惰性多孔介质内天然气预混燃烧的数学模拟评述

天然气在惰性多孔介质内的预混燃烧是一个包含燃烧、辐射、对流及导热的复杂过程，从数学模拟的角度，比较了几种不同的甲烷-空气化学反应模型，研究了多孔介质内辐射传递方程的不同求解方法，并且分析了多孔介质的导热系数、对流换热系数等对燃烧器性能的影响。     

微细直管内甲烷燃烧的数值模拟研究

采用计算流体力学方法对二维微细直管内甲烷和空气的预混燃烧进行了数值模拟,研究了燃烧器尺寸、壁面导热系数、对流换热系数、壁面厚度以及粗糙度对于燃烧的影响。模拟结果显示,燃烧器内径的变化、壁面导热系数、对流换热系数和壁面厚度的变化影响了热量在壁面内的传递和流体内径向温度的传递,使得燃料点燃和燃烧稳定性受到影响,甚至导致燃烧停止。壁面粗糙度增加了燃烧器内流体的扰动,增强了流体与壁面和流体内的换热,导致燃烧稳定性受到影响。模拟结果为设计和开发高效稳定的燃烧器提供了参考。     

H2／空气预混燃烧模拟计算和散热的研究

采用20步反应机理模拟了H2/空气在内径2 mm长20 mm的圆管内的预混燃烧.H2/空气预混火焰由壁面向中心传播,呈圆锥形.随着气流向后流动,燃烧区域截面温度曲线由"U"形变为"M"形,后又变为倒"U"形,分别对应壁面加热预混气体的过程,预混燃烧火焰由近壁面向中心传播的过程和燃烧后气体对外散热过程.微燃烧器对外散热量较大,约占总输入热的10%左右,其中燃烧段散热约占5%.辐射散热在壁面散热中占主导地位,占总散热的80%～90%,外壁低辐射系数的材料有利于减少散热和增加燃烧稳定性.对微燃烧而言,燃烧器壁厚增加使燃烧器散热增加,反而不利于降低燃烧器散热.燃烧器入口处壁温与壁面导热系数、壁厚不呈单调变化趋势.在导热系数为3～20 W/(m·K)、壁厚为1 mm左右时,燃烧器入口处壁温较高,有利于稳定燃烧.     

多孔介质特性参数对燃烧温度及压力影响的数值模拟研究

考查了两段式多孔介质内预混气燃烧的温度与压力分布情况。建立了甲烷／空气预混气体在多孔介质内燃烧的二维数学模型,运用FLUENT软件求解瞬态控制方程的方法计算出燃烧稳定后多孔介质内的温度、与压力分布,并考查了不同当量比、多孔介质辐射衰减系数和导热系数对温度和压力分布的影响。结果表明,甲烷／空气预混气体在多孔介质中燃烧,当量比越大温度峰值越高,压力梯度越大;小孔介质辐射衰减系数的改变对温度分布和压力分布没有明显的影响,而大孔介质辐射衰减系数对温度分布和压力分布有较大的影响;增加多孔介质的导热系数,会使固相与气相温度均有所升高,燃烧区域压力降低。     

多孔介质回热微燃烧器预混燃烧特性研究

设计了多孔介质回热徽燃烧器,对微燃烧器内H2/Ak的预混燃烧特性进行了实验研究和数值模拟,实验结果表明,当过量空气系数1.0＜α＜3.0时,微燃烧器具有较高的燃烧效率,出口烟气温度和较低的燃烧热损失率,且燃烧热功率P越高,α越大,热损失率越小.当P=100 W时,其出口烟气温度最高可达到1 232 K,当α=3.0时,燃烧效率仍达到96.85％,而热损失率仅为14.87％.数值模拟结果表明,由于采用了回热夹层和多孔介质回热结构,有效地回收了热量损失,使得微燃烧器具有良好的热性能.证明设计的多孔介质回热微燃烧器是一种燃烧效率高、热损失率低的微燃烧器.     

甲烷在过量焓燃烧器内的燃烧特性

设计了一个通道截面为7 mm x0.6 mm的等速螺线过量焓微燃烧器,并在其中完成了CH4/空气预混气的燃烧实验.通过数据采集系统得到了微燃烧器端面的温度分布,使用气相色谱法分析了烟气成分.实验结果表明,过量焓燃烧器能够通过逆流换热有效地实现热量回收,提高可燃预混气进入燃烧区前的温度,有利于微尺度火焰的稳定,并在较宽的空气过量系数范围内实现甲烷/空气预混气在燃烧器的中心稳定燃烧.当空气过量系数大于1时,甲烷可以实现完全燃烧;当空气过量系数小于1时,烟气中存在H2和CO,但无残留的甲烷.     

多孔介质微小燃烧器的传热特性分析

采用计算流体力学软件Fluent,对H_2/空气预混气在全填充多孔介质平板微燃烧器内的燃烧过程进行数值模拟.研究了多孔介质导热系数、壁面导热系数、当量比、孔隙率对微燃烧器回热循环的影响规律.模拟结果表明:预热区对流回热效率、多孔介质导热效率与多孔介质导热系数呈正相关趋势;壁面导热系数增大会使预热区对流回热效率下降,壁面对流回热效率上升;预热区对流回热效率、壁面对流回热效率与当量比呈负相关趋势;多孔介质孔隙率是影响回热效率的重要因素,随着孔隙率的增大,预热区对流回热效率下降,壁面对流回热效率上升.     

预混燃烧数值模拟与结构改进

对煤气-空气预混燃烧进行了数值模拟,通过模拟研究了燃烧器的结构对煤气-空气预混效果的影响,优化了燃烧器的结构,使煤气-空气预混效果达到最佳。模拟结果与实际燃烧过程情况相符。     

多孔介质的热物性对往复流动下超绝热火焰的影响

多孔介质燃烧室的传热性能主要取决于多孔介质材料的热物性,本文在气固两相局部非热平衡假设基础上,建立往复式流动下多孔介质超绝热燃烧的二维数学模型,研究了多孔介质的比热、导热系数、衰减系数和体积换热系数等对温度分布和燃烧速率的影响,以期为多孔介质选材和往复流动下多孔介质超绝热燃烧器的优化设计提供理论依据。     

甲烷/空气预混回热循环微多孔燃烧数值分析

在热循环型微燃烧器中充入甲烷/空气预混合气体进行燃烧数值模拟,探究该类型燃烧器在加入多孔介质条件下,对燃烧效率和预混气体预热效应的影响。文中采用数值模拟并使用甲烷/空气二阶反应,对比燃烧器在没有加入泡沫陶瓷多孔介质的条件下,在某次反应过程中对微燃烧器的影响,同时还发现多孔介质可以明显地使燃烧器提高燃烧效率,减小热损失,减少污染尾气,而且能更好地回收反应产生的热量并预热未反应气体。     

超低热值燃气催化燃烧室特性的模拟

对一种新型超低热值燃气催化燃烧室的特性进行了数值模拟研究.这种燃烧室采用蜂窝结构,应用于超低热值燃气轮机系统;超低热值预混气体流过蜂窝状燃烧器的每一个微细通道,在通道表面发生催化反应.分析了催化燃烧室催化剂负载量、预混气体体积流量、燃烧室入口温度和燃料体积分数等主要因素对催化反应器催化特性的影响.计算表明:催化剂负载量制约整个催化反应的速度;减小体积流量、提高燃料体积分数和提高燃烧室入口温度能够显著提高催化转化效率;为避免反应器温度过高导致催化剂失活,甲烷的浓度和燃气入口温度必须合理控制.     

Swirling distributed combustion for clean energy conversion in gas turbine applications

Distributed combustion provides significant performance improvement of gas turbine combustors. Key features of distributed combustion includes uniform thermal field in the entire combustion chamber, thus avoiding hot-spot regions that promote NO_x emissions (from thermal NO_x) and significantly improved pattern factor. Rapid mixing between the injected fuel and hot oxidizer has been carefully explored for spontaneous ignition of the mixture to achieve distributed combustion reactions. Distributed reactions can be achieved in premixed, partially premixed or non-premixed modes of combustor operation with sufficient entrainment of hot and active species present in the flame and their rapid turbulent mixing with the reactants. Distributed combustion with swirl is investigated here for our quest to explore the beneficial aspects of such flows on clean combustion in simulated gas turbine combustion conditions. The goal is to develop high intensity combustor with ultra low emissions of NO and CO, and much improved pattern factor. Experimental results are reported from a cylindrical geometry combustor with different modes of fuel injection and gas exit stream location in the combustor. In all the configurations, air was injected tangentially to impart swirl to the flow inside the combustor. Ultra-low NO_x emissions were found for both the premixed and non-premixed combustion modes for the geometries investigated here. Swirling flow configuration, wherein the product gas exits axially resulted in characteristics closest to premixed combustion mode. Change in fuel injection location resulted in changing the combustion characteristics from traditional diffusion mode to distributed combustion regime. Results showed very low levels of NO (∼3 PPM) and CO (∼70 PPM) emissions even at rather high equivalence ratio of 0.7 at a high heat release intensity of 36 MW/m³-atm with non-premixed mode of combustion. Results are also reported on lean stability limit and OH^* chemiluminescence under both premixed and non-premixed conditions for determining the extent of distribution combustion conditions.     

Investigation on hydrogen-fueled combustion characteristics and thermal performance in a micro heat-recirculation combustor inserted with block

Numerical investigation on the premixed H₂/air combustion in a micro heat-recirculation combustor inserted with/without block is conducted. Effects of block setting, heat-recirculation, and flow rate on combustion characteristics and thermal performance are depicted and analyzed. The results demonstrate that the block enhances the flame stability and preheating effect, which also reduces the heat loss via exhaust gas, while it shortens reactants residence time. The combustor setting with a transverse block gains a better thermal performance than that inserted with a longitudinal block. With the increase of transverse block height, the high-temperature zone is broadened and radiation is improved. However, the block with a height of 10 mm separates the fluid field and weakens the effects of heat recirculation, leading to a lower outer wall temperature. Furthermore, the appropriate block insertion method and height contribute to the significant improvement of heat transfer, radiant efficiency and further optimization of micro power generator.     

Development of high intensity CDC combustor for gas turbine engines

Colorless distributed combustion (CDC) has been demonstrated to provide ultra-low emission of NOx and CO, improved pattern factor and reduced combustion noise in high intensity gas turbine combustors. The key feature to achieve CDC is the controlled flow distribution, reduce ignition delay, and high speed injection of air and fuel jets and their controlled mixing to promote distributed reaction zone in the entire combustion volume without any flame stabilizer. Large gas recirculation and high turbulent mixing rates are desirable to achieve distributed reactions thus avoiding hot spot zones in the flame. The high temperature air combustion (HiTAC) technology has been successfully demonstrated in industrial furnaces which inherently possess low heat release intensity. However, gas turbine combustors operate at high heat release intensity and this result in many challenges for combustor design, which include lower residence time, high flow velocity and difficulty to contain the flame within a given volume. The focus here is on colorless distributed combustion for stationary gas turbine applications. In the first part of investigation effect of fuel injection diameter and air injection diameter is investigated in detail to elucidate the effect fuel/air mixing and gas recirculation on characteristics of CDC at relatively lower heat release intensity of 5 MW/m³ atm. Based on favorable conditions at lower heat release intensity the effect of confinement size (reduction in combustor volume at same heat load) is investigated to examine heat release intensity up to 40 MW/m³ atm. Three confinement sizes with same length and different diameters resulting in heat release intensity of 20 MW/m³ atm, 30 MW/m³ atm and 40 MW/m³ atm have been investigated. Both non-premixed and premixed modes were examined for the range of heat release intensities. The heat load for the combustor was 25 kW with methane fuel. The air and fuel injection temperature was at normal 300 K. The combustor was operated at 1 atm pressure. The results were evaluated for flow field, fuel/air mixing and gas recirculation from numerical simulations and global flame images, and emissions of NO, CO from experiments. It was observed that the larger air injection diameter resulted in significantly higher levels of NO and CO whereas increase in fuel injection diameter had minimal effect on the NO and resulted in small increase of CO emissions. Increase in heat release intensity had minimal effect on NO emissions, however it resulted in significantly higher CO emissions. The premixed combustion mode resulted in ultra-low NO levels (<1 ppm) and NO emission as low as 5 ppm was obtained with the non-premixed flame mode.     

多孔介质回热微燃烧器的扩散燃烧

设计了多孔介质回热微燃烧器.进行了微燃烧器的扩散燃烧特性实验研究,得到了其燃烧效率、出口尾气温度、壁面温度和热损失率随燃烧热功率和过量空气系数的变化规律.实验发现,在较宽的操作范围内,微燃烧器具有较高的燃烧效率和出口尾气温度,而且随着燃烧功率和过量空气系数的增大,微燃烧器的壁面温度和热损失率反而减小.分析表明,采用回热夹层和多孔介质相向的进气方式,使得反应气体的流动方向与散热方向相反,有效回收了热量损失,提高了微燃烧器的热效率和出口尾气温度.所设计的多孔介质回热微燃烧器对开发微燃烧透平发电系统具有重要应用价值.     

多孔介质往复流动燃烧的一维数值模拟

建立了往复流动多孔介质燃烧器的一维数学模型：在该系统中,可燃预混气周期性换向,分别从两端流入燃烧器。假定气相与固相处于局部热平衡状态,考虑了辐射换热的影响。采用有限容积法求解,通过大量数值计算研究了主要工况参数,如半周期、流速、当量比、热损失、多孔介质衰减系数及其热容对该燃烧系统温度分布和反应特性的影响。计算结果与实验结果在定性上吻合良好。     

预混气体在多孔介质中往复式超绝热燃烧的数值研究

根据气、固两相局部非热平衡假设,建立了RSCP系统的二维非稳态数学模型,对于固体能量方程中的辐射源项采用辐射传递的有限体积法求解,研究了当量比、换向半周期、混合气流速对温度分布、辐射热流量和放热率的影响,考察了最高温升和可燃极限与这些参数之间的关联．研究表明,燃烧室内温度呈梯形分布,高温区较宽;气体的最高温度明显高于绝热火焰温度;贫可燃极限显著扩展,对提高燃烧效率和节约能源有重要作用。     

Distributed swirl combustion for gas turbine application

Colorless distributed combustion (CDC) has been shown to provide significant improvement in gas turbine combustor performance. Colorless distributed combustion with swirl is investigated here to develop ultra-low emissions of NO and CO, and significantly improved pattern factor. Experimental investigations have been performed using a cylindrical geometry combustor with swirling air injection and axial hot gas exit stream from the combustor. Air was injected tangentially to impart swirl to the flow inside the combustor. The results obtained from the combustor have demonstrated very low levels of NO (∼3 PPM) and CO (∼70 PPM) emissions at an equivalence ratio of 0.7 and a high heat release intensity of 36 MW/m³-atm under non-premixed combustion. To further simulate gas turbine operating conditions, inlet air to the combustor was preheated to 600 K temperature and the combustor operated at 2 atm pressure. Results showed very low levels of CO (∼10 PPM) but the NO increased somewhat to ∼10 PPM at an equivalence ratio of 0.5 and heat release intensity of 22.5 MW/m³-atm under non-premixed combustion conditions. For premixed combustion, the combustor demonstrated low levels of both NO (5 PPM) and CO (8 PPM) at an equivalence ratio of 0.6 and a heat release intensity of 27 MW/m³-atm. Results are reported at different equivalence ratios on the emission of NO and CO, lean stability limit and OH^* chemiluminescence. These results suggest that further performance improvement can be achieved with improved fuel mixture preparation prior to the ignition of fuel at higher operational pressures using swirling combustor design for our quest to develop ultra low emission high intensity combustor for gas turbine application.     

天然气塔式同轴分级燃烧室掺氢燃烧特性 数值模拟研究

为了解天然气掺氢对贫预混燃气轮机性能的影响,采用Chemkm-pro研究了燃料的化学反应动力学 特性,对比了不同当量比、掺氢比下的绝热火焰温度、层流火焰传播速度及点火延迟时间,结果表明掺氢能缩 短燃料点火延迟时间,增加绝热火焰温度及提高火焰传播速度。进一步以天然气塔式同轴分级燃烧室为研 究对象,研究了掺氢比对燃烧室燃烧场分布及燃烧效率、总压损失系数、温度分布不均匀度、一氧化碳及氮氧 化物排放量等性能参数的影响。结果表明,随着掺氢比的增加,燃烧效率上升,总压损失系数增加,温度分布 不均匀度下降,一氧化碳排放量下降,氮氧化物排放量增加。掺氢比在35%时燃烧室发生回火。在30% ~ 35%掺氢比范围内,燃烧室性能参数变化较大。其中,总压损失系数增幅为24. 74%,温度分布不均匀度降幅 为31.11%,氮氧化物排放量增幅为416.12%。