Effect of Nozzle Inclination Angle on Fuel-Air Mixing and Combustion in a Heavy Fuel Engine

Heavy-fuel engines are widely used in UAVs(Unmanned Autonomous Vehicles)because of their reliability and high-power density.In this study,a combustion model for an in-cylinder direct injection engine has been imple-mented using the AVL FIRE software.The effects of the angle of nozzle inclination on fuel evaporation,mixture distribution,and combustion in the engine cylinder have been systematically studied at 5500 r/min and consider-ing full load cruise conditions.According to the results,as the angle of nozzle inclination increases,the maximum combustion explosion pressure in the cylinderfirst increases and then it decreases.When the angle of nozzle incli-nation is less than 45°,the quality of the mixture in the cylinder and the combustion performance can be improved by increasing the angle.When the angle of nozzle inclination is greater than 45°,however,the mixture unevenness increases slightly with the angle,leading to a deterioration of the combustion performances.When the angle of nozzle inclination is between 35°and 55°,the overall combustion performance of the engine is rela-tively good.When the angle of nozzle inclination is 45°,the combustion chamber’s geometry and the cylinder’s airflow are well matched with the fuel spray,and the mixture quality is the best.Compared with 25°,the peak heat release rate increases by 20%,and the maximum combustion burst pressure increases by 5.5%.

Catalytic performance for methane combustion of supported Mn-Ce mixed oxides

A series of supported Mn-Ce mixed oxide catalysts were prepared by the impregnation method and used for the oxidation of methane. The catalysts were characterized by N2 adsorption （BET）, X-ray diffraction （XRD）, laser Raman spectrum （LRS）, and temperature programmed reduction （TPR） techniques. The XRD and LRS results confirmed the high dispersion of active components or formation of solid solution between manganese and cerium oxides in the bulk and on the surface of mixed oxide catalysts. The reducibility was remarkably promoted by the stronger synergistic interaction between the two oxides from H2-TPR measurements. As expected, all the experimental mixed oxide catalysts showed excellent activity for methane combustion at low temperature. Especially, for the catalyst with Mn-Ce ratio 3：7, methane conversion reached 92% at a temperature as low as 470 ℃.

Experimental Investigation of the Effect of Mixed Additives on Homogeneous Charge Compression Ignition Combustion

The experimental investigation of homogeneous charge compression ignition (HCCI) process is carried out on a 4-cylinder diesel engine. One of the cylinders is modified for HCCI combustion with mixed additives. The influence of mixed additives on the HCCI combustion process is investigated. The experimental results indicate that the mixed additives are better than the single additives for HCCI fuel, causing ignition and heat release to be advanced and the peak of heat release rate to increase under the condition of different engine speeds and steady HCCI combustion. Moreover, with the increase in engine speed, the influence of mixed additives on HCCI combustion is more obvious. In addition, the mixed additives are beneficial to improve HCCI engine misfire at a high engine speed and make the engine operate stable.

Experimental Study of MHD-Assisted Mixing and Combustion Under Low Pressure Conditions

In order to reveal the mechanism of MHD-assisted mixing, and analyse the major parameters which influence the effect of MHD-assisted mixing, experiments of MHD-assisted mixing are carried out with a non-premixed butane-air combustion system. The evolvement of the discharge section and the effect of MHD-assisted mixing on combustion are investigated by changing the magnetic flux density and airflow velocity. The results show that the discharge area not only bends but also rotates around the centered wire electrode, which are mainly caused by the Lorentz force. Moreover, the highest curvature occurs near the centered wire electrode.The discharge localizes near the surface of the wire electrode and annular electrode when there is no ponderomotive force. However, if the ponderomotive force is applied, the discharge happens between these two electrodes and it gradually shrinks with time. The discharge area cannot localize near the annular electrode, which is due to the increase of energy loss in the airflow.When the airflow velocity exceeds a certain value, the discharge section becomes unstable because the injected energy cannot maintain the discharge. The rotation motion of the discharge section could enlarge the contact surface between butane and air, and is therefore beneficial for mixing and combustion. Magnetic flux density and airflow velocity are critical parameters for MHD-assisted mixing.

THE COMBUSTIBILITY OF CHINESE FIR AND MACCLURE MICHELIA MIXED FOREST

Based on the theory of forest burning link, the combustibility of the 6-year-old Chinese fir (Cunninghamia lanceolata) and macclure michelia (Michelia macclurei) mixed forest was determined in Youxi County, Fujian Province from 1988 to 1989. The results show that the daily mean moisture in the forest, moisture content of litter and the water reserves of the stand in mixed forest are 3%, 7.6% and 46.8% higher than that in pure stand respectively, the inflammables quantity and energy ratios of the stand biomass and total potential energy in mixed stand are 8.5% and 3.69% lower than that in pure stand respectively. Mixed forest can decrease the combustibility of stand.

Effects of Lobe Peak-to-Trough Width Ratio on Mixing and Combustion Performance in ATR Combustors

The air-turbo-rocket(ATR)engine is a promising propulsion plant for achieving numerous surface and air launched missile missions.The application of lobed mixer in the ATR combustor can promote the mixing of the fuelrich gas and the air,thus improving the engine performance significantly.The numerical simulation method was conducted to explore the effects of lobe peak-to-trough width ratio on mixing and combustion performance in ATR combustors.Results show that:For a given peak lobe width b1,the combustion efficiency and total pressure loss decrease with the increase of trough lobe width b2;For a given b2,the combustion efficiency and total pressure loss decrease with the increase of b1;The fan-type lobed mixer with smaller b2has a better effect on promoting the combustion efficiency in the region near the ATR combustor center line than that with a pair of parallel side walls.The total pressure recovery coefficient reaches more than 0.99 at the exit of combustor in nonreactive combustion while the total pressure loss reaches more than 4%in the reacting combustion.Compared with the mixing process,more than80%of the total pressure loss is caused during combustion.

Effect of kerosene injection states on mixing and combustion characteristics in a cavity-based supersonic combustor

It has been found that the static pressure distribution along the axial direction of liquid kerosene is lower than that of the gaseous kerosene under the same flow condition and overall equivalent ratio from previous studies.To further investigate this phenomenon,a compressible two-phase parallel simulation method is utilized to analyze the mixing and combustion characteristics of gaseous and liquid kerosene jets in a cavity-based supersonic combustor.The numerical results are consistent with the experiments and demonstrate that gaseous injection leads to a cavity shear layer that dives deeper into the cavity,forming two recirculation zones in the front and rear of the cavity.In contrast,the cavity shear layer is closer to the mainstream during liquid injection,and only a large recirculation zone is formed in the rear of the cavity.As a result of the cavity shear layer and the recirculating flow,the fuel vapor of gaseous injection accumulates in the front of the cavity,while for the liquid injection,the fuel vapor disperses in the cavity,cavity shear layer,and the region above,and the rear of the cavity has a higher fuel vapor concentration than the front.This unique fuel distribution causes the combustion area to be concentrated in the cavity during the gaseous injection but dispersed inside and downstream of the cavity during the liquid injection.As a result,forming a thermal throat under the same conditions is more challenging during liquid injection,and the generated static pressure distribution is lower than that during the gaseous injection.

Co–Cr–O mixed oxides for low–temperature total oxidation of propane: Structural effects, kinetics, and spectroscopic investigation

A series of Co–Cr–O mixed oxides with different Co/Cr molar ratios are synthesized and tested for the total oxidation of propane.The reaction behaviors are closely related to the structural features of the mixed oxides.The catalyst with a Co/Cr molar ratio of 1:2(1 Co2 Cr)and a spinel structure has the best activity(with a reaction rate of 1.38μmol g^–1 s^–1 at 250℃),which is attributed to the synergistic roles of its high surface acidity and good low-temperature reducibility,as evidenced by the temperature-programmed desorption of ammonia,reduction of hydrogen,and surface reaction of propane.Kinetic study shows that the reaction orders of propane and oxygen on the 1 Co2 Cr catalyst(0.58±0.03 and 0.34±0.05,respectively)are lower than those on the 2 Co1 Cr catalyst(0.77±0.02 and 0.98±0.16,respectively)and 1 Co5 Cr(0.66±0.05 and 1.30±0.11,respectively),indicating that the coverages of propane and oxygen on 1 Co2 Cr are higher than those on the other catalysts due to its higher surface acidity and higher reducibility.In addition,in-situ diffuse reflectance infrared spectroscopic investigation reveals that the main surface species on 1 Co2 Cr during the reaction are polydentate carbonate species,which accumulate on the surface at low temperatures(<250℃)but decompose at relatively high temperatures.

Study on the influences of interaction behaviors between multiple combustion-gas jets on expansion characteristics of Taylor cavities

The purpose of this study is to investigate means of controlling the interior ballistic stability of a bulk-loaded propellant gun（BLPG）.Experiments on the interaction of twin combustion gas jets and liquid medium in a cylindrical stepped-wall combustion chamber are conducted in detail to obtain time series processes of jet expansion,and a numerical simulation under the same working conditions is also conducted to verify the reliability of the numerical method by comparing numerical results and experimental results.From this,numerical simulations on mutual interference and expansion characteristics of multiple combustion gas jets（four,six,and eight jets） in liquid medium are carried out,and the distribution characteristic of pressure,velocity,temperature,and evolutionary processes of Taylor cavities and streamlines of jet flow Held are obtained in detail.The results of numerical simulations show that when different numbers of combustion gas jets expand in liquid medium,there are two different types of vortices in the jet flow field,including corner vortices of liquid phase near the step and backflow vortices of gas phase within Taylor cavities.Because of these two types of vortices,the radial expansion characteristic of the jets is increased,while changing numbers of combustion gas jets can restrain Kelvin-Helmholtz instability to a certain degree in jet expansion processes,which can at last realize the goal of controlling the interior ballistic stability of a BLPG.The optimum method for both suppressing Kelvin-Helmholtz instability and promoting radial expansion of Taylor cavities can be determined by analyzing the change of characteristic parameters in a jet flow field.

凹腔构型对超声速气-固两相富燃燃气掺混燃烧的影响

凹腔作为燃烧增强装置,在超声速气-固两相富燃燃气掺混燃烧中发挥着重要作用。基于火焰稳定凹腔和斜劈装置,提出了波瓣凹腔构型,通过数值模拟深入分析了凹腔构型在超声速气流中对气-固两相富燃燃气掺混燃烧的影响。通过对流场参数、流场云图及颗粒运动轨迹等的分析,发现富燃燃气中的气相组分和凝相颗粒在空间分布和释能过程中表现出分区运动和分区燃烧的特点。结果表明:随着燃烧过程的深入,颗粒的空间分布逐渐分散;流场参数在燃气喷口附近变化剧烈、流场下游变化缓慢;波瓣结构具备增强流场湍动能和降低流场不均匀性的能力,进而促进了各组分的掺混燃烧;采用双波瓣凹腔时展现出最优的促进效果。波瓣结构能够扩大流场中高温区域的空间分布,有效延长凝相颗粒在高温区域的停留时间,为凝相颗粒的燃烧和能量释放提供了更为有利的条件。

EGR技术对生物柴油混合燃料发动机性能的影响研究

为缓解柴油掺烧生物柴油导致的NO_(x)排放过高问题,将4190ZLC船用中速柴油机作为试验台架,通过AVL_FIRE软件建立燃烧室模型,并验证该模型准确性。设置生物柴油掺混比0~40%等4组变量,EGR率0~12.5%等4组变量,进行柴油机燃烧、性能和排放分析。结果表明,掺烧适量生物柴油能够降低柴油机缸内温度,降低Soot排放,但同时会导致NO_(x)排放明显升高;EGR的引入能够实现低温燃烧,显著降低NO_(x)排放,但EGR率过高会增加Soot排放。生物柴油掺混比B40、EGR率12.5%组合NO排放比原机降低47.7%,Soot排放质量分数比原机降低98.13%。本文结果将为柴油掺混生物柴油燃烧并结合EGR技术提供一定的研究方向。

水泥分解炉SNCR脱硝系统的深度强化学习多目标优化控制研究

选择性非催化还原(selective non-catalytic reduction,SNCR)脱硝过程的工艺参数优化可以有效减少水泥分解炉NO_(x)排放和脱硝运行成本。以某水泥分解炉为研究对象,建立基于LightGBM的NO_(x)浓度预测模型,以脱硝成本和NO_(x)浓度最小化为优化目标,采用深度确定性策略梯度(deep deterministic policy gradient,DDPG)算法对水泥分解炉掺烧污泥协同SNCR脱硝过程的相关工艺参数进行优化控制建模。结果表明,NO_(x)浓度预测模型均方根误差(root mean squared error,RMSE)为6.8,平均绝对百分比误差(mean absolute percentage error,MAPE)为3.48%;采用DDPG算法可以对相关工艺参数进行优化,喷氨量和污泥掺烧量分别为427.87 L/h和9.78 t/h时,NO_(x)排放浓度为225.99 mg/(Nm^(3)),脱硝运行成本为1 747.8元/h。该优化结果与其他优化算法结果和常规工况对比,NO_(x)排放浓度和脱硝运行成本均呈现不同程度下降;对模型进行仿真及效果验证可知,所建立模型能输出合理的喷氨量和污泥掺烧量组合,减少SNCR出口NO_(x)浓度波动,有效降低NO_(x)排放浓度和脱硝成本,可实现对SNCR脱硝系统的多目标优化控制。该结果可为基于智能算法的水泥分解炉SNCR脱硝的多目标优化控制设计提供一定参考。

H_(2)与氨混燃增强火焰燃烧特性模拟研究

氢和氨作为清洁能源受到广泛关注,为深入探究氢-氨混燃的燃烧特性和影响因素,本文借助Chemkin仿真平台建立相关反应模型,以氢-氨混合气体为燃料,空气作为助燃剂,采用Otomo等人提出的一种氨氧化机理对其燃烧过程进行模拟计算,并模拟研究了混合气体的点火延迟时间、层流燃烧速度、绝热燃烧温度、NO排放等燃烧特性随当量比、初始压力以及燃料中H_(2)比例的具体变化规律,对不同工况下的层流火焰结构、H和OH自由基的产率(rate of production,ROP)、NO生成的敏感度进行了化学动力学分析。结果表明:纯氨气体的点火延迟时间长、层流燃烧速度慢,掺氢后燃烧特性均有所改善,且提高了火焰的绝热燃烧温度,但掺氢比例越大,NO排放越多。NO摩尔分数随当量比变化的趋势先增后减,在当量比为0.8左右达到峰值。综合考虑氢-氨混燃的一系列燃烧特性以及掺氢、加压的成本和收益情况,推荐H_(2)占比15%、当量比φ=1.1、压力P=0.2 MPa为氢-氨混合燃烧的最优条件。

固体火箭超燃冲压发动机点火燃烧过程实验研究

为解决硼基贫氧燃料固体火箭超燃冲压发动机补燃室内硼颗粒超声速点火燃烧难题,设计制造了在超声速燃气射流掺混区域开设观察窗的点火燃烧过程试验样机,开展了含硼贫氧固体燃料的超声速点火试验。试验模拟了26 km,Ma5.9的飞行工况并通过高速摄像获得了点火燃烧过程的火焰形态。试验结果表明:掺混增强装置可以显著改善补燃室内存在的分层流动和一次燃气气固两相分离的现象,为硼颗粒提供良好的点火条件从而提升其附近硼颗粒的点火燃烧性能。通过合理设计掺混增强装置位置,将硼颗粒在一次燃气喷注口附近的高温点火区点燃比在补燃室中段点燃具有更高的燃烧效率,本文设计的燃烧组织结构在试验中实现了硼贫氧固体燃料0.812的燃烧效率。

甲烷掺氢燃料反应动力学特性分析及机理验证

燃气轮机燃用天然气-氢气混合燃料可以大幅降低碳排放。为了研究天然气在不同掺氢比时的燃烧特性,利用Cantera开源程序对其基本反应动力学特性开展研究,计算常压和典型F级燃气轮机运行条件下不同掺氢比时混合燃料的层流火焰速度、点火延迟时间等基本反应动力学参数。分析8种反应机理计算获得的火焰位置、温度场分布、主要燃烧产物(CO_(2)和H_(2)O)、中间燃烧产物(OH基和CO)和微量燃烧产物NO的浓度分布,并与悉尼大学天然气-氢气混合燃料(体积分数50%H_(2)+50%CH_(4))模型燃烧室实验数据进行比较。结果表明,采用DRM22、USC2、Kee以及Miller-Bowman机理计算获得的混合气体燃烧特性与实验结果吻合,耦合加州大学单独的氮氧化物机理后所获得的NO_(x)排放值也具有较高的计算精度。结果可为氢燃料燃气轮机燃烧室性能的后续研究提供理论依据,为氢燃料燃气轮机的安全运行奠定基础。

氧化剂燃气来流下TAGN富燃料掺混燃烧特性

在新型氧/燃分离式组合固体发动机中,氧化剂燃气来流工况对富燃料掺混燃烧特性具有重要影响。为揭示氧化剂来流下富燃料掺混燃烧特性,基于课题组前期建立的氧化剂/富燃料掺混燃烧反应详细机理,构建了新型氧/燃分离式组合固体发动机二维稳态燃烧模型。通过数值仿真分析,获得了不同来流温度和马赫数下,高氯酸铵(AP)氧化剂燃气对硝酸三氨基胍(TAGN)富燃料掺混燃烧特性的影响。结果表明,随着AP燃气来流的初温升高,沿流动方向的混合效果变强,而沿径向方向的混合效果变差,TAGN富燃料前端传热系数有所提升,燃面平均退移速率出现小幅下降;增大AP燃气来流马赫数,显著强化了AP和TAGN的掺混和传热过程,提高了TAGN燃气和AP燃气之间的反应速率,燃面平均退移速率显著增大。

特征参数对微混喷嘴内燃料与空气混合均匀性影响

由于微混喷嘴尺寸小、数量多且无旋流的结构特点,微混燃烧室结构可能形成新的设计准则。为探究微混喷嘴的混合特性优化方法,提取微混喷嘴内雷诺数、相对预混长度、射流动量比等特征参数,通过大涡模拟模型研究其对混合均匀性的影响规律。结果表明:微混喷嘴内预混距离增加,燃料与空气的掺混空间扩大,混合特性明显提升;在较大的射流动量比下,燃料与空气掺混更加剧烈,混合质量上升;燃料入口流速对于喷嘴混合性能的影响并不明显;雷诺数大于1×10^(5)时,喷嘴内流动达到第二自模化区,混合均匀度不再随雷诺数的变化而改变。通过特征参数对喷嘴的混合均匀度进行拟合,所得公式可在当量比为0.5~1.0、雷诺数大于1×10^(5)及入口空气温度为18~818℃时对混合均匀度进行准确预测。该公式可对微混喷嘴的混合特性进行初步计算,并为其结构设计提供参考经验。

掺氢比例对螺旋微混-旋流复合喷嘴燃烧不稳定的影响研究

为实现燃气轮机低排放目标,进行了螺旋微混-旋流复合结构喷嘴在不同掺氢比例下的燃烧不稳定特性实验研究。在恒定输出功率下,探究了掺氢体积分数为0%~100%时燃烧室腔体及预燃级内压力振荡状态。结果表明:在主燃级当量比为0.45的条件下,燃烧室压力振幅随着掺氢比例增加先增加后减小,掺氢比例为70%时,燃烧室内出现了2903.4、4490.2 Hz 2种频率的压力振荡信号;该掺氢比例下燃烧产生的这2种压力振荡频率与燃烧室固有声学模态频率重合,进而形成驻波;预燃级一阶声学模态频率为5450 Hz,燃烧区产生的该频段声波传播至预燃级内形成驻波,导致预燃级内出现5400 Hz附近的压力脉动峰值,与燃烧室腔体相反,其在70%掺氢比例工况下的压力脉动幅值最小;综合燃烧室及预燃级压力脉动情况,主燃级的掺氢比例在30%~60%区间最为合适。

污泥/煤泥混合燃烧过程中N和S污染物迁移规律

为探究污泥/煤泥混合燃烧过程中N、S污染物的排放机理,开展N、S污染物迁移规律研究.基于热重-质谱分析仪获得的污泥/煤泥混合燃烧时气态污染物的基础生成规律,建立污泥/煤泥混合燃烧实验系统,研究不同污泥质量分数、温度下污泥/煤泥混合燃烧的SO_(2)、NO的排放规律,并通过对4个不同阶段燃烧产物的X射线光电子能谱(XPS)检测,研究N、S官能团在燃烧过程中的转化规律.结果表明,污泥质量分数为40%时固硫固氮效果最明显;随污泥质量分数增加,吡啶类氮更多转化为吡咯类氮,使HCN产量增加以及胺类和腈类生成量增加,导致总NO排放量随污泥质量分数增加先增加后减少;有机硫类释放更为完全,燃烧产生的含S污染物增多,灰分中硫酸盐含量同步增长,因此总SO_(2)的释放量随污泥质量分数增加变化较小.

掺氢对天然气燃烧室燃烧及排放特性影响

天然气混合氢气燃烧可有效降低含碳物质的排放。但掺混氢气会改变燃料性质,进而影响燃烧进程,故有必要对掺氢燃烧进行深入研究。主要研究了以混氢天然气为燃料的燃气轮机的燃烧特性和排放特性,采用数值模拟的方法研究不同的掺氢比(H_(2)体积含量为0~100%,一共6种工况)对GE-10实验型燃气轮机燃烧室燃烧过程的影响。研究结果表明,随着掺氢比的增加,火焰温度上升,燃烧反应区前移。在低掺混比下火焰筒出口处的温度分布随掺氢比增大趋向均匀,当掺氢比超过0.6时,出口处温度分布均匀性大幅下降。此外,混合燃料中氢气成分的增加会导致局部释热量提高,进而导致NO_(x)排放增加,当掺氢比超过0.8时,NO_(x)排放量增加的幅度变大。同时,随着掺氢比的提高,CO和CO_(2)的排放量显著减少,H_(2)O的生成量显著增加。研究结果将为后续混氢燃烧技术在工业燃气轮机上的应用提供理论指导。