高温空气低燃气浓度燃烧过程的数值模拟研究

从工程实际出发,本文提出了高温空气低燃气浓度燃烧新技术,即充分利用烟气余热提高助燃空气温度,提高热能利用率;同时通过优化喷口结构,提高燃气射流速度,使燃气射流在同空气射流混合燃烧前卷吸大量炉内烟气,从而降低燃气射流中的可燃物浓度,进而降低氮氧化物的排放。通过数值模拟研究表明,通过燃气射流速度从24.56m/s提高到55.26m/s,可以降低NOx的排放;当围绕燃气喷口的六个圆形空气喷口改为两个矩形喷口时,燃气射流可从两侧卷吸更多的炉内烟气,形成低燃气浓度燃烧,从而大大降低了NOx的排放。     

多孔介质燃烧-换热器NOx排放的二维数值研究

通过二维单温模型,考虑甲烷燃烧的详细化学反应机理,数值研究多孔介质燃烧-换热器内的燃烧、传热和NO排放规律.研究主要工作参数过量空气系数和燃烧器功率对氮氧化物排放的影响.结果表明,过量空气系数和功率对NO排放有显著的影响.功率一定时,过量空气系数由1.12增大到1.42时,NO体积分数由3.9E-5减少到1.8E-5....     

2955t/h超超临界塔式炉炉膛传热与燃烧的数值模拟

通过数值模拟对2955 t/h超超临界塔式炉炉膛内燃烧过程进行研究,给出了炉内流场、温度场的分布规律以及NOx排放的影响规律.结果表明,采用同心切圆燃烧方式、CCOFA风和SOFA风对燃烧区域过量空气系数的多级控制,实现了炉膛出口烟温偏差小、NOx的排放量低的要求,数值模拟与试验数据相比,两者基本吻合.     

煤粉高温空气燃烧与氮氧化物生成特性

借助循环流化床在高过剩空气系数下燃烧提供高温低氧空气的工艺,在直径为220 mm高为3000 mm的实验台上研究褐煤、烟煤和无烟煤在高温低氧空气下的燃烧特性和氮氧化物生成特性.实验结果表明,褐煤、烟煤和无烟煤在高温低氧空气下燃烧稳定性好,温度波动小;高温低氧的气氛降低了褐煤、烟煤、尤其是无烟煤燃烧的氮氧化物排放;褐煤、烟煤和无烟煤燃烧的氮氧化物排放值分别为440 mg/m3,390 mg/m3和332 mg/m3.     

内部烟气再循环式小型天然气炉内NOx排放的研究

本文采用实验和数值模拟方法对内部烟气再循环式小型天然气炉内氮氧化物的排放进行了研究.探讨了炉膛中加装的一种中心圆筒结构对炉内烟气再循环流动及NOx排放的影响.研究结果表明,中心圆筒的存在可以使氮氧化物的排放有所降低.与不加装中心圆筒的工况相比,加装中心圆筒后炉内NOx的排放随过晕空气系数的变化较弱.炉内加装中心圆筒后,烟道入口处的温度降低,这表明中心圆筒的存在强化了炉壁的散热,从而降低了排烟温度.     

底排装置非定常环状伴随射流的特性分析

为了研究环形喷口底排弹出膛口时的尾部二次燃烧特性和环状伴随射流流动特性,针对底排燃烧室在瞬态泄压条件下的强非稳态扰动过程,建立了环状喷口射流与超声速来流相互作用的二维轴对称化学非平衡流模型,数值研究环形喷口底排装置的非定常伴随射流燃烧流动演化特性。计算结果表明:环形喷口射流在泄压初期挤压形成高度欠膨胀的中心射流,随着喷口压力降低,逐渐转变为亚音速环状射流。泄压中期,燃烧反应强度由射流边缘向中心轴线方向逐渐加剧,在气体回流作用下,尾部流场温度快速升高。在泄压过程中,不同初始压力下的底部压力和轴线温度变化趋于一致。随着燃烧室内初始压力增大,底压系数峰值增加,降压时间延长。1.5 ms后,初始压力对尾部流场无明显影响。     

300MW四角切圆锅炉燃尽风布置方式对低氮燃烧特性的影响

根据对象锅炉结构特性和煤质特性提出了三种燃尽风布置方式,并对燃尽风风率对不同布置方式下炉内燃烧和NO_x排放的过程进行了数值模拟分析。研究表明,燃尽风率为30%左右时,三种布置方式下锅炉各参数都表现出合理的水平,并且能够满足NO_x排放要求。两段送风的深度空气分级方式在煤粉的燃烧和燃尽,降低NO_x的排放量方面效果较好,更为适合四角切圆锅炉的低氮燃烧改造。     

预热温度影响甲烷高温空气燃烧特性的数值分析

为了深入认识近年发展起来的一种新型燃烧技术－高温空气燃烧的机理和超低氮氧化物排放特性,本文将扩散燃烧模型、热力ＮＯ生成模拟与完全湍流Ｎ－Ｓ方程相结合,数值研究了甲烷高温燃烧的火焰特性、空气预热温度对燃烧特性和ＮＯ排放浓度的影响规律。研究结果与实验数据符合良好,为在我国发展这项技术提供了依据。     

城市干化污泥循环流化床燃烧过程中NO和N2O的排放特性

在15 kW循环流化床实验台上进行了城市干化污泥的燃烧实验,研究了污泥含水率、燃烧温度、过量空气系数、二次风比率等因素对NO和N₂O排放特性的影响。实验结果表明:污泥含水率从4.5%增加至17.5%时,NO排放浓度明显降低,N₂O排放浓度明显升高;燃烧温度升高,NO排放浓度呈上升趋势,N₂O排放浓度则呈下降趋势;增大过量空气系数会促进NO和N₂O的生成;提高二次风比率可以降低NO和N₂O的排放浓度。城市干化污泥在循环流化床燃烧过程中NO和N₂O的排放浓度高于污泥与煤混烧时的排放浓度,但燃料N向NO和N₂O的转化率低于与煤混烧过程。     

空气/天然气λ对QHCCI燃烧过程影响的研究

本文采用天然气气口顺序喷射、柴油引燃方式实现了基于天然气的准均质压燃着火燃烧过程（ＱＨＣＣＩ），本文研 究了气口喷射天然气／空气过量空气系数（λ）ＱＨＣＣＩ对燃烧过程的影响，分析了各种排放产物及燃油经济性同过量空气 系数（λ）、停缸数和引燃柴油量的关系。通过燃烧优化，发动机ＮＯｘ、颗粒和ＮＭＨＣ排放均达到了欧Ⅱ排放指标。     

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.     

Characteristics and structure of inverse flames of natural gas

Characteristics and structure of nominally non-premixed flames of natural gas are investigated using a burner that employs simultaneously two distinct features: fuel and oxidiser direct injection, and inverse fuel and oxidiser delivery. At low exit velocities, the result is an inverse diffusion flame that has been noted in the past for its low NO_x emissions, soot luminosity, and narrow stability limits. The present study aimed at extending the burner operating range, and it demonstrated that the inverse flame exhibits a varying degree of partial premixing dependent on the discharge nozzle conditions and the ratio of inner air jet and outer fuel jet velocities. These two variables affect the flame length, temperature distributions, and stability limits. Temperature measurements and Schlieren visualisation show areas of enhanced turbulent mixing in the shear region and the presence of a well-mixed reaction zone on the flame centreline. This reaction zone is enveloped by an outer diffusion flame, yielding a unique double-flame structure. As the fuel–air equivalence ratio is decreasing with an increase in the inner jet velocity, the well-mixed reaction zone extends considerably. These findings suggest a method for establishing a flame of uniform high temperature by optimising the coaxial nozzle geometry and flow conditions. The normalised flame length is decreasing exponentially with the air/fuel velocity ratio. Measurements demonstrate that the inverse flame stability limits change qualitatively with varying degree of partial premixing. At the low premixing level, the flame blow-out is a function of the inner and outer jet velocities and the nozzle conditions. The flame blow-out at high degree of partial premixing occurs abruptly at a single value of the inner air jet velocity, regardless of the fuel jet velocity and almost independent of the discharge nozzle conditions.     

Effect of fuel injection location on a plasma jet assisted combustion with a backward-facing step

Non-reacting and reacting experiments on the ignition by a plasma jet (PJ) torch were performed to understand the correlation between fuel injection location and combustion characteristics in unheated Mach 2 airflow. Fuel was injected through three sonic injectors in the recirculation region behind a backward-facing step: a parallel injector at 2 mm from the bottom wall and two normal injectors at 2 and 9 mm from the step wall. In order to mitigate the combustion pressure interaction with nozzle, an isolator was installed between the nozzle and combustor. The combustion performance of normal injection was little affected by the difference of fuel injection locations. Moreover, normally injected fuel was escaped not to be held in the recirculation region despite of low fuel injection rates. This led to lower combustion performance relative to the parallel injection which provided fuel not to leave the recirculation region. In this case, the role of the recirculation region was to fully hold fuel, and the PJ torch provided hot gases as a heat source and acted as a flame-holder to ignite fuel–air mixtures. In a low temperature inflow condition, combustible regions were constrained around the bottom wall where embedded with the PJ torch. When thermal choking occurred in the combustor, it induced shock train both in the combustor and isolator. Under this unstable condition, the combustion performance of the normal injection was lower than that of the parallel injection. This is because the normal injection led most fuel into low temperature incoming air-stream.     

燃气轮机合成气燃烧室中燃烧噪声的现场测试与分析

燃气轮机的燃烧噪声是反映燃烧室燃烧稳定性的主要参数.本文对国内某座煤基IGCC示范电站的40 MW级燃气轮机在诸多运行条件下的燃烧噪声进行了现场测试,分析了气液双燃料喷嘴在燃烧轻柴油、燃烧合成气以及油气切换过程中燃烧室的燃烧噪声,另外分析了合成气掺烧驰放气与合成气加湿对燃烧稳定性的影响.结果表明:合成气燃烧室在油气切换过程中燃烧噪声会增加,但距离振荡燃烧的阈值仍有很大的裕度;烧合成气时随着燃气轮机功率增加燃烧噪声降低;合成气加湿时随着蒸汽流量增加污染物NOx排放显著降低,并且燃烧噪声也有降低的趋势.     

造纸污泥流化床焚烧试验研究

在一座密相床截面积为 ０．２３ ｍ×０．２３ｍ、高度为 ５ｍ的流化床燃烧试验装置上进行了造纸污泥的焚烧试验．探明污泥水分、流化速度、二次风份额和过剩空气系数等参数对污泥燃烧性能的影响规律,为高水分造纸污泥焚烧炉的优化设计提供了依据．测试表明,在不添加脱硫剂情况下焚烧烟气中ＳＯ２、ＮＯｘ和Ｎ２Ｏ的排放浓度完全满足国家排放标准．     

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。     

DMM燃料柴油机可控预混合燃烧的研究

本文介绍了在压燃式发动机上进行的预混合燃烧研究。在柴油机的进气道入口处安装了一个电控燃料喷射系统,喷入具有低十六烷值、低沸点的甲缩醛(DMM)燃料,在压缩冲程中形成均匀的混合气,并在上止点附近喷入少量柴油来点燃混合气。本文研究了预混合燃料比、发动机负荷、进气中CO2浓度和喷孔直径对发动机燃烧和排放的影响。试验结果表明,进气道喷射DMM的预混合燃烧能同时大幅降低NOx和碳烟排放,为降低柴油机有害排放提供了一种新途径。     

Gas jet as a waveguide for air-coupled ultrasound

The directional characteristics of an ultrasonic signal have been studied during propagation within an axial gas jet. The effects of nozzle shape, nozzle diameter, and variations in jet velocity, temperature and gas composition have been investigated. At high flow velocities of an air jet, divergence of the ultrasonic beam was observed. This was attributed to the effects of refraction, caused by increased acoustic velocities in the direction of the flow. An effective waveguide was also demonstrated by cooling the air jet to below ambient temperatures, so that the acoustic velocity in the air jet was lower than that in the surrounding atmosphere. This could also be achieved by using carbon dioxide mixed with air, whereas the use of helium led to increased divergence. The result is likely to be of use in air-coupled ultrasonic materials inspection.     

PSP measurement of flow fields in a supersonic combustor with a backward-facing step

The mixing fields within a SCRAM-jet combustion chamber are visualized using pressuresensitive paint (PSP) as an oxygen sensor. The experiments are performed in a small supersonic wind tunnel at the National Aerospace Laboratory — Kakuda Research Center (NAL-KRC). The main stream Mach number is 2.4, and the dynamic pressure ratios between the injected gas and the main flow are 0.3, 0.7, 1.1 and 1.5. Three fuel injection nozzles are used; oxygen is injected from the central nozzle and air from the two nozzles at either side. The spread of the injected gas is measured to observe the effects of placing the nozzles in different positions. The results show that the jet has its own independent flow structure, and that little mixing of gases occurs between the flow structures created by each nozzle. When the injection dynamic pressure ratio is increased, the oxygen fraction rises in the recirculation zone and falls in the separation zone downstream of the injection.