CH4/空气简化动力学机理数值验证

选择绕圆柱预混燃烧算例，验证CH₄/空气三种简化动力学机理（16s41r、15s19r和53s325r）.考虑均匀来流，忽略湍流和湍流与燃烧相互作用以及燃料扩散效应，假设层流有限反应速率，采用保自由流5阶WENO格式求解多组分Euler方程组，得到CH₄/空气预混燃烧流场温度等值线、沿驻点线压力和温度及其CH₄、CO和CO₂质量百分数分布.结果表明：三种简化动力学机理给出的流场均出现弓形激波和火焰面，弓形激波和火焰驻点距离及其形状、诱导区宽度和简化动力学机理相关.当圆柱直径增大，弓形激波和火焰向圆柱上游移动，对应的驻点距离均增大，诱导区宽度变短，点火延时变小，但火焰和弓形激波位置次序未变化.53s325r模型要比16s41r模型和15s19r模型精度要高，点火延时覆盖的压力和温度范围也较宽，所有简化机理均未完全反应，在较大圆柱直径下游达到化学平衡.     

超音速等离子体点火过程的三维数值模拟

为了研究等离子体点燃超音速混合气流的过程,设计并验证了超音速燃烧室的三维计算模型,计算出了燃烧室等离子体点火时的流场参数和化学反应规律,分析了等离子体点火对燃烧室内燃烧的影响。计算结果表明:高温等离子体射流的滞止作用通过增加混合气在燃烧室内的停留时间提高了点火效率; 等离子体点火时燃烧区域的压力扩散比较充分,内部为压力相对平衡的低速流动; 高温等离子体射流高速射向混合气流时产生的速度矢量偏移扩大了点火面积,从而使点火效率得到提高; 氢气、空气燃烧的燃烧产物主要是水,燃烧区域局部温度主要受局部放热反应的影响。     

第18届全国激波与激波管学术会议青年优秀论文专题序言

正激波作为气体动力学最具特色的基本物理现象之一,表现出强间断与非线性的物理特征.激波能够在超/高超声速气流内部诱导漩涡,生产复杂的气体物理过程;激波能够诱导热化学反应,构成了高温气体力学和凝聚态爆轰动力学的学科基础;激波还能够压缩可燃气体实现其自点火,形成能够以超声速自持传播的燃烧反应带;而激波管则是一种广泛应用的实验技术,发展前途是无限的.     

弹头激波诱导燃烧特性的数值模拟

为了研究弹头激波诱导燃烧，基于有限体积的考虑化学反应的Navier-Stokes（N-S）方程，对预混氢气-空气化学恰当比时的燃烧流场进行了数值模拟.时间项基于2阶隐式LU-SGS格式，对流项基于Steger-Warming进行离散，化学反应源项采用对角化隐式处理.首先，研究了网格对燃烧爆轰流场结构的影响，并利用Lehr实验结果验证了计算方法的可靠性；其次，研究了弹头的飞行Mach数（Ma=4.18，5.11，6.46）、弹头直径（D=5，10，15 mm）对燃烧流场稳定性的影响.研究表明:计算网格对氢气-空气爆轰流场结构影响很大；弹头直径一定时，氢气-空气燃烧流场稳定性随着飞行Mach数的增大而增强；弹头飞行Mach数一定时，氢气-空气燃烧流场稳定性随着弹头直径减小而增强.      

基于特征线理论的辨识法在激波装配中的应用

准确地给出激波位置信息对于激波装配极为重要.但是，在使用计算流体力学（computational fluid dyna-mics，CFD）方法模拟复杂流动时很难准确地给出激波的位置.根据激波捕捉得到的流场信息确定的激波位置往往带有极大误差，在定常问题的模拟中，这种误差可以随着迭代逐渐消除，然而在非定常问题的模拟中，这种误差往往会积累甚至导致计算崩溃.文章将基于特征线理论的激波辨识技术应用到激波装配中，根据已有流场信息准确判断激波的位置.对于定常问题，该方法的应用加速了收敛速度；对于非定常问题，该方法的应用可以极大地避免初始误差的产生.      

MILD煤粉燃烧湍流与化学反应相互作用的数值分析

采用计算流体动力学(CFD)数值模拟方法分析了湍流与化学反应相互作用下MILD煤粉燃烧的微观特征。比较了涡耗散模型(EDM模型)和涡耗散概念模型(EDC模型)对MILD煤粉燃烧的影响,两者得到的速度场、温度场、烟气成分等结果与实验结果符合较好.在此基础上分析了MILD煤粉燃烧湍流和化学反应的微观特征尺度,发现采用EDC模型能更准确地反映MILD煤粉燃烧的微观特征,即山于强烈的烟气内部再循环导致的高湍流混合和烟气稀释后低氧浓度下的缓慢化学反应.     

极端条件两相界面流与反应流机理、模型与算法研究进展

清华大学喷雾燃烧与推进实验室长期专注于极高速、强可压和高瞬变等极端条件下的两相流和反应流前沿科学问题,并致力于应用基础研究成果解决航空航天动力与推进系统的关键技术难题。综述了实验室近些年在极端条件下两相流动和含化学反应流动物理机理、数理模型与数值算法等方面的研究进展。首先,介绍了实验室发展的耦合高瞬变相变过程的强可压缩气液两相界面流的数理模型和高精度数值方法,以及针对激波受气液（曲）界面约束情况下,描述非定常激波透射/反射（如波角、波强等物理量关系）的激波动力学分析方法。其次,基于上述模型、算法与分析方法,实验室研究了激波液滴相互作用、高速液滴撞击壁面等一系列问题,解析了上述高瞬变过程中复杂波系与界面的时空演化过程。以被激波或壁面冲击的液滴内流体空化初生为例,揭示了曲界面汇聚膨胀波诱导流体空化的机理,推导了预测空化初生位置的理论公式。最后,介绍了面向发动机燃烧室内的强可压缩两相喷雾反应流动,实验室开发了基于Euler-Lagrange框架的高性能数值仿真软件TURFsim,并成功用于真实复杂几何结构的航空发动机燃烧室和超声速燃烧室的数值模拟。以典型的超声速混合层流动数值模拟为例,总结了斜激波增强混合层混合特性的规律及其物理机理,获得了极限条件火核生成及火焰的传播模式与机理,详细分析了液雾弥散与蒸发、小激波和局部爆震波的时空演化特性,提出使用"第三Damk?hler数Da_Ⅲ"定量表征燃烧模式,应用该无量纲参数成功进行了局部准等容燃烧过程的辨识与演化分析。上述研究结果对于航空航天发动机燃烧室复杂物理过程的理解及工程设计具有重要价值。      

基于详细化学反应机理的DME发动机三维湍流燃烧模拟

采用基于详细化学反应机理的三维湍流燃烧数值模拟,研究直喷柴油机燃用二甲基醚(DME)的伴有化学反应的流动燃烧现象.模拟预测的缸内压力随曲轴转角的变化及NO排放浓度与实验相符.分析了计算所得的曲轴转角随缸内流场速度、温度和组分浓度的分布历程,结果表明甲醛在低中温下相对稳定,随着温度的升高,氧化反应加速进行,而由于流动及壁面传热等效应,甲醛作为不完全燃烧产物存在于排气中.     

转捩与湍流对激波边界层干扰及底部流动结构的影响

为研究转捩与湍流对激波边界层干扰及底部流动结构的影响，文章选取了二维与三维高超声速双斜面进气道模型与大钝头着陆器模型，并使用γ-Re_θ转捩模型开展数值模拟研究.研究表明，对于二维进气道模型，随着前缘钝度的增加，激波边界层干扰位置前移，分离区变大，与层流流动情况相比，有转捩流动发生时，激波边界层干扰位置后移，同时分离流动强度变弱，分离区缩小；对于三维进气道模型，其拐角附近的分离流动呈现明显的三维特征，转捩流动也存在三维流动结构，与静风洞状态相比，噪音风洞状态下，有转捩流动发生，对壁面热流影响较大，对激波系影响很小.对于着陆器模型，底部流动发生转捩，使得底部流动由不稳定非定常的流动结构变为稳定定常的流动结构，这有益于姿态控制设计.      

JF12激波风洞高Mach数超燃冲压发动机实验研究

针对高Mach数（Ma ≥ 7）超燃冲压发动机高气动阻力下的燃烧组织问题，提出一种双突扩燃烧室结构方案.使用数值模拟方法考察了射流与双突扩燃烧室组合方式的混合燃烧特性.设计了双突扩超燃冲压发动机模型，在力学研究所JF12长试验时间激波风洞内，开展了Ma=7.0和Ma=9.5的氢燃料点火和燃烧试验对比.在风洞有效试验时间100 ms内，实现了Ma=7.0和Ma=9.5超燃冲压发动机的成功点火与稳定燃烧.在Ma=7.0情况下，进气道采用三维压缩，燃烧室入口设计Mach数Ma_c=2.5，壁面压力分布实验结果显示燃烧放热靠近燃烧室扩张段上游；在Ma=9.5情况下，进气道采用二维压缩，燃烧室入口设计Mach数Ma_c=3.5，由于燃烧室流动速度特别高，燃烧放热靠近燃烧室扩张段下游.      

Diesel flame lift-off stabilization in the presence of laser-ignition: a numerical study

Diesel flame lift-off and stabilization in the presence of laser-ignition were numerically investigated with the method of Eulerian stochastic fields. The aim was to scrutinise the interaction between the lifted diesel flame and an ignition kernel upstream of the lifted flame. The numerical simulation was carried out in a constant-volume combustion vessel with n-heptane as fuel. The process was studied previously in an experiment employing Diesel #2 as the fuel in the same combustion vessel. In the experiment a lifted flame was first established at a position downstream of the nozzle. An ignition kernel was then initiated using a high-energy pulse laser at a position upstream of the natural lift-off position of the diesel flame. The laser-ignition kernel was modelled using a high-temperature (～2000 K) hot spot. In both experiment and simulations the upstream front of the ignition kernel was shown to remain around the initial laser ignition site for a substantially long period of time, while the downstream front of the ignition kernel propagates rapidly towards the natural lift-off position downstream of the laser ignition site. The lift-off position oscillated before the final stabilization at the natural lift-off position. The structures and the propagation speed of the reaction fronts in the laser-ignition kernel and the main flame were analysed. Two different stabilization mechanisms, the auto-ignition mechanism and the flame propagation mechanism, were identified for the naturally lifted flame and the laser-induced reaction front, respectively. A mechanism was proposed to explain the oscillation of the lift-off position.     

等离子体对含硼两相流扩散燃烧特性的影响

为排除来流空气对含硼燃气的掺混效应, 研究等离子体对含硼富燃料推进剂在补燃室二次燃烧过程的影响, 建立了含硼两相流平行进气扩散燃烧物理模型. 利用高速摄影仪拍摄了含硼燃气在补燃室二次燃烧的火焰图像, 分析了该物理模型的扩散燃烧特性和硼颗粒的二次点火距离. 采用硼颗粒的King点火模型、有限速度/涡耗散模型、颗粒轨道模型和RNG k-ε模型以及等离子体模型, 模拟了一定条件下等离子体对含硼两相流扩散燃烧过程的影响. 结果表明, 依据含硼燃气二次燃烧图像得到的硼颗粒二次点火距离, 与数值模拟结果基本一致, 保证了该物理模型和计算方法的可靠性. 含硼两相流经过等离子体区域后, 硼颗粒在运动轨迹上颗粒温度明显增加, 颗粒直径明显减小, B₂O₃的质量分数分布区域明显扩增, 70%的硼颗粒在到达补燃室2/3尺寸前燃烧效率已达到100%, 硼颗粒充分燃烧释放出更多热量导致中心流线区域温度增加近1/2, 可见等离子体可以明显强化含硼两相流的燃烧过程, 提高硼颗粒的燃烧效率.     

Unstable combustion induced by oblique shock waves at the non-attaching condition of the oblique detonation wave

The instability of oblique shock wave (OSW) induced combustion is examined for a wedge with a flow turning angle greater than the maximum attach angle of the oblique detonation wave (ODW), where archival results rarely exist for this case in previous literatures. Numerical simulations were carried out for wedges of different length scales to account for the ratio of the chemical and fluid dynamic time scales. The results reveal three different regimes of combustion. (1) No ignition or decoupled combustion was observed if a fluid dynamic time is shorter than a chemical time behind an OSW. (2) Oscillatory combustion was observed behind an OSW if a fluid dynamic time is longer than a chemical time behind an OSW and the fluid dynamic time is shorter than the chemical time behind a normal shock wave (NSW) at the same Mach number. (3) Detached bow shock-induced combustion (or detached overdriven detonation wave) was observed if a fluid dynamic time is longer than a chemical time behind a NSW. Since no ignition or decoupled combustion occurs as a very slow reaction and the detached wave occurs as an infinitely fast reaction, the finite rate chemistry is considered to be the key for the oscillating combustion induced by an OSW over a wedge of a finite length with a flow turning angle greater than the maximum attach angle for an ODW. Since this case has not been previously reported, grid independency was tested intensively to account for the interaction between the shock and reaction waves and to determine the critical time scale where the oscillating combustion can be observed.     

Large eddy simulation of the low temperature ignition and combustion processes on spray flame with the linear eddy model

Large eddy simulation coupled with the linear eddy model (LEM) is employed for the simulation of n-heptane spray flames to investigate the low temperature ignition and combustion process in a constant-volume combustion vessel under diesel-engine relevant conditions. Parametric studies are performed to give a comprehensive understanding of the ignition processes. The non-reacting case is firstly carried out to validate the present model by comparing the predicted results with the experimental data from the Engine Combustion Network (ECN). Good agreements are observed in terms of liquid and vapour penetration length, as well as the mixture fraction distributions at different times and different axial locations. For the reacting cases, the flame index was introduced to distinguish between the premixed and non-premixed combustion. A reaction region (RR) parameter is used to investigate the ignition and combustion characteristics, and to distinguish the different combustion stages. Results show that the two-stage combustion process can be identified in spray flames, and different ignition positions in the mixture fraction versus RR space are well described at low and high initial ambient temperatures. At an initial condition of 850 K, the first-stage ignition is initiated at the fuel-lean region, followed by the reactions in fuel-rich regions. Then high-temperature reaction occurs mainly at the places with mixture concentration around stoichiometric mixture fraction. While at an initial temperature of 1000 K, the first-stage ignition occurs at the fuel-rich region first, then it moves towards fuel-richer region. Afterwards, the high-temperature reactions move back to the stoichiometric mixture fraction region. For all of the initial temperatures considered, high-temperature ignition kernels are initiated at the regions richer than stoichiometric mixture fraction. By increasing the initial ambient temperature, the high-temperature ignition kernels move towards richer mixture regions. And after the spray flames gets quasi-steady, most heat is released at the stoichiometric mixture fraction regions. In addition, combustion mode analysis based on key intermediate species illustrates three-mode combustion processes in diesel spray flames.     

Large-eddy simulations of transcritical injection and auto-ignition using diffuse-interface method and finite-rate chemistry

The need for improved engine efficiencies has motivated the development of high-pressure combustion systems, in which operating conditions achieve and exceed critical conditions. Associated with these conditions are strong variations in thermo-transport properties as the fluid undergoes mixing and phase transition, and two-stage ignition with low-temperature combustion. Accurately simulating these physical phenomena at real-fluid environments remains a challenge. This study examines a diffuse-interface method for simulating the injection and ignition of n-dodecane at transcritical conditions. To this end, a compressible solver with a real-fluid state equation and finite-rate chemistry is employed. Simulations of an ECN-relevant diesel-fuel injector are performed for both inert and reacting conditions. For the spray ignition, four specific operating points (corresponding to ambient temperatures between 900 K and 1200 K) are investigated to examine effects of the real-fluid environment and low-temperature chemistry. Comparisons with available experimental data demonstrate that the presented numerical method adequately captures the diesel fuel injection and auto-ignition processes under transcritical conditions.     

Experimental study and modeling of shock tube ignition delay times for hydrogen-oxygen-argon mixtures at low temperatures

Recent literature has indicated that experimental shock tube ignition delay times for hydrogen combustion at low-temperature conditions may deviate significantly from those predicted by current detailed kinetic models. The source of this difference is uncertain. In the current study, the effects of shock tube facility-dependent gasdynamics and localized pre-ignition energy release are explored by measuring and simulating hydrogen-oxygen ignition delay times. Shock tube hydrogen-oxygen ignition delay time data were taken behind reflected shock waves at temperatures between 908 to 1118 K and pressures between 3.0 and 3.7 atm for two test mixtures: 4% H₂, 2% O₂, balance Ar, and 15% H₂, 18% O₂, balance Ar. The experimental ignition delay times at temperatures below 980 K are found to be shorter than those predicted by current mechanisms when the normal idealized constant volume (V) and internal energy (E) assumptions are employed. However, if non-ideal effects associated with facility performance and energy release are included in the modeling (using CHEMSHOCK, a new model which couples the experimental pressure trace with the constant V, E assumptions), the predicted ignition times more closely follow the experimental data. Applying the new CHEMSHOCK model to current experimental data allows refinement of the reaction rate for H + O₂ + Ar ↔ HO₂ + Ar, a key reaction in determining the hydrogen-oxygen ignition delay time in the low-temperature region.     

Effect of steam on the single particle ignition of solid fuels in a drop tube furnace under air and simulated oxy-fuel conditions

This article investigates the effect of steam on the ignition of single particles of solid fuels in a drop tube furnace under air and simulated oxy-fuel conditions. Three solid fuels, all in the size range 125–150 µm, were used in this study; specifically, a low rank sub-bituminous Colombian coal, a low-rank/high-ash sub-bituminous Brazilian coal and a charcoal residue from black acacia. For each solid fuel, particles were burned at a constant drop tube furnace wall temperature of 1475?K, in six different mixtures of O₂/N₂/CO₂/H₂O, which allowed simulating dry and wet conventional and oxy-fuel combustion conditions. A high-speed camera was used to record the ignition process and the collected images were treated to characterize the ignition mode (either gas-phase or surface mode) and to calculate the ignition delay times. The Colombian coal particles ignite predominately in the gas-phase for all test conditions, but under simulated oxy-fuel conditions there is a decrease in the occurrence of this ignition mode; the charcoal particles experience surface ignition regardless of the test condition; and the Brazilian coal particles ignite predominately in the gas-phase when combustion occurs in mixtures of O₂/N₂/H₂O, but under simulated oxy-fuel conditions the ignition occurs predominantly on the surface. The ignition delay times for particles that ignited in the gas-phase are smaller than those that ignited on the surface, and generally the simulated oxy-fuel conditions retard the onset of both gas-phase and surface ignition. The addition of steam decreases the gas-phase and surface ignition delay times of the particles of both coals under simulated oxy-fuel conditions, but has a small impact on the gas-phase ignition delay times when the combustion occurs in mixtures of O₂/N₂/H₂O. The steam gasification reaction is likely to be responsible for the steam effect on the ignition delay times through the production of highly flammable species that promote the onset of ignition.     

An assessment of large eddy simulations of premixed flames propagating past repeated obstacles

This paper presents an assessment of Large Eddy Simulations (LES) in calculating the structure of turbulent premixed flames propagating past solid obstacles. One objective of the present study is to evaluate the LES simulations and identify the drawbacks in accounting the chemical reaction rate. Another objective is to analyse the flame structure and to calculate flame speed, generated overpressure at different time intervals following ignition of a stoichiometric propane/air mixture. The combustion chamber has built-in repeated solid obstructions to enhance the turbulence level and hence increase the flame propagating speed. Various numerical tests have also been carried out to determine the regimes of combustion at different stages of the flame propagation. These have been identified from the calculated results for the flow and flame characteristic parameters. It is found that the flame lies within the ‘thin reaction zone’ regime which supports the use of the laminar flamelet approach for modelling turbulent premixed flames. A submodel to calculate the model coefficient in the algebraic flame surface density model is implemented and examined. It is found that the LES predictions are slightly improved owing to the calculation of model coefficient by using submodel. Results are presented and discussed in this paper are for the flame structure, position, speed, generated pressure and the regimes of combustion during all stages of flame propagation from ignition to venting. The calculated results are validated against available experimental data.     

Detailed and simplified kinetic models of n-dodecane oxidation: The role of fuel cracking in aliphatic hydrocarbon combustion

A detailed kinetic model is proposed for the combustion of normal alkanes up to n-dodecane above 850 K. The model was validated against experimental data, including fuel pyrolysis in plug flow and jet-stirred reactors, laminar flame speeds, and ignition delay times behind reflected shock waves, with n-dodecane being the emphasis. Analysis of the computational results reveal that for a wide range of combustion conditions, the kinetics of fuel cracking to form smaller molecular fragments is fast and may be decoupled from the oxidation kinetics of the fragments. Subsequently, a simplified model containing a minimal set of 4 species and 20 reaction steps was developed to predict the fuel pyrolysis rate and product distribution. Combined with the base C₁-C₄ model, the simplified model predicts fuel pyrolysis rate and product distribution, laminar flame speeds, and ignition delays as close as the detailed reaction model.