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.

Experimental Studies on Model Scramjet in a Mach 6 High Enthalpy Free-Jet Wind Tunnel

A side-wall compression scramjet model with different combustor geometries has been tested in a propulsion tunnel that typically provides the testing flow with Mach number of 5.8, total temperature of 1800K, total pressure of 4.5MPa and mass flow rate of 4kg/s. This kerosene-fueled scramjet model consists of a side-wall compression inlet, a combustor and a thrust nozzle. A strut was used to increase the contraction ratio and to inject fuels, as well as a mixing enhancement device. Several wall cavities were also employed for flame-holding. In order to shorten the ignition delay time of the kerosene fuel, a little amount of hydrogen was used as a pilot flame. The pressure along the combustor has an evident raise after ignition occurred. Consequently thrust was observed during the fuel-on period. However, the thrust was still less than the drag of the scramjet model. For this reason, the drag variation produced by different strut and cavities was tested. Typical results showed that the cavities do not influence the drag so much, but the length of the strut does.

Experimental Study and Numerical Simulation of Cellular Structures and Mach Reflection of Gaseous Detonation Wave

In this paper the Deflagration to Detonation Transition (DDT) process of gaseous H-2-O-2 mixture and Mach reflection of gaseous detonation wave on a wedge have been conducted experimentally. The cellular pattern of DDT process and Mach reflection were obtained from experiments with wedge angle theta = 10(0) similar to 40(0) and initial pressure of gaseous mixture 16kPa similar to 26.7kPa. The 2-D numerical simulations of DDT process and Mach reflection of detonation wave were performed by using the simplified ZND model and improved space-time conservation element and solution element (CE/SE) method. The numerical cellular structures were compared with the cellular patterns of soot track. Compared results were shown that it is satisfactory. The characteristic comparisons on Mach reflection of air shock wave and detonation wave were carried also out and their differences were given.

Destruction of Chemical Agents in a Plasma Reactor with Working Gas of Hydrogen

气脉冲除灰技术燃烧和除灰过程研究

中国电站锅炉燃用大量的未经洗选的劣质煤，导致严重的锅炉积灰问题，尤其是125-600MWe的大型锅炉的回转式空气预热器堵灰更加严重。积灰不仅使锅炉热效率下降，而且堵塞烟气流道，影响了锅炉的正常运行。已有的各种除灰器都有较大的局限性。中国科学院力学研究所燃烧研究实验室根据我国国情开发出了燃烧气脉冲除灰技术，并在30多台大型电站锅炉应用取得了很好的效果。为了理解气脉冲除灰的工作过程，掌握运行规律，解释应用中出现的问题，以提高技术水平和开发新产品，尚需对气脉冲除灰的燃烧和除灰过程做更深入的研究。本论文工作针对燃烧气脉冲除灰技术在实际使用中提出的问题，开展了实验室研究。主要研究了乙炔、水煤气、液化石油气和甲烷四种燃料在气脉冲实验装置中的火焰传播情况和压力波形。研究了混合比、阻塞比和出口截面比对火焰速度和压力峰值的影响。在现有点火条件下找到了在静止混合气体中四种燃料的贫点火极限和乙炔在有一定流速时的贫点火极限；比较了燃烧室内乙炔空气混合物静止时和有一定流速时的爆炸压力峰值。初步搞清了各种因素对火焰速度和压力波形的影响，实验结果对实际应用有指导作用。为了理解火焰传播和压力波形之间的关系，用燃烧室内压力均匀的简化模型，计算了压力波形并且与实验结果进行了对照，由此推算了湍流燃烧速度并探讨了各种因素对它的影响。用考虑了管内有压力波传播的一维简化模型，计算了火焰传播过程中燃烧室两端的压力波形和火焰面前后的气流速度，以及不同时刻的燃烧室内气体流速分布。估算了气流剪切力的量级，进行了模拟积灰的气脉冲对比实验，测量了同一气脉冲条件下两种厚薄不同板的振动加速度值及其随时间和空间的衰减情况。还得到了压力在空间的衰减变化情况。定性地研究了积灰脱落机理，初步认为：对于粘结灰只有振动才有效，气流的剪切不能除去粘结灰。

障碍物扰动对半开口管道中火焰传播特性的影响

自从1926年Chanman和Wheeler率先开创有障碍物管道中的火焰传播研究工作以来，管道中障碍物扰动引起的火焰加速现象引起了广泛的关注。由于这类现象在燃烧科学上的学术意义及其在生产中诸如安全问题等方面的实际意义，人们相继进行了一系列的研究工作。归纳起来，可以分为两大类：1）封闭管道的火焰传播。人们在不同形状的管道或容器中研究了障碍物对火焰加速的影响，在理论分析和数值计算方面也作了一些有益的工作；2）开口管道的火焰传播。相对于闭口管道，开口管道中的火焰传播研究则逊色得多。这方面尚缺乏系统的实验数据，理论方面的分析也欠缺得多。但当前在实际中，并不乏开口体系的应用，如，现已广泛应用于电力系统的一种燃气除灰装置，是一燃烧气体燃料的半开口系统。因此，研究半开口管道中非稳态燃烧的加速机制具有重要意义。在本论文工作中，通过大量的实验研究，比较系统地研究了障碍物的扰动对预混火焰传播特性的影响。实验在一长L=5m、内径D＝80mm的一端封闭、一端开口的火焰传播管内进行，管内均匀布置障碍物，通过改变障碍物的形状、间距、阻塞比大小，同时选用五种不同的可燃气体，探索了障碍物结构对预混湍流火焰加速和管内压力上升的影响。实验表明，对于敏感气体如氢气和乙炔，由于障碍物扰动产生的影响，火焰不断加速，并最终达到一准稳定状态；在适当的条件下，火焰传播状态可由爆燃向爆轰转变，此时火焰速度发生跃变；而对干不敏感气体如甲烷，则爆燃转爆轰现象不容易发生。在不同的火焰传播状态，障碍物结构特性对火焰速度和压力产生的影响各不相同。在缓燃态，随着阻塞比的变化，最大火焰速度先上升后下降，在BR=0.3～0.4之间存在一最大值；在銮塞态，最大火焰速度受阻塞比变化的影响不明显，略低于燃烧产物的声速；在阻塞比BR＝0.5附近，压力达到最大值。而在爆轰态，随着阻塞比的增加，最大火焰速度和压力逐渐降低，爆燃转爆轰的浓度范围变小。由于在有障碍物的管道中，火焰速度很容易达到声速（变塞态）或超声速（爆轰态），必须考虑流体的马赫数效应。本文在前人研究成果的基础上，给出了湍流马赫数修正的可压缩性两方程湍流模型，模拟了半开口狭长管道中重复布置的障碍物引起的湍流火焰加速现象。最大火焰速度和管内压力的计算结果与实验测量值吻合良好，这表明用修正后的湍流模型能够比较真实地模拟障碍物管内预混火焰的发展过程。通过对管道内障碍物扰动引起的燃烧波加速的机理和技术研究，对流场扰动对燃烧波产生和发展的影响规律有了比较全面的了解，研究结果对气脉冲除灰技术的完善具有直接的指导意义。

Numerical Investigation On The Flowfield Of "Swallowtail" Cavity For Supersonic Mixing Enhancement

A "swallowtail" cavity for the supersonic combustor was proposed to serve as an efficient flame holder for scramjets by enhancing the mass exchange between the cavity and the main flow. A numerical study on the "swallowtail" cavity was conducted by solving the three-dimensional Reynolds-averaged Navier-Stokes equations implemented with a k-epsilon turbulence model in a multi-block mesh. Turbulence model and numerical algorithms were validated first, and then test cases were calculated to investigate into the mechanism of cavity flows. Numerical results demonstrated that the certain mass in the supersonic main flow was sucked into the cavity and moved spirally toward the combustor walls. After that, the flow went out of the cavity at its lateral end, and finally was efficiently mixed with the main flow. The comparison between the "swallowtail" cavity and the conventional one showed that the mass exchanged between the cavity and the main flow was enhanced by the lateral flow that was induced due to the pressure gradient inside the cavity and was driven by the three-dimensional vortex ring generated from the "swallowtail" cavity structure.

Self-organized generation of transverse waves in diverging cylindrical detonations

Self-organized generation of transverse waves associated with the transverse wave instabilities at a diverging cylindrical detonation front was numerically studied by solving two-dimensional Euler equations implemented with an improved two-step chemical kinetic model. After solution validation, four mechanisms of the transverse wave generation were identified from numerical simulations, and referred to as the concave front focusing, the kinked front evolution, the wrinkled front evolution and the transverse wave merging, respectively. The propagation of the cylindrical detonation is maintained by the growth of the transverse waves that match the rate of increase in surface area of the detonation front to asymptotically approach a constant average number of transverse waves per unit length along the circumference of the detonation front. This cell bifurcation phenomenon of cellular detonations is discussed in detail to gain better understanding on detonation physics.

Laminar Burning Velocities and Markstein Lengths of Premixed Methane/Air Flames near the Lean Flammability Limit in Microgravity

Effects of flame stretch on the laminar burning velocities of near-limit fuel-lean methane/air flames have been studied experimentally using a microgravity environment to minimize the complications of buoyancy. Outwardly propagating spherical flames were employed to assess the sensitivities of the laminar burning velocity to flame stretch, represented by Markstein lengths, and the fundamental laminar burning velocities of unstretched flames. Resulting data were reported for methane/air mixtures at ambient temperature and pressure, over the specific range of equivalence ratio that extended from 0.512 (the microgravity flammability limit found in the combustion chamber) to 0.601. Present measurements of unstretched laminar burning velocities were in good agreement with the unique existing microgravity data set at all measured equivalence ratios. Most of previous 1-g experiments using a variety of experimental techniques, however, appeared to give significantly higher burning velocities than the microgravity results. Furthermore, the burning velocities predicted by three chemical reaction mechanisms, which have been tuned primarily under off-limit conditions, were also considerably higher than the present experimental data. Additional results of the present investigation were derived for the overall activation energy and corresponding Zeldovich numbers, and the variation of the global flame Lewis numbers with equivalence ratio. The implications of these results were discussed. 2010 The Combustion Institute. Published by Elsevier Inc. All rights reserved.