甲烷层流和湍流预混火焰OH^*和CH^*的化学发光特性

化学发光能够对火焰结构和燃烧过程进行良好的表征,但利用化学发光对湍流火焰进行测量的研究相对较少。为了更深入地研究和发展湍流燃烧理论,设计了伴燃射流燃烧器,通过ICCD相机和相应滤波片获取了OH^*和CH^*的化学发光图像,对甲烷/空气层流和湍流预混火焰的化学发光特性进行了研究,并利用分布高度、峰值位置、强反应区占比、峰值等参数对不同速度和当量比时的OH^*和CH^*进行表征。结果表明,层流时OH^*和CH^*的分布明显不同,而湍流的混合作用导致二者的分布范围趋向一致。随着当量比增大,不同速度下OH^*和CH^*的分布高度都呈单调递增趋势,但湍流的增长趋势要相对平缓;峰值位置的变化趋势与分布高度几乎一致,间接表明OH^*和CH^*的主导生成反应不变。强反应区占比在层流和湍流状态下的表现完全相反:从贫燃到富燃,层流中由大于0.1降低到0.05以下,而湍流中则由0.05上升到0.1以上,表明湍流对贫燃时的燃烧反应起抑制作用,在富燃时反而起促进作用。另外, OH^*和CH^*的峰值变化可以对火焰的流动状态进行判断,且CH^*尤为明显:随当量比增加,如果峰值先升后降,则可以认为火焰为层流状态;如果峰值单调递增,则是湍流状态。以速度和当量比为自变量,以OH^*和CH^*的峰值比为因变量,提出了不同速度条件下利用化学发光对当量比进行定量表征的统一关系式,解决了不同速度时需要分别进行拟合的问题,对后续的化学发光燃烧诊断研究具有重要意义。     

甲烷/空气同轴射流火焰反应热与OH~*/CH~*定量表征特性研究

激发态粒子是化学反应过程的天然示踪剂,当前激发态粒子研究主要都是在一维简单火焰下进行。为了考察复杂情况下激发态分布对化学反应热的定量表征规律,进行了甲烷/空气同轴射流扩散火焰的试验,开展了甲烷/空气详细燃烧机理与激发态燃烧机理的同轴射流预混火焰和扩散火焰的数值模拟,分析了OH~*和CH~*的分布特性,研究了激发态对反应热的表征关系。结果表明:通过试验ICCD相机和相应滤光片获取的OH~*和CH~*的化学发光图像和数值模拟中OH~*和CH~*摩尔分数分布的模拟结果吻合, OH~*分布主要分为三个燃烧区域, CH~*分布主要为两个燃烧区域。扩散火焰中OH~*和CH~*分布呈现单峰,反应热呈现双峰现象,反应热与激发态变化趋势相似,达到第一峰值后激发态逐渐减小为零,而反应热达到第一峰值后先降低再缓慢上升到第二峰值,最后减小至零。扩散火焰中沿轴向方向,当C_2H+O=CH~*+CO(R12)反应速率达到峰值时,反应热达到第一波峰; H+O+M=OH~*+M(R2)反应速率达到峰值时,反应热达到第二波峰。预混火焰中随着局部当量比的增加, OH~*和CH~*的摩尔分数明显增大,分布区域更广;反应热和激发态粒子OH~*和CH~*的分布趋势一样,在激发态粒子OH~*和CH~*质量分数增大时,反应热也增大,当激发态粒子OH~*和CH~*的质量分数达到峰值的时候,反应热也达到峰值;沿轴向方向, OH~*和CH~*的四个生成反应速率的峰值都在同一位置,反应热也达到最大值, CH+O_2=OH~*+CO(R1)和C_2H+O=CH~*+CO(R12)反应速率相比H+O+M=OH~*+M(R2)和C_2H+O_2=CH~*+CO_2(R11)反应速率更快。     

热氧喷嘴水煤浆扩散火焰辐射光谱特性研究

火焰的辐射光谱可为燃烧诊断提供诸多信息,因此目前对简单的气态火焰自由基辐射特性已进行了大量研究,而关于非均相火焰的辐射光谱特性研究则相对较少。采用改进的热氧喷嘴技术在敞开空间下直接点燃水煤浆,并利用光纤光谱仪和紫外成像系统,着重对甲烷和水煤浆火焰的辐射光谱及OH*的二维分布特性进行研究。结果表明：与甲烷火焰的光谱辐射相比,水煤浆火焰不仅存在OH*,CH*和C₂*特征辐射,还产生了Na*,Li*,K*和H*的发射谱线,并出现了连续的黑体辐射,这些光谱辐射特征可作为水煤浆气化或燃烧的标志,也可作为水煤浆是否点燃的判据;通入水煤浆后,OH*强度明显下降,而CH*和C₂*强度增大。对比甲烷火焰OH*二维分布,水煤浆火焰OH*峰值强度明显下降,化学反应区域面积显著减小;沿着火焰传播方向,甲烷和水煤浆火焰轴向的OH*强度均呈先增大后减小的趋势;甲烷火焰径向的OH*在反应核心区出现了双峰形态分布,而水煤浆火焰OH*径向始终呈单峰分布。随着氧碳当量比增大,水煤浆火焰OH*的存在范围扩大,说明氧气的增加促进了OH*的产生;随水煤浆流量提高,OH*的反应核心区域缩小,峰值强度明显下降,CH*,C₂*,Na*,Li*,K*和H*的强度显著增强,连续的黑体辐射强度也明显增大,这些辐射光谱的变化可用于表征操作负荷的变化。     

基于高光谱技术的甲烷层流预混火焰自由基特性研究

高光谱技术提供了空间和光谱维度的信息,同时基于传统黑体模型的实验技术和计算方法不适用于甲烷火焰的辐射特性,而火焰中自由基的高光谱信息反映了火焰结构、组分浓度分布等燃烧的多方面特征,能够为燃烧模型的完善提供依据。利用高光谱技术在不同当量比和不同流量下研究了甲烷预混火焰中自由基的空间和光谱特性。对不同当量比的研究表明,随着当量比的增加,火焰中心处的CH*和C*₂自由基的辐射强度先增加后降低,而燃烧区域内二者的平均辐射强度一直增加,火焰中心处的点可以表征局部的燃烧状态,而燃烧区域内辐射均值表征热释率等整体燃烧状态,定量给出了两种方法的不同趋势。火焰中心处的CH*自由基辐射强度在当量比为1.01时达到峰值,而C*₂自由基辐射强度在当量比为1.12时达到峰值,两种自由基的辐射峰值可以分别作为燃烧中反应强度和稳定性的判据。当量比可以由C*₂和CH*辐射强度之比来表征,修正了C*₂/CH*和当量比的线性关系,提出应使用燃烧区域内C*₂和CH*的平均辐射强度之比,并提出了该比值与当量比的二次关系。利用高光谱技术生成了燃烧区域内C*₂/CH*的云图,得到了详细的空间信息,当量比大于1时,首次在火焰面附近发现了明显的过渡区,体现了高光谱技术的优势。对当量比保持不变情况下的不同流量的研究表明,随着流量的增加,火焰高度增加,而火焰顶部和火焰中心的自由基的浓度分布基本不发生变化,揭示了实验工况下流动的特征时间远小于化学反应特征时间,化学反应过程未受到明显影响。应用高光谱较好的识别出了火焰中的多种自由基,研究了甲烷层流预混火焰中自由基辐射特性及其随着不同当量比和流量变化的趋势,对燃烧现象和机理的认识具有重要意义。     

气化炉内柴油火焰光谱辐射特性及CH*二维辐射特性研究

火焰的自发辐射光谱与火焰的结构、温度分布等燃烧特征参数密切相关。对激发态自由基辐射的辐射强度与二维分布进行研究,可清晰地反映火焰燃烧状态而不对火焰产生扰动。基于多喷嘴对置式气流床气化实验平台,利用光纤光谱仪和配置CCD相机的高温内窥镜,对柴油扩散火焰的辐射光谱及CH*辐射二维分布特性进行研究。考察了当量比和撞击作用对火焰辐射光谱和CH*辐射分布的影响。结果表明,柴油火焰在306.47及309.12 nm处存在OH*辐射特征峰,在431.42 nm处存在CH*辐射特征峰,且存在明显的碱金属原子Na*(589.45 nm),K*(766.91和770.06 nm)发射光谱。此外,由于柴油不完全燃烧生成大量碳黑,在辐射光谱的可见光波段产生了强烈的连续黑体辐射。火焰中的黑体辐射对CH*辐射特征峰的检测存在干扰,且当量比越低时背景辐射越强,对自由基特征峰检测干扰越大。基于普朗克定律利用插值法可扣除430 nm附近波段背景辐射。柴油火焰中CH*辐射峰值随当量比的增加单调减小,CH*辐射等值线沿火焰发展方向依次出现三峰状、双峰状及单峰状,最终收缩为以反应核心区为中心的圆核。随着当量比的提高,出现各个形状的CH*辐射强度阈值不断降低,火焰主反应区面积减小且向下游移动,当量比增加到1.0附近时,理论上柴油完全燃烧,CH*辐射强度显著降低,贫燃火焰的CH*辐射强度及分布区域几乎稳定不变。利用CH*辐射强度值判定火焰举升长度,对于单喷嘴射流火焰,火焰举升长度随当量比的增加经历了显著增加后小幅下降的过程。相同当量比时两喷嘴撞击火焰CH*辐射强度峰值始终高于单喷嘴射流火焰对应值;火焰举升长度随当量比的增加小幅增加。火焰撞击的约束作用使得火焰举升长度不易随着当量比变化发生较大波动,燃烧更加稳定。这为定量判断火焰燃烧状态提供了一种直观、有效的方法,同时为柴油燃烧的化学动力学研究提供了实验依据。     

甲烷-空气预混火焰中OH∗,CH∗发光的定量测量及模拟

基于燃烧化学自发光的诊断技术对发动机诊断、监控有重要意义.针对碳氢燃料燃烧中OH*，CH*激发态物质的生成机理，及其与释热率、当量比的关系进行了实验与模拟探究.首先，利用提出的辐射标定手段对当量比0.7~1.33范围内甲烷-空气预混火焰进行了化学发光量化测量，通过波长分辨的光学收集系统，同时获得各发光组分的浓度，具有很强的便利性.然后采用一维燃烧反应模拟，对与实验工况相同条件下的发光辐射进行定量计算，并对比了释热分布与激发态物质（OH*，CH*，C₂*，CO₂*）的相互关系，计算结果表明，在甲烷-空气层流火焰中，OH*，CH*最合适标识释热率，C₂*次之，CO₂*与释热率分布几乎无相关性.通过实验与计算的对比结果，分析了现有OH*，CH*的各反应通道和常数的准确度，并评估了两自发光组分的主要生成反应路径.      

甲烷/氧气层流反扩散火焰形态及滞后特性研究

对空气气氛中甲烷/氧气反扩散火焰的形态和推举滞后特性进行了实验研究. 实验中通过改变气体流量考察了气速变化对火焰形态演变及滞后特性的影响, 并利用紫外相机系统研究了气速对不同形态火焰中OH^*分布的影响. 研究结果表明: 甲烷气速、氧气气速和火焰的历史状态是决定火焰形态的三个重要参数, 并以此对实验范围内的火焰形态进行了分区; 氧气气速对不同形态反扩散火焰轴线上的OH^*分布有相似的影响, 当氧气缺乏时, 反扩散反应区较短, 当氧气富余时, 反扩散反应区在轴向分布较广; 同轴甲烷的气速对反扩散火焰的滞后特性影响显著, 随着甲烷气速的增加, 反扩散火焰的推举速度和再附着速度呈线性减小, 部分预混火焰向反扩散火焰转变的速度呈线性增加.     

介质阻挡体放电对甲烷扩散火焰特性的影响

本文在高频交流激励模式下,采用同轴圆柱构型激励器,开展了介质阻挡体放电对空气/甲烷同轴剪切扩散火焰燃烧特性影响实验研究。激励器敷设在外喷嘴环缝以电离空气,采用纹影系统和B型热电偶分别获取流场形态和火焰温度,激励频率为8 kHz,通过改变气体流量和放电电压,分析了不同工况下射流流场、火焰结构和火焰温度在等离子体作用下的变化规律。结果表明:等离子体气动效应能有效增强射流湍流强度,强化空气/甲烷掺混,增大射流角,并随激励电压提高作用效果逐渐增强,实验中未形成明显扩张流动的初始射流在放电电压30 kV时其射流角最大为23.5°。贫燃条件下等离子体激励会改善火焰形态,增强燃烧稳定性,并在流量较低时缩短火焰长度。此外,富燃火焰下游温度会随着激励强度增大不断升高,而贫燃火焰下游温度变化受上游燃烧强度影响存在升高和降低两种情况。     

水雾作用下富燃料甲烷预混火焰化学发光特性

利用阶梯光栅光谱仪与自行研制的水雾协流管式燃烧器,对富燃料甲烷/空气层流预混火焰化学发光特性进行实验研究.分析了锥形预混火焰燃烧过程中火焰面OH、CH以及C2自由基粒子光谱强度分布规律,以及水雾协流作用下的预混火焰发射光谱特性,探讨了水雾液滴对富燃料甲烷预混火焰发射光谱的影响.实验结果表明:当水雾量充足时,作用于内锥火焰阵面的水雾液滴使得火焰阵面OH、CH以及C2自由基粒子发射光谱强度减弱,抑制预混火焰燃烧;当作用于火焰面的水雾载荷比较小时,富燃料预混火焰的OH、CH的发射光谱强度得到一定程度的增强.     

二维偏振光谱技术对燃烧场的诊断

利用单脉冲激光诱导偏振光谱技术测量了甲烷/空气预混火焰、酒精灯火焰和固体燃剂燃烧场中OH的二维分布。简述了激光诱导偏振光谱技术的基本原理和二维测量的实验方法;通过测量火焰中OH自由基A~2∑~+-X~2∏(0,0)跃迁带中Q1(8)吸收线的强度,获得了燃烧场中OH的二维分布。实验结果对了解火焰构造,研究燃烧机理等有一定的参考价值。     

NO and OH* emission characteristics of very-lean to stoichiometric ammonia–hydrogen–air swirl flames

One of the main concerns regarding ammonia combustion is its tendency to yield high nitric oxide (NO) emissions. Burning ammonia under slightly rich conditions reduces the NO mole fraction to a low level, but the penalties are poor combustion efficiency and unburnt ammonia. As an alternative solution, this paper reports the experimental investigation of premixed swirl flames fueled with ammonia-hydrogen mixtures under very-lean to stoichiometric conditions. A gas analyzer was used to measure the NO mole fraction in the flame and post flame regions, and it was found that low NO emissions (as low as 100 ppm) in the exhaust were achieved under very lean conditions (? ≈ 0.40). Low NO emission was also possible at higher equivalence ratios, e.g. ? = 0.65, for very large ammonia fuel fractions (X_NH3 > 0.90). 1-D flame simulations were performed to elaborate on experimental findings and clarify the observations of the chemical kinetics. In addition, images of OH* chemiluminescence intensity were captured to identify the flame structure. It was found that, for some conditions, the OH* chemiluminescence intensity can be used as a proxy for the NO mole fraction. A monotonic relationship was discovered between OH* chemiluminescence intensities and NO mole fraction for a wide range of ammonia-hydrogen blends (0.40 < ? < 0.90 and 0.25 < X_NH3 < 0.90), making it possible to use the low-cost OH* chemiluminescence technique to qualify NO emission of flames fueled with hydrogen-enriched ammonia blends.     

The effect of fuel inlet turbulence intensity on H2/CH4 flame structure of MILD combustion using the LES method

Large eddy simulations (LES) are employed to investigate the effect of the inlet turbulence intensity on the H₂/CH₄ flame structure in a hot and diluted co-flow stream which emulates the (Moderate or Intense Low-oxygen Dilution) MILD combustion regime. In this regard, three fuel inlet turbulence intensity profiles with the values of 4%, 7% and 10% are superimposed on the annular mixing layer. The effects of these changes on the flame structure under the MILD condition are studied for two oxygen concentrations of 3% and 9% (by mass) in the oxidiser stream and three hot co-flow temperatures 1300, 1500 and 1750 K. The turbulence-chemistry interaction of the numerically unresolved scales is modelled using the (Partially Stirred Reactor) PaSR method, where the full mechanism of GRI-2.11 represents the chemical reactions. The influences of the turbulence intensity on the flame structure under the MILD condition are studied by using the profile of temperature, CO and OH mass fractions in both physical and mixture fraction spaces at two downstream locations. Also, the effects of this parameter are investigated by contours of OH, HCO and CH₂O radicals in an area near the nozzle exit zone. Results show that increasing the fuel inlet turbulence intensity has a profound effect on the flame structure particularly at low oxygen mass fraction. This increment weakens the combustion zone and results in a decrease in the peak values of the flame temperature and OH and CO mass fractions. Furthermore, increasing the inlet turbulence intensity decreases the flame thickness, and increases the MILD flame instability and diffusion of un-burnt fuel through the flame front. These effects are reduced by increasing the hot co-flow temperature which reinforces the reaction zone.     

Low pressure premixed CH4/air flames with forced periodic mixture fraction oscillations: experimental approach

An experimental setup for the generation and investigation of periodic equivalence ratio oscillations in laminar premixed flames is presented. A special low-pressure burner was developed which generates stable flames in a wide pressure range down to 20 mbar and provides the possibility of rapid mixture fraction variations. The technical realization of the mixture fraction variations and the characteristics of the burner are described. 1D laser Raman scattering was applied to determine the temperature and concentration profiles of the major species through the flame front in correlation to the phase-angle of the periodic oscillation. OH* chemiluminescence was detected to qualitatively analyze the response of the flame to mixture fraction variations by changing shape and position. Exemplary results from a flame at p=69 mbar, forced at a frequency of 10 Hz, are shown and discussed. The experiments are part of a cooperative research project including the development of kinetic models and numerical simulation tools with the aim of a better understanding and prediction of periodic combustion instabilities in gas turbines. The focus of the current paper lies on the presentation of the experimental realization and the measuring techniques.     

Investigation of non-premixed flame combustion characters in GO_2/GH_2 shear coaxial injectors using non-intrusive optical diagnostics

Single-element combustor experiments are conducted for three shear coaxial geometry configuration injectors by using gaseous oxygen and gaseous hydrogen(GO2/GH2) as propellants. During the combustion process, several spatially and time- resolved non-intrusive optical techniques, such as OH planar laser induced fluorescence(PLIF), high speed imaging, and infrared imaging, are simultaneously employed to observe the OH radical concentration distribution, flame fluctuations, and temperature fields. The results demonstrate that the turbulent flow phenomenon of non-premixed flame exhibits a remarkable periodicity, and the mixing ratio becomes a crucial factor to influence the combustion flame length. The high speed and infrared images have a consistent temperature field trend. As for the OH-PLIF images, an intuitionistic local flame structure is revealed by single-shot instantaneous images. Furthermore, the means and standard deviations of OH radical intensity are acquired to provide statistical information regarding the flame, which may be helpful for validation of numerical simulations in future. Parameters of structure configurations, such as impinging angle and oxygen post thickness, play an important role in the reaction zone distribution. Based on a successful flame contour extraction method assembled with non-linear anisotropic diffusive filtering and variational level-set, it is possible to implement a fractal analysis to describe the fractal characteristics of the non-premixed flame contour. As a result, the flame front cannot be regarded as a fractal object. However, this turbulent process presents a self-similarity characteristic.     

Effects of the penetration height of ethylene transverse jets on flame stabilization behavior in a Mach 2 supersonic crossflow

Effects of fuel jet penetration height on supersonic combustion behaviors were investigated experimentally in a supersonic combustion ramjet model combustor at a Mach speed of 2 and at a stagnation temperature of 1900 K. The jet-to-crossflow momentum flux ratio was varied to control the fuel-jet penetration height, using several injectors with different orifice diameters: 2, 3, and 4 mm. First, transverse nitrogen jets were observed to identify a relationship between the fuel jet penetration height and the momentum flux ratio by focusing Schlieren photography. Then, supersonic combustion behaviors of ethylene were investigated through combustion pressure measurements. Simultaneously, time-resolved images of CH* chemiluminescence and shadowgraphs were recorded with high-speed video cameras. Furthermore, a morphology of supersonic combustion modes was investigated for various equivalence ratios and fuel penetration heights in a two-dimensional latent space trained by the shared Gaussian process latent variable models (SGPLVM), considering CH* chemiluminescence images and the shock parameters. The results indicated that the penetration height of nitrogen jets was a function of the jet momentum flux ratio; this function was expressed by a fitting curve. Five typical combustion modes were identified based on time-resolved CH* chemiluminescence images, shadowgraphs, and pressure profiles. Even for a given equivalence ratio, different combustion modes were observed depending on the fuel penetration height. For an injection diameter of 3 and 4 mm, cavity shear-layer and jet-wake stabilized combustions were observed as the scram modes. On the other hand, although the cavity shear-layer and lifted-shear-layer stabilized combustions were observed, no jet-wake stabilized combustion was observed for an orifice diameter of 2 mm. Fuel penetration heights above the cavity aft wall were expected to affect the combustion behavior. Finally, a morphology of the supersonic combustion modes was clearly shown in the two-dimensional latent space of the SGPVLM.