泡沫陶瓷内火焰分布的ECT可视化研究

本文运用电容层析成像(ECT)方法,以非侵入的方式,对多孔介质燃烧中的火焰分布进行可视化测量.针对高孔隙率泡沫陶瓷(8PPI)的孔隙结构特点,提出了一种"十字架形"几何结构模型,用丁泡沫型多孔介质内甲烷-空气预混燃烧的二维数值模拟.ECT成像结果与数值模拟结果吻合,显示了两个不同学科信息的融合性和互验性.     

小尺度多孔介质燃烧室中火焰分布的电容层析成像测量

电容层析成像(ECT)是一项极具应用前景的过程成像测量技术,该技术具有非侵入、响应快、系统简单等诸多优点。本文成功地将ECT应用于小尺度多孔介质燃烧室中着火、熄火、不稳定燃烧等过程的参数分布检测,检测结果为微燃烧研究提供了重要的依据,同时验证了小尺度燃烧空间中填加多孔介质能显著提高燃烧效率及燃烧稳定性的特点。本文对火焰的介电特性进行了探讨,提出了火焰复等效介电系数模型,给出了火焰复等效介电系数与燃烧场宏观物理量之间定性关系,填补了ECT对火焰感应机理未知的空白。     

新型ECT传感器在燃烧检测中的应用研究

电容层析成像(ECT)是一项基于电容敏感原理的过程成像技术,是极具应用前景的多相流检测技术之一.本文提出了一种新型ECT传感器,该型传感器具有采集信号强、噪音小、结构稳定、有利于高温环境参数检测等优点.本文将该型传感器应用于多孔介质内火焰分布的检测,分析比较了不同燃气/空气流量、不同孔密度分布对燃烧特性的影响,验证了多孔介质内燃烧的优越性,同时证明了该型传感器应用于高温环境的参数检测是完全可行的.     

多孔介质中甲烷预混气火焰传播特性实验研究

本文对甲烷预混气在多孔介质中的火焰传播特性进行了实验研究,在开口竖直管中充填多孔介质,通过改变预混气氧含量使火焰在不同多孔介质中传播并测量火焰传播速度。预混气中氧含量最高达到29％。实验结果表明:多孔介质中甲烷可燃预混气火焰传播速度大于其层流火焰传播速度,可达到5倍以上(当量比的甲烷-空气预混气);多孔介质当量孔直径越大,或预混气层流火焰速度越高,则预混气火焰传播速度越高;多孔介质中可燃混气的火焰传播界限变小,当量孔直径大的多孔介质其界限值较大。实验结果与Babkin提出的多孔介质中的火焰传播机理相符。     

用于爆炸火焰真温场测量的多光谱热成像仪研究

温度是评估弹药热辐射毁伤的重要参数。弹药在引爆后会在极短时间内压缩周围空气并向四周猛烈释放出大量能量,伴随着能量释放弹药介质会急剧升温并形成火焰场,通过测量、分析火焰场的真温值,便可以得到爆炸火焰的空间热辐射毁伤效应。由于爆炸过程的强破坏性和瞬态性,爆炸火焰的测量主要是依靠辐射测温法。在以往研究中,已有学者针对爆炸火焰测量研制了相应的辐射测温仪器,但目前所研制的仪器只能测量出爆炸火焰在单波长下的亮温场,而单波长亮温场无法实现真温值的计算。针对这一问题,研制了一套多光谱热成像仪,该仪器采用多幅分光技术,可实现爆炸火焰在同时刻、不同波长下的分光成像,并利用高速CCD相机进行数据采集,最后依据多光谱辐射测温理论反演出爆炸火焰真温场。多幅分光技术是由远距离多孔分光镜头所完成的,该镜头主要分为两个部分：主成像镜头和分光镜头。主成像镜头的功能是对远距离爆炸火焰进行聚焦成像,其所成图像经由单凸透镜汇聚到正后方的多孔分光镜头上。多孔分光镜头内置分光光栏,光栏上可镶嵌不同波长的窄带滤光片,当入射光透过光栏上的窄带滤光片后,透射光便为被测目标的单波长辐射能量。远距离多孔分光镜头可对500 m以内的爆炸火焰...     

循环流化床返料系统固体颗粒微波多普勒测量

本文基于微波多普勒速度测量和电容层析成像浓度测量技术,研究循环流化床多分离器系统固体颗粒流量分配特性。其中微波多普勒测量系统主要由微波信号发射和接受天线、微波信号采集系统和分析软件组成.电容层析成像系统由电容传感器和电容采集模块构成。通过微波测量得到颗粒的平均速度,电容层析成像得到颗粒平均浓度分布,将上述两个参数结合,得到固体颗粒的流量。实验结果证实了电容和微波相结合对颗粒返料流率测量的可行性.     

基于多孔介质模型的40-T混合磁体CICC摩擦阻力特性分析

多孔介质理论被认为可能为CICC的热工水力特性提供理论支撑。通过多孔介质模型对40-T混合磁体外超导磁体的CICC导体进行分析计算,并用实验测量结果对渗透率、阻力系数、颗粒直径等参数进行修正,以探索CICC的多孔介质模型近似方法。     

基于LabVIEW的微小电容测量

针对电容层析成像技术中的微小电容测量的问题,以数字相敏检波原理为基础,LabVIEW软件及NI采集卡为核心设计了微小电容测量系统。LabVIEW程序控制NI采集卡产生激励信号加在微小电容两端,C/V转换电路将其转换为电压信号,NI采集卡将采集的电压信号传送到PC机中,并在LabVIEW程序中通过数字相敏检波算法对数据进行处理及显示。最终,通过对数据进行线性化,得到相应的测量电容值。实验结果表明,该系统具有精度高,线性度好,稳定性好等优点,可以满足电容层析成像系统中对微小电容的测量的要求。     

多孔介质体元内随机运动的核磁共振成像研究

多孔介质体元内随机运动的核磁共振成像是一种透视流体微观无规则运动的方法.在多孔介质中,存在两种无规则运动.一种是分于扩散.它是由于分子的布朗运动引起的;另一种是弥散,它是由多孔介质中毛管网络的复杂结构造成的.多孔介质中的液体弥散和分子扩散会在成像体无内产生相位分散.这种相位分散致使回波信号发生衰减.采用适当的梯度脉冲.可以从这种信号衰减中获得视扩散系数(ADC)的分布图像.本文作者在4.7T高场超导核磁共振成像系统上.采用特制的高梯度线圈获得了扩散和机扩散系数分布的图像.在水和丙酮模型中获得了扩散系教图像,其扩散系数值与标准值相符.在人体肾结石中获得了扩散系数分布图像,在不同流速下,获得了多孔介质中的视扩散系数分布图像.并分析了视扩散系数与速度的关系.在多孔介质中定量确定扩散系数和机扩散系数及其空间分布将会极大地提高核磁共振成像技术在渗流力学研究中的应用能力.     

湍流对多孔介质内预混火焰影响的初步研究

当气流速度较大时,多孔介质内预混燃烧的模拟需要考虑湍流的影响,本文利用简化的k-ε双方程湍流反应流模型对多孔介质内的预混火焰进行了数值模拟.结果表明,湍流大大加强了气流的组分和能世扩散,计算得到的火焰传播速度、CO及NO的排放量都与实验值符合得比较好,与层流模型相比,湍流模型能够改善计算结果.     

On the determination of laminar flame speed from low-pressure and super-adiabatic propagating spherical flames

The outwardly propagating spherical flame (OPF) method is popularly used to measure the laminar flame speed (LFS). Recently, great efforts have been devoted to improving the accuracy of the LFS measurement from OPF. In the OPF method, several assumptions are made. For examples, the burned gas is assumed to be static and in chemical equilibrium. However, these assumptions may not be satisfied under certain conditions. Here we consider low-pressure and super-adiabatic propagating spherical flames, for which chemical non-equilibrium exists and the burned gas may not be static. The objective is to assess the chemical non-equilibrium effects on the accuracy of LFS measurement from the OPF method. Numerical simulations considering detailed chemistry and transport are conducted. Stoichiometric methane/air flames at sub-atmospheric pressures and methane/oxygen flames at different equivalence ratios are considered. At low pressures, broad heat release zone is observed and the burned gas cannot quickly reach the adiabatic flame temperature, indicating the existence of chemical non-equilibrium of burned gas. Positive flow in the burned gas is identified and it is shown to become stronger at lower initial pressure. Consequently, the LFS measurement from OPF at low pressures is not accurate if the burned gas is assumed to be static and at chemical equilibrium. For super-adiabatic spherical flames, the burned gas speed is found to be negative due to the local temperature overshoot at the flame front. Such negative speed of burned gas can also reduce the accuracy of LFS measurement. It is recommended that the direct method measuring both flame propagation speed and flow speed of unburned gas should be used to determine the LFS at low pressures or for mixtures with super-adiabatic flame temperature.     

轴对称含烟黑火焰非均匀温度与烟黑浓度分布同时重建模拟研究

对于非均匀吸收、发射、无散射的轴对称含烟黑火焰对象,常规双色法不再适用。本文基于烟黑辐射特性,提出并模拟研究了同时重建火焰温度与烟黑容积份额的新的辐射测量方法。从重建结果看,重建误差主要集中在火焰中心区域,这是观测路径上测量误差累积的结果。温度重建主要受火焰断面参数分布类型影响,而烟黑容积份额重建主要受测量误差的影响,这由它们与单色辐射强度的内在关系所决定。     

Application of computed tomography to microgravity combustion

This paper describes applications of computed tomography (CT) to combustion phenomena under microgravity conditions. Infrared Thermography (IT) has been considered as a promising method for two-dimensional measurement of flames. We have applied IT to CT for a butane flame under microgravity conditions. The method joining spectroscopy to CT for diffusion flame of hydrogen has also been carried out. Intensity of chemical luminescence, which is originated from combustion-chemical reaction in the flame, can be measured by scanning a spectrometer with collimator. The effectiveness of the CT applications to microgravity combustion has been confirmed from two method.     

Simulation on simultaneous estimation of non-uniform temperature and soot volume fraction distributions in axisymmetric sooting flames

For visualizing non-uniform absorbing, emitting, non-scattering, axisymmetric sooting flames, because conventional two-color emission methods are no longer suitable, a three-color emission method for the simultaneous estimation of temperature and soot volume fraction distributions in these flames is studied in this paper. The spectral radiation intensities at wavelengths of red, green, and blue, which may be derived from color flame images, are simulated for the inverse analysis. Then the simultaneous estimation is carried out from the spectral radiation intensities by using a Newton-type iteration algorithm and the least-squares method. In this method, a factor is used to balance the wide variation of spectral radiation intensities due to both the wide ranges of temperature and wavelength of the flame radiation. The results indicate that the three-color method is suited for the reconstruction of flame structures with single or double peaks with small difference between the peak and valley. For a double-peaked flame structure with larger peak and valley difference, reasonable result can be obtained just when the mean square deviations of measurement data are small, for example, not more than 0.01.     

Analysis of Aluminum Dust Cloud Combustion Using Flame Emission Spectroscopy

In this study, aluminum flame analysis was researched in order to develop a measurement method for high-energy-density metal aluminum dust cloud combustion, and the flame temperature and UV-VIS-IR emission spectra were precisely measured using a spectrometer. Because the micron-sized aluminum flame temperature was higher than 2 400 K, Flame temperature was measured by a non-contact optical technique, namely, a modified two-color method using 520 and 640 nm light, as well as by a polychromatic fitting method. These methods were applied experimentally after accurate calibration. The flame temperature was identified to be higher than 2 400 K using both methods. By analyzing the emission spectra, we could identify AlO radicals, which occur dominantly in aluminum combustion. This study paves the way for realization of a measurement technique for aluminum dust cloud combustion flames, and it will be applied in the aluminum combustors that are in development for military purposes.     

Analysis of Aluminum Dust Cloud Combustion Using Flame Emission SpectroscopySCIEI北大核心CSCD

In this study, aluminum flame analysis was researched in order to develop a measurement method for high-energy-density metal aluminum dust cloud combustion, and the flame temperature and UV-VIS-IR emission spectra were precisely measured using a spectrometer. Because the micron-sized aluminum flame temperature was higher than 2 400 K, Flame temperature was measured by a non-contact optical technique, namely, a modified two-color method using 520 and 640 nm light, as well as by a polychromatic fitting method. These methods were applied experimentally after accurate calibration. The flame temperature was identified to be higher than 2 400 K using both methods. By analyzing the emission spectra, we could identify AlO radicals, which occur dominantly in aluminum combustion. This study paves the way for realization of a measurement technique for aluminum dust cloud combustion flames, and it will be applied in the aluminum combustors that are in development for military purposes.     

Measurements of burning velocities of dimethyl ether and air premixed flames at elevated pressures

Laminar burning velocities of dimethyl ether (DME) and air premixed flames at elevated pressures up to 10 atm were measured by using a newly developed pressure-release type spherical bomb. The measurement system was validated using laminar burning velocities of methane–air flames. A comparison with the previous experimental data shows an excellent agreement and demonstrates the accuracy and reliability of the present experimental system. The measured flame speeds of DME–air flames were compared with the previous experimental data and the predictions using the full and reduced mechanisms. At atmospheric pressure, the measured laminar burning velocities of DME–air flames are in reasonable agreement with the previous data from spherical bomb method, but are much lower than both predictions and the experimental data of the PIV based counterflow flame measurements. The laminar burning velocities of DME–air flames at 2, 6, and 10 atm were also measured. It was found that flame speed decreases considerably with the increase of pressure. Moreover, the measured flame speeds are also lower than the predictions at high pressures. In addition, experiments showed that at high pressures the rich DME–air flames are strongly affected by the hydrodynamic and thermal-diffusive instabilities. Markstein lengths and the overall reaction order at different equivalence ratios were extracted from the flame speed data at elevated pressures. Sensitivity analysis showed that reactions involving methyl and formyl radicals play an important role in DME–air flame propagation and suggested that systematic modification of the reactions rates associated with methyl and formyl formations are necessary to reduce the discrepancies between predictions and measurements.     

Laser imaging system for determination of three-dimensional scalar gradients in turbulent flames

An imaging system for the measurement of three-dimensional (3D) scalar gradients in turbulent hydrocarbon flames is described. Combined line imaging of Raman scattering, Rayleigh scattering, and CO laser-induced fluorescence (LIF) allows for simultaneous single-shot line measurements of major species, temperature, mixture fraction, and a one-dimensional surrogate of scalar dissipation rate in hydrocarbon flames, while simultaneous use of two crossed, planar LIF measurements of OH allows for determination of instantaneous flame orientation. In this manner the full 3D scalar dissipation can be estimated in some regions of a turbulent flame on a single-shot basis.     

A comparison of computational and experimental lift-off heights of coflow laminar diffusion flames

As a sensitive marker of changes in flame structure, the number densities of excited-state CH (denoted CH^*), and excited-state OH (denoted OH^*) are imaged in coflow laminar diffusion flames. Measurements are made both in normal gravity and on the NASA KC-135 reduced-gravity aircraft. The spatial distribution of these radicals provides information about flame structure and lift-off heights that can be directly compared with computational predictions. Measurements and computations are compared over a range of buoyancy and fuel dilution levels. Results indicate that the lift-off heights and flame shapes predicted by the computations are in excellent agreement with measurement for both normal gravity (1g) and reduced gravity flames at low dilution levels. As the fuel mixture is increasingly diluted, however, the 1g lift-off heights become underpredicted. This trend continues until the computations predict stable flames at highly dilute fuel mixtures beyond the 1g experimental blow-off limit. To better understand this behavior, an analysis was performed, which indicates that the lift-off height is sensitive to the laminar flame speed of the corresponding premixed mixture at the flame edge. By varying the rates of two key “flame speed” controlling reactions, we were able to modify the predicted lift-off heights so as to be in closer agreement with the experiments. The results indicate that reaction sets that work well in low dilution systems may need to be modified to accommodate high dilution flames.     

Stabilization, propagation and instability of tribrachial triple flames

A tribrachial (or triple) flame is one kind of edge flame that can be encountered in nonpremixed mixing layers, consisting of a lean and a rich premixed flame wing together with a trailing diffusion flame all extending from a single point. The flame could play an important role on the characteristics of various flame behaviors including lifted flames in jets, flame propagation in two-dimensional mixing layers, and autoignition fronts. The structure of tribrachial flame suggests that the edge is located along the stoichiometric contour in a mixing layer due to the coexistence of all three different types of flames. Since the edge has a premixed nature, it has unique propagation characteristics. In this review, the propagation speed of tribrachial flames will be discussed for flames propagating in mixing layers, including the effects of concentration gradient, velocity gradient, and burnt gas expansion. Based on the tribrachial edge structure observed experimentally in laminar lifted flames in jets, the flame stabilization characteristics including liftoff height, reattachment, and blowout behaviors and their buoyancy-induced instability will be explained. Various effects on liftoff heights in both free and coflow jets including jet velocity, the Schmidt number of fuel, nozzle diameter, partial premixing of air to fuel, and inert dilution to fuel are discussed. Implications of edge flames in the modeling of turbulent nonpremixed flames and the stabilization of turbulent lifted flames in jets are covered.