讨，并对该燃烧技术用于处理造纸黑液的研究情况作了介绍。结果表明，采用低压多级雾化喷嘴对水煤浆进行雾化，形成的雾炬和偏置射流预燃室的流场有良好的匹配，在预燃室内形成大尺度的回流区，有利于煤浆的点火、稳燃和消除灰渣。

超声速燃烧室凹腔火焰稳定器的数值模拟

为分析凹腔火焰稳定器在超声速燃烧室中的流动特性,运用数值模拟方法研究了凹腔对H2超声速燃烧的作用规律。通过对比分析不同凹腔长深比L/Du,后缘倾角θ,后缘深度D_d和H_2喷射位置Ljet对燃烧室性能的影响,发现凹腔的火焰稳定机制主要在于富含自由基的高温回流区;L/D_u=7-9,θ=30°,D_u/D_d=1.0和L_(jet)=24mm的燃烧室强化混合燃烧的性能较好,可以获得较高的燃烧效率和总压恢复。

微重力下薄燃料表面火焰传播的地面窄通道模拟

对微重力下薄燃料表面逆风火焰传播的地面窄通道模拟,进行了量纲分析,并通过火焰传播图像记录进行了实验验证.结果表明,减小实验段特征尺寸可以实现微重力燃烧的地面模拟.在各种氧气浓度条件下,竖直和水平窄通道内的火焰传播速度随气流速度的变化趋势完全不同,而且,水平窄通道可以有效限制自然对流,而竖直窄通道较难.当通道高度增大时,竖直和水平窄通道中,火焰传播速度和吹熄极限速度都不同程度地增大,这是热损失减小、火焰面遇见的气流速度减小以及自然对流速度增大3个因素的综合结果.对于水平窄通道, 1 cm是一个可以定性模拟微重力下自然对流的尺寸.对于竖直窄通道,则需要高度更小的窄通道来限制自然对流.

气脉冲发生器中火焰传播与压力变化的研究

燃烧气脉冲发生器用于电厂锅炉除灰，其工作原理是预混可燃气体在右端部分开口在内部有障碍物的容器中快速燃烧，以形成一定的压力脉冲，并产生作用于积灰表面的射流和冲击波，火焰在端流扰动装置的作用下不断加速，容器中的压力不断上升，火焰传播愈快，压力波形愈陡，压力锋值愈高，针对这些现象，该文进行了实验和理论研究。主要研究了乙炔，水煤气，液化石油气和甲烷4种燃料，在不同燃料浓度，不同阻塞比时对火焰传播和压力上升的影响，计算和实验结果对实验应用有指导作用。

微重力蜡烛火焰特征数值模拟

建立了微重力蜡烛火焰的数学模型。计算与分析表明，火焰的形状由空气动力学特征决定，火焰是温度取决于化学反应动力学特征和火焰的热损失。在静止微重力环境中，自然对流的消失使火焰为半球形。辐射热损失对烛火焰温度（颜色）特征的形成有重要贡献，在静止重力环境下，化学反应放热速率受氧气扩散速率控制，辐射热损失的冷却使火焰温度低于正常重力温度值。但当环境气体的流动速度加大时，辐射热损失的影响逐渐减小，蜡烛火焰的温度逐渐接近正常重力蜡烛火焰的温度。当氧浓度较小时，火焰峰值温度小于烟黑形成的阈值温度（1300 K）；当氧浓度较大时，火焰温度大于烟黑形成的阈值温度。

氢/空气火焰在半开口有障碍管道中的传播特性

针对氢/空气混合物，通过实验研究了其预混火焰在半开口管道中的火焰传播加速现象。结果表明，火焰传播状态随着氢气当量比的变化而发生改变。当氢/空气混合物被点燃后，由于障碍物的扰动，火焰在管道中不断加速传播，并最终到一准稳态传播。在氢气当量比0.34附近时，火焰速度发生跃变。当氢气当量比足够大时，火焰传播由爆燃态转变为爆轰态。在本实验条件下，爆燃转准爆轰的临界条件是d/λ ≥ 2.6（d是圆环形障碍物内径，λ是爆轰格胞尺度）。障碍物阻塞比的变化对最大火焰速度和压力提升的影响不明显。

柱形容器开口泄爆过程中的火焰传播特性

泄爆过程中流动与燃烧的相互作用机制是研究开口泄爆问题的关键.对柱形容器泄爆过程中压力与火焰发展传播过程的观测与分析表明,不同泄爆条件下压力与火焰的发展传播具有明显特点.泄爆诱导流动通过加速火焰传播、加剧火焰变形、增大火焰面积对容器内燃烧产生增强作用,泄爆流动大小主要由泄爆面积决定.小口中低压泄爆过程压力与火焰的发展过程与封闭燃烧中类似;小口高压以及大口泄爆过程中,火焰变形剧烈,传播速度明显上升,并导致压力的回升.

障碍物结构对管道中预混火焰加速的影响

在一端封闭、一端开口的火焰传播管中均匀布置障碍物，研究了障碍物结构对管道中预混火焰传播的影响。结果表明，由于障碍物的扰动，火焰不断加速，在阻塞比相同的条件下，最终的火焰稳态速度与障碍物的形状和间距基本无关，其中障碍物间距仅仅影响火焰的加速速率，在障碍物间距约等于火焰传播管内径（W/D ≈ 1.0）时，平均火焰速度达到最大值，火焰到达稳态传播的距离最短。同时，本文用一维简化模型模拟了火焰在障碍物管道中的加速过程，计算结果与实验测试结果在定性上比较吻合，说明在管内火焰速度较低的情况下，用一维可压缩流动近似处理能初步揭示管内火焰的加速机制。

Investigation of High-Speed Combustible Gas Ignited by a Hot Gas Jet Produced in the Shock Tube

The high-speed combustible gas ignited by a hot gas jet, which is induced by shock focusing, was experimentally investigated. By use of the separation mode of shock tube, the test section of a single shock tube is split into two parts, which provide the high-speed flow of combustible gas and pilot flame of hot gas jet, respectively. In the interface of two parts of test sections the flame of jet was formed and spread to the high-speed combustible gas. Two kinds of the ignitions, 3-D "line-flame ignition" and 2-D "plane-flame ignition", were investigated. In the condition of 3-D "line-flame ignition" of combustion, thicker hot gas jet than pure air jet, was observed in schlieren photos. In the condition of 2-D "plane-flame ignition" of combustion, the delay time of ignition and the angle of flame front in schlieren photos were measured, from which the velocity of flame propagation in the high-speed combustible gas is estimated in the range of 30-90m/s and the delay time of ignition is estimated in the range of 0.12-0.29ms.