FTIR遥测固体推进剂燃烧温度

应用遥感FTIR对固体推进剂燃烧火焰的温度进行了研究。遥感FTIR光谱仪在光谱分辨率为4cm^-1时,连续收集燃烧火焰的发射光谱。分别利用分子基带转振光谱测温法,以及分子发射光谱最大强度谱线测温法,对燃烧温度进行了遥感实时测定。文中列出了两种方法测得的各时刻的火焰温度。结果表明。两种方法在测量快速、剧烈燃烧的火焰温度时,都是很可靠的方法,当火焰的燃烧比较稳定时,分子发射光谱最大强度谱线测温法更为简便、快速。     

被动式FTIR遥感掺纳米材料固体推进剂的燃烧火焰温度

应用被动式遥感FTIR,分别对掺入纳米级金属氧化物、掺入同种材料普通金属氧化物及无掺入物的固体推进剂的燃烧火焰温度进行了测量.固体推进剂的主要成分为硝化棉和硝化甘油.掺加物分别为6 nm CuO,56 nm Fe2O3,16 nm NiO粒子及相应的普通金属氧化物.FTIR仪器分辨率为1 cm.利用燃烧产物中H2O分子在2.75μm处的基带发射光谱精细结构,根据分子转振光谱测温法,计算出燃烧火焰温度.结果表明,掺有纳米级CuO,Fe2O3和NiO粒子的固体推进剂的燃烧火焰温度分别为3 089,3 193和3 183 K,此温度与掺入同种材料的普通金属氧化物和无掺入物的固体推进剂的燃烧火焰温度无明显差别.     

甲醇-空气和甲醇-空气-稀释气预混层流燃烧特性

本文利用定容燃烧弹研究了不同初始压力、初始温度、气体稀释度和燃空当量比下甲醇-空气-稀释气预混层流燃烧特性.结果表明:对于给定初始压力和温度,甲醇-空气预混合气的质量燃烧率、燃烧压力和温度的最大值均出现在当量比1.左右,而火焰发展期和燃烧期在此当量比下最短.火焰发展期、燃烧期和燃烧压力峰值随初始温度的增加而减小,最高燃烧温度随初始温度的增加而增加,燃烧压力峰值和最高燃烧温度随初始压力的增加而增加.火焰发展期和燃烧期随稀释度的增加而增加,而燃烧压力峰值和最高燃烧温度随稀释度的增加而降低.     

红外光谱遥测固体推进剂燃烧温度及有机化合物对其影响

本文用遥感FTIR光谱 ,测定了固体推进剂燃烧火焰在光谱范围为 4 5 0 0～ 70 0cm- 1 处的红外发射光谱 ,利用HCl分子转振基带 (3 4 6 μm)精细结构的P 分支光谱 ,准确测定了固体推进剂燃烧火焰温度 ,并对含有不同材料固体推进剂 ,如有机化合物对燃烧温度的影响 ,作了讨论。     

用相对强度法测量固体推进剂火焰温度分布

许多高温体如火焰，由于本身伴随着非常复杂的化学反应，辐射出的光谱非常复杂。这些光谱通常包括连续谱、谱线和谱带三部分，而且在许多情况下谱线非常密集。如果用谱线强度法测温，就会发现由于谱线非常密集，很难找到合适的孤立谱线。文章针对这些密集谱线，在特定条件下提出用多条谱线的总强度代替一条谱线的强度来测量温度的方法，改进了常用的相对强度法表达方式，使用密集谱线的总强度与另一条谱线强度的比值来计算温度，成功测量了固体推进剂火焰的温度分布，并将结果和热电偶测量的结果做了比较。     

天然气在不同初始温度和压力下的燃烧特性研究

利用定容燃烧弹研究了不同初始温度和初始压力下的天然气燃烧特性,分析了初始温度、初始压力和当量比对其燃烧过程的影响.研究结果表明:随着初始温度的升高(300～450 K),天然气质量燃烧速率明显增加,燃烧持续期和火焰发展期显著缩短.随着初始压力的升高(0.1～0.75 MPa),天然气质量燃烧速率明显减慢,燃烧持续期和火焰发展期显著增长.且稀混合气和浓混合气条件下初始温度和初始压力的变化对燃烧持续期和火焰发展期的影响更明显.     

基于辐射法和原子发射光谱法的转炉口火焰温度测量

转炉炼钢的终点控制包括钢水出钢时温度及其成分的控制,炉口火焰能够反映炉内脱碳速率及转炉运行参数等。工业炉燃烧火焰可见光谱段,普遍存在着钾(K)和钠(Na)等碱金属元素的原子发射谱线,利用K的特征谱线相对比值可以计算火焰温度。基于辐射双色法,三色法和谱线相对强度法对转炉口火焰温度进行了测量;数据处理过程中对特征谱线进行了基线拟合提取,小波脊线拟合提取;特征谱线进行了Gauss函数和Lorenz函数拟合。结果表明,辐射测温法对谱线比较敏感,选择合理的波段能够有效,精确地测量火焰温度;采用谱线相对强度法受制于特征谱线的数学模型、谱线的跃迁机率、能级的简并度及火焰的光学厚度,需要分辨率非常高的光谱仪才能进行高温转炉火焰中电子温度的测量。     

甲烷-空气预混V形火焰的CARS实验研究

本文将相干反斯托克斯(CARS)理论光谱计算和实验光谱分析的方法应用于预混V形火焰燃烧的温度测量实验,利用N2的Q支CARS谱线,使用单脉冲宽带方法获得了预混V形火焰的CARS信号光谱强度特性,测量了V形火焰水平方向和竖直方向上的温度分布特征,从中得出了火焰锋面的厚度,分析了火焰锋面的皱褶与摆动对CARS信号的影响。同时测量了不同燃料系数下V形火焰燃烧产物的温度,得出了温度随燃料系数的变化趋势,为进一步研究预混 V形火焰的结构提供了依据。     

利用辐射光谱法在线测量固体火箭推进剂燃烧温度（英文）

针对固体火箭发动机恶劣环境下的高温燃烧测量问题,提出了利用辐射光谱法来开展固体火箭推进剂燃烧温度在线测量的方法,采用200～1 100nm光纤光谱仪测量了高压实验燃烧器下固体火箭推进剂燃烧火焰辐射光谱,总结了其光谱特性,并基于普朗克定律和光谱拟合方法获得了相应的推进剂燃烧温度,这对固体火箭推进剂燃烧诊断与燃烧机理研究具有重要的参考价值。     

利用辐射光谱法在线测量固体火箭推进剂燃烧温度

针对固体火箭发动机恶劣环境下的高温燃烧测量问题，提出了利用辐射光谱法来开展固体火箭推进剂燃烧温度在线测量的方法，采用200～1 100 nm光纤光谱仪测量了高压实验燃烧器下固体火箭推进剂燃烧火焰辐射光谱，总结了其光谱特性，并基于普朗克定律和光谱拟合方法获得了相应的推进剂燃烧温度，这对固体火箭推进剂燃烧诊断与燃烧机理研究具有重要的参考价值。     

一种测量发光火焰温度的数据处理方法研究

火焰温度是燃烧诊断的重要参数之一,它对研究各种燃烧过程具有重要价值。根据多光谱辐射测温所用的参考温度数学模型,提出了一种基于遗传算法的新的数据处理方法。该方法对火焰发射率与波长的关系依次进行了三点直线拟合,并通过遗传算法进行了优化,从而得到了发光火焰的温度和发射率。采用多波长高温计测量了某种固体推进剂燃烧火焰的自辐射光谱,并进行了数据处理。计算结果表明:火焰温度计算值与理论值之差在±100K以内;这种基于遗传算法的新的数据处理方法是测量发光火焰温度的一种可行性方法。     

Flame structure of HMX/GAP propellant at high pressure

The chemical and thermal structure of a HMX/GAP propellant flame was investigated at a pressure of 0.5 MPa using molecular beam mass spectrometry and a microthermocouple technique. The pressure dependence of the burning rate was measured in the pressure range of 0.5–2 MPa. The mass spectrometric probing technique developed for flames of energetic materials was updated to study the chemical structure of HMX/GAP flames at high pressures. Eleven species, including HMX vapor, were identified, and their concentrations were measured in a zone adjacent to the burning surface at pressures of 0.5 and 1 MPa. Temperature profiles in the propellant combustion wave were measured at pressures of 0.5 and 1 MPa. Species concentration profiles were measured at 0.5 MPa. Two main zones of chemical reactions in the flame were found. The data obtained can be used to develop and validate combustion models for HMX/GAP propellants.     

Structure,equation of state and elasticity of crystalline HNIW by molecular dynamics simulations

We have performed theoretical investigations on the structure, equation of state (EOS), elasticity, and mechanical properties of 2, 4, 6, 8, 10, 12-Hexanitrohexaazaisowurzitane (HNIW) energetic material by molecular dynamics (MD) simulations. The lattice parameters and equations of state of the four polymorphs (ε-, γ-, β-, and α-HNIW) under high pressure are calculated. Our calculated results agree with the previous experiments and theoretical calculations. Meanwhile, the elastic constants and some other mechanical properties of the most stable ε-HNIW under high pressure and temperature are predicted successfully.     

单元推进剂液滴在高温高压下的微爆现象观测

 利用挂滴装置和高速摄影系统研究了单元推进剂LP1846液滴在0.2～4.0 MPa、673～973 K工况下的微爆特性。观察到液滴在不同环境压力和温度下的3种微爆模式,即液滴在着火前的轻度破碎、液滴在燃烧时的部分破碎和全部爆碎,并给出了微爆过程的特征照片,定量测试了液滴微爆延迟期、微爆温度和微爆直径与环境压力、温度的关系。初步分析了液滴微爆机理,认为第一种微爆机理主要是水组分的过热,第二、三种微爆机理是液相化学反应。研究结果对控制LP1846燃烧稳定性和指导液体发射药火炮内弹道设计均有参考价值。     

宽带相干反斯托克斯喇曼散射法诊断固体燃剂燃烧场

 报道了采用单次脉冲非稳腔空间增强探测 相干反斯托克斯喇曼散射（USED CARS）技术诊断常压下固体燃剂瞬态燃烧场温度和氮气浓度。采用宽带USED CARS技术，在固体燃剂瞬态燃烧场获得了较高信噪比的单次激光脉冲氮气Q支CARS实验谱，用CARS理论计算软件拟合CARS实验谱，给出了固体燃剂瞬态燃烧场温度和氮气浓度在不同高度的分布，固体燃剂燃烧场温度约2 250K、氮气相对浓度16%～20%。     

Experimental study of linear burning rates of liquid nitromethane using a novel high-pressure continuous feed liquid strand burner

A novel high-pressure strand burner with the ability to maintain a continuous feed of a liquid monopropellant is used to investigate the linear burning rates of liquid nitromethane as a function of chamber pressure. A new procedure for obtaining linear burning rates is presented. The present study investigates that pressure dependence in a subset of the low-pressure region, ranging from 3  to 8 MPa, which corresponds to a region with significant discrepancies in existing literature. The linear burning rate of liquid nitromethane is known to have a pressure dependence that follows Saint Robert’s Law in select pressure regions. The results fall between the upper and lower limits of existing literature with a pressure exponent of n = 1.106. To complement the experimental results, numerical simulations of a simple 1D burner-stabilized flame were conducted with three different nitromethane mechanisms. Similar to the experimental results, the simulations showed significant discrepancies for the predicted flame temperatures and heat release rate for nitromethane combustion in an inert environment. The combined experimental and modeling results highlight the need to further investigate the sensitivity of the reaction kinetics to different external factors.     

Quantitative measurement of temperature in oxygen enriched CH4/O2/N2 premixed flames using Laser Induced Thermal Grating Spectroscopy (LITGS) up to 1.0 MPa

The application of laser diagnostics to high pressure combustion phenomena is particularly challenging, especially in practical combustors such as rocket motors. In this study, temperature measurements using Laser Induced Thermal Grating Spectroscopy (LITGS) are demonstrated in oxygen enriched CH₄/O₂/N₂ premixed laminar flames at pressures up to 1.0?MPa. We use a previously developed OH absorption LITGS technique to determine product gas temperatures from 0.3 to 1.0?MPa, for both high temperature oxygen-enriched and pure-oxygen flames, for measurements up to 3000?K. Further, we demonstrate how it is necessary to correct the measurements for the local absorption of laser light to obtain accurate temperatures, and offer a technique for producing the correction by using different laser energies. Once the correction is applied, we demonstrate that the measurements at 0.5?MPa are within 1.6% of the adiabatic non-strained flame temperatures, with a standard deviation of about 160?K, thus offering a competitive method for the challenging conditions at high pressures and temperatures. The values obtained at derived temperatures at 1.0?MPa were lower than the adiabatic unstrained flame temperatures, which could possibly be attributed to loss mechanisms.     

Absolute OH concentration profiles measurements in high pressure counterflow flames by coupling LIF, PLIF, and absorption techniques

A high-pressure combustion chamber enclosing counterflow burners was set-up at ICARE-CNRS laboratory. It allows the stabilization of flat twin premixed flames at atmospheric and high pressure. In this study, lean and stoichiometric methane/air counterflow premixed flames were studied at various pressures (0.1?MPa to 0.7?MPa). Relative OH concentration profiles were measured by Laser Induced Fluorescence. Great care was attached to the determination of the fluorescence signal by taking into account the line broadening and deexcitation by quenching which both arise at high pressure. Subsequently, OH profiles were calibrated in concentration by laser absorption technique associated with planar laser induced fluorescence. Results are successfully compared with literature. The good quality of the results attests of the experimental set-up ability to allow the study of flame structure at high pressure.     

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.     

Experimental investigation of ethylene/air combustion instability in a model scramjet combustor using image-based methods

The combustion instabilities of supersonic combustion were investigated experimentally in a laboratory-scale scramjet combustor with a cavity flame holder. Ethylene was injected transversely from an orifice to the supersonic flow of Mach 2 with a stagnation temperature of 1900 K and a total pressure of 0.37 MPa. The dynamic pressure, CH* chemiluminescence and shadowgraph images were measured with a pressure sensor and a high-speed video camera. Dynamic pressure was analyzed by fast Fourier transform, and time-resolved CH* chemiluminescence images were modally decomposed by the sparsity-promoting dynamic mode decomposition (SP-DMD). The results indicated that two combustion instabilities were observed for cavity shear-layer stabilized combustion and the oscillation between jet-wake stabilized and cavity shear-layer ram combustions for the power spectral density (PSD) of pressure. In the case of the combustion instability of cavity shear-layer stabilized combustion, a dominant peak of approximately 128 Hz was observed for the PSD of pressure. This instability corresponded to an entire flame oscillation of the cavity shear-layer stabilized combustion, which was validated by the SP-DMD and a low rank reproduction with 10 modes. This was driven by a fuel injection oscillation in the injection orifice. In the case of oscillation between the jet-wake stabilized and the cavity shear-layer ram combustions, peaks around 1600 Hz were observed for the PSD of pressure. This mechanism was also explained by the SP-DMD modes and a low rank reproduction using within 10 modes. The DMD and shadowgraph images indicated that the vortex formed by a separation of the boundary layer induced a strong jet-wake flame, resulting in the temporal thermal choke followed by cavity shear-layer stabilized ram combustion. The data-driven approach with SP-DMD clarified the combustion instability mechanisms of the supersonic combustion in detail.