壁面渗透燃烧微燃烧器结构参数优化实验研究

针对一种圆柱多孔壁面组织渗透燃烧微尺度燃烧器,本文在甲烷/空气不同燃料当量比和混合气流量下,对比实验了关键参数燃烧室内径(d)和燃烧室高度(h)变化对燃烧器性能的影响.结果表明随燃烧室内径减小,吹熄极限速度显著下降,烟气平均温度升高,同时壁面温度下降;燃烧室高度减小,可燃烧极限当量比和淬熄极限速度均增大;在高径比h/d接近1时,烟气平均温度最高,壁面最高温度不变,大流量下壁面温度降低更快.因此,当缩小壁面渗透微燃烧器时,为防止燃烧效率降低和热损失增加,应优先缩小内径并保持高径比接近1.0.     

正丁烷/空气混合气催化点火的实验研究

本文在通道高度分别为2 mm和4 mm的平板微反应器内进行了正丁烷/空气混合气的催化燃烧实验。结果表明,在入口流速以及燃烧室高度相同的情况下,催化起燃温度随当量比的增加而下降,且稳定燃烧时最大放热量出现在混合气当量比略大于1时。实验中并未发现明显的气相着火现象。在入口流速以及当量比相同的条件下,混合气在通道高度4 mm的反应器内的起燃温度低于2 mm反应器,表明气相扩散对催化起燃可能产生了一定的影响。     

超低热值多孔介质燃烧器功率范围试验

本文对积木式结构多孔介质燃烧器稳定燃烧超低热值燃气的功率范围进行了试验研究。用甲烷和氮气配制了试验燃气的热值为1.4~3.0 MJ/m~3,在理论当量比条件下组织了预混燃烧。通过改变甲烷的流量,测试了不同燃烧强度工况下燃烧室壁面的温度分布,进而判定了各工况条件下燃烧室内是否能保持稳定燃烧。结果表明,本文所设计的燃烧器对于超低热值气体有着良好的适应性,对于热值高于1.4 MJ/m~3的气体都有一个稳定燃烧的功率区间,且稳定燃烧的功率范围随着气体热值的增大而增大。在预热温度为1200 K的前提下,燃气热值为1.4 MJ/m~3时,稳定燃烧的燃烧强度范围为30.57~107.01 kW/m~2,而当气体热值为3.0 MJ/m~3时,燃烧极限的近似范围是107.01~229.30 kW/m~2。     

微型摆式发动机内丙烷/空气单次燃烧实验研究

在厘米尺度百瓦级微型摆动式发动机样机上进行了单次燃烧实验,燃用当量比φ=0.9~1.2的丙烷/空气预混合气时,对燃烧室内的火焰传播形态、气体动态压力和摆臂运动进行测量,获得了平均火焰传播速度、燃烧持续时间、燃料质量燃尽率、压力和摆臂止点角度随当量比变化的规律特性。结果表明:在进气初始温度300 K、压力0.13 MPa条件下,φ=1.0~1.2工况时,微摆发动机内燃烧为湍流燃烧,燃烧持续时间在5 ms以内,压力峰值高于8个大气压;随当量比增加,燃烧持续时间缩短、平均火焰传播速度加快和压力峰值升高,更接近定容燃烧,有利于提高输出功率。     

微通道粗糙度对甲烷催化燃烧影响的数值研究

采用详细化学反应机理对甲烷空气预混气体在不同粗糙度下微通道内催化燃烧进行了数值模拟。结果表明:粗糙度的存在使得微通道内甲烷转化率减小,出口温度降低,粗糙表面将阻碍催化反应的进行,而且粗糙度越大这种阻碍作用越大;在同一粗糙度下,随着当量比、混合气入口速度的增加,粗糙度对催化反应的阻碍作用越明显,粗糙度越大,燃烧效率越低。     

微尺度预混合火焰结构和熄火特性研究

本文以空气中的无约束甲烷预混合火焰为对象,用实验和数值解析的方法研究了微尺度预混合火焰的火焰结构和熄火特性。实验测得不同尺寸下混合气当量比和喷出速度与熄火关系图,在不到理论当量比(φ>1)时,火焰已经熄灭,管径越小,极限混合气当量比φu越大。数值解析研究了d=0．3 mm无约束甲烷预混合火焰,在混合气当量比大于 1的富燃料燃烧条件下,空气中形成的预混合火焰结构是内层预混合火焰和外层扩散火焰,极限当量比约为1,解析结果再现了实验现象。     

甲烷微尺度催化燃烧的数值模拟

本文联合使用计算流体力学软件FLUENT和可以计算表面反应的化学反应动力学软件DETCHEM对有逆流换热的微尺度燃烧器进行了数值计算。计算中忽略空间反应。燃料-空气混合物的当量比为0.4,反应器壁面采用等温边界条件。计算结果表明,采用催化燃烧可以实现微尺度下通常情况下无法实现的甲烷稳定燃烧。通过适当设置催化表面,可以实现燃料低温、高效转变。甲烷的总转变率受流动状态、反应温度和催化表面的大小等因素的影响。     

斜喷环流环形燃烧室点火实验研究

本文发展了一种通过旋流喷嘴斜切喷入可燃气体,在燃烧室内形成周向环流以增强掺混的环形燃烧室模型,并开展点火实验研究,使用高速相机记录点火过程中的周向联焰,在不同点火模式下,与传统直喷型环形燃烧室的火焰传播特征进行对比,分析了当量比、空气流量和热功率对周向点火时间的影响。实验发现,斜喷环流的周向速度分量对周向火焰传播过程有重要影响;当空气流量达到一定程度时,影响周向点火时间的流动加速系数主要由空气流量决定。     

基于多孔介质燃烧的小型推进器实验研究

多孔介质具有良好的蓄热、传热性能,多孔介质燃烧可以有效地降低系统的热损失,提高尺度燃烧的稳定性.本文在一个内径2 am、长2 cm的圆柱形腔体里组织多孔介质燃烧,测量了点火和稳定燃烧的当量比范围,腔体和出口温度等参数;将燃烧室与小喷管结构相结合,获得了稳定的微推力.     

较高当量比氢气空气预混合气的燃烧特性研究

利用纹影法,在定容燃烧弹中研究了较高当量比和不同初始压力下氢气空气预混合气的燃烧特性,分析了两参数对其燃烧特性的影响。试验结果表明,本实验条件下的氢气空气预混合物燃烧过程中,主火焰两侧出现挤流火焰,且挤流火焰的传播明显快于主火焰;根据出现挤流火焰与否、两侧挤流火焰相遇与否、实验时的热力参数、燃料浓度等条件,燃烧过程可分为四个阶段;在本文的实验条件下随着当量比增加,挤流火焰燃烧速度加快,其倾向于自燃时的多点燃烧;随着初始压力降低,挤流火焰逐渐出现在主火焰层流燃烧阶段。     

微型火焰管中燃烧的研究

提出了一种新型的微动力机电系统观念,即微型热光电 TPV(thermo photovoltaic)系统。微型燃烧室是微型TPV系统中最重要的部分之一。为了获得较高的能量转换效率,需要使燃烧器壁面四周处于较高且分布均匀的温度状态。尺寸效应对微型燃烧室中的持续燃烧带来了很大的影响。为了分析微型燃烧器中燃烧的可行性和有关影响因素,在不同工况下进行实验。结果表明,在一定的流量和混合比范围内,可以在微型火焰管内维持稳定的燃烧,高温能够在燃烧室四周均匀分布。     

进气温度对微燃机燃烧室燃烧特性的影响分析

本文通过实验研究了在保持微型燃气轮机燃烧室出口排气温度不变的情况下,改变进口空气温度对燃烧室燃烧特性的影响.结果表明,随着燃烧室进气温度的增大,燃烧效率提高,燃烧室出口温度不均匀性系数减小,热阻增大,总压恢复系数有所降低.同时,实验结果还表明,随着燃烧室进口空气温度的增大,燃烧室出口处CO及未燃烬碳(UHC)排放浓度显著降低,但NO排放浓度则增大.根据实验结果,本文还分析了进气温度的改变对燃烧室燃烧特性的影响规律,为今后微型燃气轮机燃烧室的研制及改进提供了参考依据.     

Towards the development of an efficient low-NOx ammonia combustor for a micro gas turbine

Recent studies have demonstrated stable generation of power from pure ammonia combustion in a micro gas turbine (MGT) with a high combustion efficiency, thus overcoming some of the challenges that discouraged such applications of ammonia in the past. However, achievement of low NOx emission from ammonia combustors remains an important challenge. In this study, combustion techniques and combustor design for efficient combustion and low NOx emission from an ammonia MGT swirl combustor are proposed. The effects of fuel injection angle, combustor inlet temperature, equivalence ratio, and ambient pressure on flame stabilization and emissions were investigated in a laboratory high pressure combustion chamber. An FTIR gas analyser was employed in analysing the exhaust gases. Numerical modeling using OpenFOAM was done to better understand the dependence of NO emissions on the equivalence ratio. The result show that inclined fuel injection as opposed to vertical injection along the combustor central axis resulted to improved flame stability, and lower NH₃ and NOx emissions. Numerical and experimental results showed that a control of the equivalence ratio upstream of the combustor is critical for low NOx emission in a rich-lean ammonia combustor. NO emission had a minimum value at an upstream equivalence ratio of 1.10 in the experiments. Furthermore, NO emission was found to decrease with ambient pressure, especially for premixed combustion. For the rich-lean combustion strategy employed in this study, lower NOx emission was recorded in premixed combustion than in non-premixed combustion indicating the importance of mixture uniformity for low NOx emission from ammonia combustion. A prototype liner developed to enhance the control and uniformity of the equivalence ratio upstream of the combustor further improved ammonia combustion. With the proposed liner design, NOx emission of 42?ppmv and ammonia combustion efficiency of 99.5% were achieved at 0.3?MPa for fuel input power of 31.44?kW.     

H2/n-C4H10/Air预混气在Swiss-Roll燃烧器中的催化燃烧特性

在微尺度催化燃烧中,由于燃料和氧气对于催化剂表面活性位的竞争,导致了可燃下限为富燃的情况。为了提高燃料利用率,拓宽可燃范围,本文在正丁烷/空气的混合气中加入一定量的氢气,在Swiss-roll燃烧器内研究了氢气/正丁烷/空气预混气的燃烧特性。结果表明,氢气能够有效拓宽正丁烷的可燃范围,可燃下限能够低于1,以贫燃的条件实现高燃料利用率。对于稳定燃烧温度的实验结果表明,燃烧器最高温度出现在富燃料一侧。     

Combustion characteristics in a small-scale reactor with catalyst segmentation and cavities

Hydrogen–air combustion characteristics of a small-scale reactor with different catalyst layouts and configurations are experimentally and numerically investigated. Four different platinum catalyst layouts are used to investigate the effect of catalyst segmentation on combustion performance. It is found that combustion phenomena are strongly related to the variations of inflow velocity, equivalence ratio, and length of catalyst segment. The existence of hetero- and homogeneous reactions in the combustor relies on sufficient catalytically induced exothermicity as well as sufficient hydrogen in the remaining mixture. Besides, the multi-segment catalyst with cavities appreciably extends the stable operating range of catalytic combustion in a small-scale combustor for a wide range of inflow velocities. Nevertheless, gas-phase reaction can be sustained and anchored by the existence of cavity in a small-scale system. The reactor with proposed mechanisms can be applied to various small-scale power, heat generation, and propulsion systems.     

微型燃烧器预混腔内催化重整、积碳及流动特性模拟

因微型燃烧器内微尺度燃烧易熄火,燃烧效率不高,存在催化重整过程中的积碳、微尺度等问题,可利用甲烷和湿空气中水蒸汽预混催化重整产氢来强化燃烧,对预混腔内催化重整,积碳及流动特性进行模拟,探讨了微型预混腔中甲烷、水蒸汽重整过程中水碳比、质量流量和催化壁面温度对催化重整、积碳、流动等的影响.     

Concept and combustion characteristics of ultra-micro combustors with premixed flame

Under micro-scale combustion influenced by quenching distance, high heat loss, shortened diffusion characteristic time, and flow laminarization, we clarified the most important issues for the combustor of ultra-micro gas turbines (UMGT), such as high space heating rate, low pressure loss, and premixed combustion. The stability behavior of single flames stabilized on top of micro tubes was examined using premixtures of air with hydrogen, methane, and propane to understand the basic combustion behavior of micro premixed flames. When micro tube inner diameters were smaller than 0.4 mm, all of the fuels exhibited critical equivalence ratios in fuel-rich regions, below which no flame formed, and above which the two stability limits of blow-off and extinction appeared at a certain equivalence ratio. The extinction limit for very fuel-rich premixtures was due to heat loss to the surrounding air and the tube. The extinction limit for more diluted fuel-rich premixtures was due to leakage of unburned fuel under the flame base. This clarification and the results of micro flame analysis led to a flat-flame burning method. For hydrogen, a prototype of a flat-flame ultra-micro combustor with a volume of 0.067 cm³ was made and tested. The flame stability region satisfied the optimum operation region of the UMGT with a 16 W output. The temperatures in the combustion chamber were sufficiently high, and the combustion efficiency achieved was more than 99.2%. For methane, the effects on flame stability of an upper wall in the combustion chamber were examined. The results can be explained by the heat loss and flame stretch.     

燃气轮机燃烧室空气加湿燃烧的实验研究

空气加湿燃烧是HAT循环的关键技术。本文通过中压全尺寸燃气轮机燃烧室空气加湿燃烧实验,研究了加湿度对燃烧特性的影响。实验中发现,燃烧室内温度分布、出口温度场、污染物生成(即NOx、CO、UHC)及燃烧稳定性都受到加湿度的影响。研究结果表明,空气加湿燃烧导致NOx排放显著下降, CO和UHC排放略有上升,燃烧室中压力振荡的频谱产生了变化,燃烧室出口温度场畸变加剧。作者从水蒸气影响燃烧的机理出发对实验结果进行了分析和解释。     

A comparative study of H2-air premixed flame in micro combustors with different physical and boundary conditions

A numerical study of H₂-air premixed combustion in the micro channels with a detailed chemical reaction mechanism is performed by solving the two-dimensional fully elliptic governing equations of continuity, momentum, energy and species, coupled with the energy equation in the solid wall. A reference case is defined as the combustion in a cylindrical tube with 0.8 mm inner diameter and 8 mm length with a non-slip wall and a uniform velocity profile at the inlet plane. Different physical and boundary conditions have been applied in order to investigate their respective effects on the flame temperature. The conditions studied in the current paper include the combustor size and geometry, inlet velocity profile, axial heat conduction in the solid wall and slip-wall and temperature jump at the gas–solid interface. It is noted that effects of Knudsen number (slip-wall and temperature jump) on the thermal and fluid field are not very significant in a d = 0.4 mm micro combustor. Furthermore, the qualitative effects of Knudsen number on the flame temperature are analysed. The results of this paper indicate that these various boundary and physical conditions have effects on the flame temperature to different extent and should be carefully monitored when applied for different applications.     

Numerical investigation of low-frequency instability and frequency shifting in a scramjet combustor

The combustion instability in a laboratory-scale direct-connect hydrogen-fueled scramjet combustor is investigated numerically. The numerical simulation has been carried out using a delayed detached eddy simulation (DDES) with a detailed reaction mechanism. The computational framework has high fidelity by applying multi-dimensional high order accurate schemes for handling convective and viscous fluxes. The field data were accumulated up to 100 milliseconds on each case to capture sufficiently the repetitive behavior of low-frequency instability of order of 100 Hz. The numerical results exhibit the formation/dissipation of pressure and shock wave induced by continuous heat release in the combustor. This motion of pressure/shock wave, so-called upstream-traveling shock wave, presents repeated dynamics between isolator and combustor with a period of several milliseconds. With this periodic hydrodynamic characteristic, the upstream-traveling shock wave interacts with the boundary layer and injected fuel stream affecting fuel/air mixing and burning, and finally inducing the combustion instability in a scramjet combustor. Frequency analysis derived major instability frequencies of 190 Hz and 450 Hz in the isolator and combustor for low and high equivalence ratios, respectively. Current numerical results present the underlying flow physics on the shifting of the instability frequency by changing the equivalence ratio observed by the previous experimental studies. The fact that an instability frequency exists homogeneously from isolator to combustor informs that the combustion instability of scramjet engine is the fully coupled flow/combustion dynamics throughout the engine on a macroscopic scale.