关于直喷喷雾液相温度分布的研究

液体燃料喷雾的蒸发特性对直喷发动机缸内的混合气形成、燃烧过程和有害排放物的形成具有十分重要的影响。在影响液体燃料喷雾蒸发的众多因素中,喷雾气相浓度和液相温度是十分关键的因素。本研究结合双相激光诱导荧光技术和双色法测温技术,对液体燃料直喷喷雾的液相温度分布进行测量研究。研究发现,在一定环境压力条件下,燃料温度对多孔直喷喷雾结构有着显著的影响,且喷雾液相温度分布随喷雾结构的变化而变化。     

单体油珠蒸发过程放大速快速影

对于液体燃料,特别是掺入一定比例水份的乳化液体燃料的蒸发和燃烧的研究,为提高燃烧效率,降低对环境的污染是一个瞩目课题。 由于单体油珠一般在φ2mm以下,不能用一般常规拍摄。本文介绍我们自它研制三种简单的放大4×-5×的装置与热电偶温度记录仪配合成功的拍摄了单体油珠蒸发和燃烧的全过程电影片的拍摄方法。     

多孔介质中液体喷雾燃烧的实验研究

本文通过自行研制的多孔介质燃烧实验系统,研究了液体燃料在热多孔介质中的燃烧可行性及其燃烧特性.燃烧系统包括燃烧室、供气系统、供油系统和测量系统等,该系统分别以气体和液体作为燃料,先通过多孔介质内的预混合燃烧对多孔介质固相进行预热,然后喷入液体燃料,实现燃烧,实验证实了液体燃料在热多孔介质内汽化及自维持燃烧的可行性,并讨论了空气量和喷油量等对燃烧室温度的影响.     

微型降膜燃烧器燃烧试验研究

本文利用水平螺旋槽降膜蒸发机理自行设计了降膜蒸发器,应用在微型燃烧器中,能够实现液体燃料的快速均匀蒸发。在没有动力的情况下实现了液态燃料的气化,而且这种燃烧器燃烧效率高,排放的污染物远低于国家标准,在同类产品中性能领先,对我国微型燃烧器的全新雾化燃烧方式的研究开发具有重要的促进意义。     

雾化燃烧模拟一体化方法及应用研究

如何模拟液体燃料的雾化、掺混及燃烧过程,一直以来都备受关注。本文试图将无网格MPS(moving particlesemi-implicit rnethod)方法与颗粒轨道模型结合起来描述液体燃料从射流、破碎、雾化、输运全过程,并与基于Euler网格气相方程耦合求解,从而可以获得对雾化燃烧全过程模拟的一体化方法。初步结果显示,其方法和技术路线可行。     

乙醇与汽油的喷雾及蒸发特性研究

随着汽车发动机的发展,缸内直喷汽油机(GDI)逐渐成为关注和研究的重点。液体燃料喷雾的结构和蒸发与直喷汽油机内燃烧的稳定性、发动机效率以及尾气排放有着密切联系。本文通过纹影测试技术对乙醇和汽油的直喷喷雾的雾化和蒸发进行测试,研究结果表明环境温度、环境压力和喷射压力对喷雾贯穿距有着显著的影响,而燃油温度在低于燃油沸点时对喷雾贯穿距影响很小。因此可以通过控制环境温度和压力,以及燃油的喷射压力和温度对喷雾贯穿距进行优化.     

基于新型热力循环的柴油机预混合燃烧研究—(1)高压空气射流控制压缩着火模拟分析

为解决内燃机预混合压缩着火相位的控制难题,提出了高压空气射流控制压缩着火相位,实现全工况范围的预混合燃烧的方案。为摸清高压空气射流控制压缩着火过程,本文建立了高压空气射流触发燃烧弹内柴油预混合气着火的CFD模型,分析射流参数对燃烧弹内气流运动、着火及燃烧过程的影响。研究结果表明;高压空气喷入柴油预混合气氛围内,使其局部小范围内温度迅速上升,满足着火条件,实现对柴油预混合气着火时刻的主动控制;燃烧放热分三个阶段,总体呈先低后高的特点,且柴油预混合燃烧速率可控。     

外界辐射对浸没在多孔介质中的液体燃料燃烧特性的影响

本文研究了不同辐射通量下浸没在沙床中的液体燃料的燃烧特性.探讨了辐射通量对液体燃料浸没在多孔沙床中的燃烧特性的影响,获得了不同辐射通量下的火焰特性、床层温度分布、离表面最近测点处蒸气区的下边界到达时间、燃烧持续时间及燃料消耗规律.实验结果揭示了浸没在多孔床中的液体燃料在不同辐射通量下燃烧时的特殊规律.     

逆向复式射流预燃室燃烧器煤粉颗粒行为预报

1引言预燃室燃烧技术是近十多年来开发研究的一种高燃烧效率低NO。的燃烧技术门．它是一种分级燃烧技术。燃料在预燃室内只是部分地燃烧,在贫氧的一次火焰区内脱挥发分,从而减少了NO。的形成。自1982年以来,我国开发研究了很多种类的预燃室,如旋流、大速差l‘］、偏置射流预燃室等。工程热物理研究所研究开发了逆向复式射流预燃室燃烧器l‘,‘］。经实验室和工业实验证明,该预燃室有极优良的火焰稳定性能和煤种适应性,能够实现较低的NOx排放。本文针对逆向射流预燃室内这一独特的流场结构,利用数值模拟来预报煤粉颗粒在其内的运…     

燃料液滴间火焰传播的高速摄影研究

作为雾状燃料燃烧现象的微观模拟,我们研究了燃料液滴在不同条件下的点火机制和火焰传播规律。本文介绍的实验方法,将干涉计量术与高速摄影方法相结合,既克服了大多数液体燃料在燃烧时亮度太低的缺点,又充分发挥了干涉计量术能记录温度场和高速摄影记录高速过程的特长。     

用轻油制备燃料电池燃料的技术研究

简要介绍燃料电池的基本原理及优点并比较不同燃料电池的燃料处理过程及其电极对燃料的要求。通过实验研究,探索了应用预蒸发技术和部分氧化技术处理轻油制备燃料电池燃料的效果。实验结果表明,温度和过量空气系数是影响轻油转改效果的重要因素,提高过量空气系数和升高反应器的温度能够增加转改后气体中氧和一氧化碳的体积份额。     

合成气稀态预混燃烧器设计

稀态预混燃烧技术是实现合成气超低污染物排放利用的一条较为有前景的途径,然而预混燃烧中的燃烧稳定性问题是威胁燃气轮机安全运行的关键问题。为了研究合成气稀态预混燃烧过程的燃烧不稳定性问题,本文设计了一个模型燃烧试验器,并采用详细化学反应模型进行了数值计算,对其流场特性、预混效果及NO_x排放特性进行了详细分析。     

高温空气燃烧NOx排放特性的试验研究

通过两种结构烧嘴的热态燃烧试验对比,研究了烧嘴结构、燃气射流速度、过量空气系数对高温空气燃烧过程氮氧化物排放的影响特性。研究结果认为:在燃气喷口两侧布置两个矩形空气喷口的烧嘴,氮氧化物排放量低于圆形空气喷口烧嘴;随着燃气射流速度的提高,高温空气燃烧过程排放的氮氧化物逐渐减少。与普通燃烧过程不同的是,随着过量空气系数的提高,在一定范围内高温空气燃烧的氮氧化物排放量不断增加。分析认为,高温空气燃烧氮氧化物排放量与火焰体积、炉内氧气与燃气混合过程以及燃气射流和空气射流对炉内烟气的卷吸量有关。     

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.     

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.     

An analytical study of droplet combustion under microgravity: Quasi-steady transient approach

An analytical model based on an assumption of combined quasi-steady and transient behavior of the process is presented to exemplify the unsteady, sphero-symmetric single droplet combustion under microgravity. The model used in the present study includes an alternative approach of describing the droplet combustion as a process where the diffusion of fuel vapor residing inside the region between the droplet surface and the flame interface experiences quasi-steadiness while the diffusion of oxidizer inside the region between the flame interface and the ambient surrounding experiences unsteadiness. The modeling approach especially focuses on predicting; the variations of droplet and flame diameters with burning time, the effect of vaporization enthalpy on burning behavior, the average burning rates and the effect of change in ambient oxygen concentration on flame structure. The modeling results are compared with a wide range of experimental data available in the literature. It is shown that this simplified quasi-steady transient approach towards droplet combustion yields behavior similar to the classical droplet theory.     

The effects of SiO2 and TiO2 on the two-phase burning behavior of aqueous HAN propellant

Silica and titania nanoparticles were included at mass loadings of 1% and 3% in aqueous HAN propellants to evaluate their effects on liquid- and gas-phase decomposition and combustion. Both the liquid-phase and overall burning rates of propellant formulations were indirectly measured in a constant-volume strand burner filled with Argon from pressures of 3–22?MPa using a novel, pressure-based method developed by the authors in recent work. This approach provides overall burn times for propellants such as aqueous HAN which continue to burn beyond the disappearance of the liquid, making it superior to methods based solely on visual observation which only monitor the liquid surface regression. The presence of silica nanoparticles increased the liquid-phase burning rate in the low- and medium-pressure regimes (<10?MPa) and increased the overall burning rate at all pressures evaluated. The maximum amount of burning rate enhancement was realized at the lowest evaluated pressure (3?MPa) which corresponded to 80% and 670% increases in the liquid-phase and overall burning rates, respectively, for a silica loading of 1%, and 160% and 830% increases in the liquid-phase and overall burning rates, respectively, for a silica loading of 3%. The presence of titania did not measurably affect the liquid-phase burning rate, but it did increase the overall burning rate in the low-pressure regime (<5.7?MPa). This low-pressure overall burning rate enhancement was not amplified by further titania loading from 1% to 3% and was maximized at the lowest evaluated pressure (3?MPa) which corresponded to a 500% increase in the overall burning rate. The observed enhancements of the propellant's liquid-phase and overall burning rates were attributed to the presence of catalytic processes which diminish at higher pressures. This work represents the first time nanoparticle additives have been utilized to tailor the combustion of liquid HAN-based monopropellants.     

Combustion of partially premixed spray jets

Gas turbines, liquid rocket motors, and oil-fired furnaces utilize the spray combustion of continuously injected liquid fuels. In most cases, the liquid spray is mixed with an oxidizer prior to combustion, and further oxidizer is supplied from the outside of the spray to complete diffusion combustion. This rich premixed spray is called “partially premixed spray.” Partially premixed sprays have not been studied systematically although they are of practical importance. In the present study, the burning behavior of partially premixed sprays was experimentally studied with a newly developed spray burner. A fuel spray and an oxidizer, diluted with nitrogen, was injected into the air. The overall equivalence ratio of the spray jet was set larger than unity to establish partially premixed spray combustion. In the present burner, the mean droplet diameter of the atomized liquid fuel could be varied without varying the overall equivalence ratio of the spray jet. Two combustion modes with and without an internal flame were observed. As the mean droplet diameter was increased or the overall equivalence ratio of the spray jet was decreased, the transition from spray combustion only with an external group flame to that with the internal premixed flame occurred. The results suggest that the internal flame was supported by flammable mixture through the vaporization of fine droplets, and the passage of droplet clusters deformed the internal flame and caused internal flame oscillation. The existence of the internal premixed flame enhanced the vaporization of droplets in the post-premixed-flame zone within the external diffusion flame.     

“Slow” active control of combustion instabilities by modification of liquid fuel spray properties

This paper describes an experimental investigation of the feasibility of using “slow” active control approaches, which “instantaneously” change liquid fuel spray properties, to suppress combustion instabilities. The objective of this control approach was to break up the feedback between the combustion process heat release and combustor pressure oscillations that drive the instability by changing the characteristics of the combustion process (e.g., the characteristic combustion time). To demonstrate the feasibility of such control, this study used a proprietary fuel injector (Nanomiser^TM), which can vary its fuel spray properties, to investigate the dependence of acoustics–combustion process coupling, i.e., the driving of combustion instabilities, upon the fuel spray properties. This study showed that by changing the spray characteristics it is possible to significantly damp combustion instabilities. Furthermore, using combustion zone chemiluminescence distributions, which were obtained by Abel’s deconvolution synchronized with measured acoustic data, it has been shown that the instabilities were mostly driven midway between the combustor centerline and wall, a short distance downstream from the flame holder, where the mean axial flow velocity is approximately zero in the vortex near the flame holder. The results of this study strongly suggest that a “slow” active control system that employs controllable fuel injectors could be effectively used to prevent the onset of detrimental combustion instabilities.     

Effects of fuel viscosity on the primary breakup dynamics of a high-speed liquid jet with comparison to X-ray radiography

One of the major concerns in combustion engines is the sensitivity of engine performance to fuel properties. Recent works have shown that even slight differences in fuel properties can cause significant changes in performance and emission of an engine. In order to design the combustion engines with multi-fuel flexibilities, the precise assessment of fuel sensitivity on liquid jet atomization process is a prerequisite since the resulting fuel/air mixture is critical to the subsequent combustion process. The present study is focusing on the effect of physical fuel properties, mostly viscosity difference, on the breakup process of the liquid jet injected into still air. Two different jet fuels, CAT-A2 and CAT-C3, are considered here as surrogates for a fossil-based fuel and a bio-derived high-viscosity alternative fuel. The simulations are performed using the volume-of-fluid (VoF) interface tracking method coupled to Lagrangian particle method in order to capture the breakup instabilities of jets and the resulting droplets. The investigations take the actual geometry of the injector into account to resolve the unsteady flow phenomena inside the nozzle that impact the turbulence transition and atomization. The simulation results are compared to the experimental measurement using X-ray radiography. Both simulation and X-ray measurements consistently describe the effects of different fuels on the fundamental properties of atomization including the breakup length, transverse liquid volume fraction and the droplet sauter-mean-diameter. The application of a Detailed Numerical Simulation approach complemented by unique X-ray diagnostics is novel and providing new understanding and research directions in engine spray dynamics.