硼烷合乙二胺的点火、燃烧及热解特性

为探索高氢含量硼烷合乙二胺储氢材料在空气中的燃烧性能,使用气相合成方法制备了硼烷合乙二胺(EDAB)微米颗粒。通过连续激光点火实验,测试了其点火和燃烧参数;通过在氮气和空气中的热解实验,研究了其燃烧过程机理。结果表明,硼烷合乙二胺的燃烧具有点火延迟时间短、点火能量低的特点,在常温常压静止空气流中,点火功率密度为10~9 W/m~2量级时,微米级硼烷合乙二胺的点火延迟时间为0.000 2~0.000 9s,最小点火能量仅0.000 1J;其连续激光点火燃烧过程分为两个阶段,分别产生亮蓝色与黄色火焰。结合材料在氮气及空气中的热解行为,推测该材料燃烧第1阶段蓝色火焰对应其热解释放氢气的燃烧,第2阶段的黄色火焰对应其骨架高温裂解所生成挥发物的燃烧。     

旋转流中预混合火焰高速传播现象—II.点火位置与燃烧过程

在前期关于Vortex-bursting旋流式预混燃烧器的燃烧效率及其进口混合气速度分布对燃烧效率的影响实验基础上,围绕燃烧器的点火特性,对旋流场中的点火位置和稳定火焰形成进行了数值分析.结果表明,不适当的点火位置会影响稳定火焰的形成,在相同的燃烧工况下,在流场中点火位置不同,火焰的发展出现不同的趋势.在靠近中心轴附近的低速区点火时,火焰能够稳定;在靠近管壁的高速区点火时,撤离点火源后,火焰吹熄.本结果对于强化预混合燃烧的稳定性具有理论和工程指导意义.     

旋转流中预混合火焰高速传播现象-II. 点火位置与燃烧过程

在前期关于Vortex-bursting旋流式预混燃烧器的燃烧效率及其进口混合气速度分布对燃烧效率的影响实验基础上，围绕燃烧器的点火特性，对旋流场中的点火位置和稳定火焰形成进行了数值分析. 结果表明，不适当的点火位置会影响稳定火焰的形成，在相同的燃烧工况下，在流场中点火位置不同，火焰的发展出现不同的趋势. 在靠近中心轴附近的低速区点火时，火焰能够稳定；在靠近管壁的高速区点火时，撤离点火源后，火焰吹熄. 本结果对于强化预混合燃烧的稳定性具有理论和工程指导意义.     

Premixed filtration combustion of micron and sub-micron particles in inert porous media: A theoretical analysis

An analytical model for one-dimensional premixed filtration combustion of volatile fuel particles-air mixture is presented. It is presumed that fuel particles first vaporize and a gaseous fuel with definite chemical structure is formed, which is subsequently oxidized in the gas phase. Flame structure is considered in the three zones. In the preheating vaporization zone, the mixture is heated until it reaches ignition temperature. In the reaction zone, the combustible mixture burns and the post flame zone is occupied by the combustion products. The temperature and mass fraction profiles are obtained of gaseous fuel in these three zones at a semi-infinite inert porous media. Thereafter, the effects of various parameters such as gas velocity, porosity, fuel particles diameter, number density of fuel particles, and heat of chemical reaction on the temperature and mass fraction profiles are investigated.     

Flame “blow-back” in the combustion of premixed gases in flow-through systems

Conclusions In the pulsating combustion of premixed mixtures the flame may be blown back from the combustion chamber into the mixing zone at velocities exceeding the flash-back velocity by more than an order. The chief factor in the determination of flame blow-back is the amplitude of the pressure pulsation, whose value depends on the combustion chamber dimensions, flow velocity, the temperature and composition of the mixture, and the resistance of the combustion chamber outlet system.Fizika Goreniya i Vzryva, Vo. 4, No. 2, pp. 209–214, 1968     

Inertial effects in nonstationary models of flame front evolution

The objective of the present study is to formulate flame front evolution models capturing the effects of flame extinction, ignition, and oscillations in addition to the conventional regime of flame propagation. The basic equations constituting the one-dimensional thermodiffusion model of combustion are reduced to a system of two ordinary differential equations for the flame front coordinate and flame temperature. These equations admit solutions that describe, for example, ignition, extinction, and nonlinear oscillations of the flame, which are observed during premixed gas combustion in microchannels with an elevated wall temperature or during gasless combustion of condensed systems. Similarity of the basic thermodiffusion models assuming an in-finitely small thickness of the chemical reaction zone allows application of a universal method to derive reduced equations in physically different systems. It is demonstrated that modeling of flame oscillations requires at least considering effects associated with flame acceleration (flame front “inertia”) and the rate of flame temperature variation. The accuracy of the proposed model with inertial effects is checked by results of direct numerical simulations of the original equations.     

Burning Phenomena of the Gun Propellant JA2

The combustion phenomena of the standard gun propellant JA2 are investigated in experiments and analyzed by a simplified theoretical model. Hereby energy transfer from the gas phase governs ignition and combustion of solid rocket and gun propellants. In addition to the heat conduction and convection, the radiation of the flame contributes to the heat feedback which controls the burning rate in dependence on pressure. The dependence on the initial temperature is given by physical parameters of the conversion from the solid to the gaseous state. Burning rates are measured in dependence on pressure and initial temperature confirming a simplified law for the burning rate. The evaluation yields that the pressure exponent can be directly assigned to the heat feedback and that the temperature of the conversion from the condensed to the gas phase lies at about 675 K. The experiments also comprise spectroscopic measurements at low pressures in the wavelength ranges from 300 nm to 14000 nm which are resolved spatially along the vertical flame profile. The analysis of the spectra delivers the profiles of species in the flames including di‐atomic radicals and tri‐atomic molecules of the final combustion products. In addition, gas phase temperatures are derived by application of the Single‐Line‐Group model which gives approximately 2800 K closely below the adiabatic flame temperature of 2900 K at low pressures. They are compared to temperatures assigned to soot particle emission. In summary, these data enable an estimation of the heat feedback from the flame to the burning surface.     

Effect of biofuels combustion on the nanoparticle and emission characteristics of a common-rail DI diesel engine

This study was performed to investigate the effect of biogas-biodiesel fuel combustion on the emissions reduction and nanoparticle characteristics in a direct injection (DI) diesel engine. In order to apply the two biofuels, biogas was injected into a premixed chamber during the intake process by using two electronically controlled gas injectors, and biodiesel fuel was directly injected into combustion chamber by a high-pressure injection system. The in-cylinder pressure and rate of heat release (ROHR) were investigated under various fuel conditions for single-fuel (biodiesel) and dual-fuel (biogas-biodiesel) combustions. To evaluate the engine performances and exhaust emissions characteristics, the indicated mean effective pressure (IMEP) and exhaust emissions were also investigated under various test conditions. Furthermore, the particle number concentration and the size distribution of nanoparticles were analyzed by using a scanning mobility particle sizer (SMPS).In the case of dual-fuels, the peak combustion pressure and ROHR were gradually decreased with the increase of the biogas fraction in the dual-fuels. As the premixed ratios increased, ignition delay and combustion durations were prolonged compared to single-fuel mode. The dual-fuels combustion showed that the IMEP decreased slightly and maintained similar levels up to 20° BTDC due to the retarded combustion phase. The concentrations of NO_x emissions were decreased for all injection timings as the premixed ratio (r_p) increased. The soot emissions in dual-fuel operations were significantly lower than those in the single-fuel mode (r_p = 0), and decreased gradually as the premixed ratio increased, regardless of injection timing. A lower nanoparticle size distribution was observed at all premixed ratios for dual-fuel combustion compared to those of the single fuel mode. The number distribution of both nuclei and accumulation modes also decreased with an increase in the biogas fraction. A slight reduction in the total particle number and total volume for all premixed ratios was observed as the injection timing increased from TDC up to 20° BTDC.     

Numerical Simulation of Quenched Combustion Model for AP/HTPB Propellant under Transient Depressurization

In order to study the out‐of‐phase blowing effect of ammonium perchlorate/hydroxyl terminated polybutadiene (AP/HTPB) under transient depressurization, a two‐dimensional periodic sandwich model of AP/HTPB sandwich unsteady combustion was established. The gas‐solid two‐step total reaction was used to couple the gas‐solid boundary layer, and the AP/HTPB step‐down temperature criterion was applied. The numerical simulation comparative analysis under the initial combustion pressure 3.5 MPa∼10 MPa and the initial depressurization rate of 1000 MPa/s∼2000 MPa/s was experimented. The results show that under the condition of initial combustion pressure of 3.5 MPa and pressure reduction rate of 1000 MPa/s, the formation of narrow diffusion chemical reaction zone appears in the initial stage of depressurization; when the combustion pressure drops to about 1.7 MPa, the flame appears dual characteristics: diffusion and premixed combustion; when the pressure dropped to 0.1 MPa, the flame is premixed combustion. AP(g) is the main factor causing the out‐of‐phase blowing effect. During the initial stage of combustion, AP(g) decomposes rapidly and its decomposition product is close to the combustion surface; with the rapid decrease of pressure, the gas‐phase heat feedback decreases, leading to the decrease of AP(g) decomposition rate and AP(g) diffusion to the gas phase, which is the initial phase of out‐of‐phase blowing effect; when the gas phase heat feedback reduced and the temperature is below 750 K, the decomposition of AP(g) is stopped and the undecomposed AP(g) is further diffused to the gas phase region, which exacerbates the out‐of‐phase blowing effect, leading to the extinguishment of AP/HTPB. The unsteady combustion flame extinction time increases with the initial combustion pressure, and decreases with the initial depressurization rate.     

点火源位置对甲烷-空气爆燃超压特征的影响

开展了化学恰当比φ = 1甲烷-空气预混气在透明方形管道内的爆燃实验研究,改变点火源位置,分析在管道一端闭口一端开口条件下,点火源位置对甲烷-空气预混气爆燃超压特征的影响。实验结果表明:当点火源与闭口端之间距离较小时,时间-超压曲线不发生振荡,随着点火源相对于闭口端距离的增加,超压分别呈微弱等幅振荡、振幅指数增长的振荡,且最大超压峰值随之增加;超压波形与火焰瞬态结构存在密切关联,振荡波形超压峰值的极值点总是位于火焰位置的极值点;当超压发生振荡时,振幅指数增长阶段的振荡周期随时间线性减小,振荡周期与未燃气气柱长度呈现较好相关性;超压振荡的原因在于,泄爆口侧的火焰前沿触发了超压振荡,闭口侧火焰前沿与声波(压力波)在未燃气气柱中相互作用放大了超压振荡。     

Experimental Study of Ignition of a Gasoline–Air Mixture in a Constant‐Volume Combustion Chamber

The characteristics of flamekernel development in a premixed gasoline–air mixture in a cylindrical constantvolume combustion chamber are measured. The experiments are performed with an initial temperature of 393 K, pressure of 6 bar, and equivalence ratio = 0.8 with the use of various ignition systems and spark plugs. The schlieren pictures of the process are presented, and the measured results for flame velocity, heatrelease rate, and mass fraction of the burnt fuel are analyzed.     

Numerical simulation of oxy-coal combustion for a swirl burner with EDC model简

The characteristics of oxy-coal combustion for a swirl burner with a specially designed preheating chamber are studied numerically. In order to increase the accuracy in the prediction of flame temperature and igni- tion position, eddy dissipation concept （EDC） model with a skeletal chemical reaction mechanism was adopted to describe the combustion of volatile matter. Simulation was conducted under six oxidant stream conditions with dif- ferent OjN2/CO2 molar ratios： 21/79/0, 30/70/0, 50/50/0, 21/0/79, 30/0/70 and 50/0/50. Results showed that 02 en- richment in the primary oxidant stream is in favor of combustion stabilization, acceleration of ignition and increase of maximum flame temperature, while the full substitution of N2 by CO2 in the oxidant stream delays ignition and decreases the maximum flame temperature. However, the overall flow field and flame shapes in these cases are very similar at the same flow rate of the primary oxidant stream. Combustion characteristics of the air-coal is similar to that of the oxy-coal with 30% 02 and 70% CO2 in the oxidant stream, indicating that the rear condition is suitable for retrofitting an air-coal fired boiler to an oxy-coal one. The swirl burner with a specially designed preheating chamber can increase flame temperature, accelerate ignition and enhance burning intensity of pulverized coal under oxy-coal combustion. Also, qualitative experimental validation indicated the burner can reduce the overall NOx emission under certain 02 enrichment and oxy-coal combustion conditions against the air-coal combustion.     

含氨燃料预混火焰的层流火焰速度及NO排放特性

将甲烷或氢气与氨气共燃可以克服NH₃火焰的点火能量高、燃烧速度慢的缺点。为了解NH₃作为燃料的燃烧特性,对含NH₃燃料进行一维层流预混火焰数值模拟,研究其层流火焰速度及NO排放特性。采用文献中5个简化反应机理进行数值计算,发现Okafor机理模拟NH₃/CH₄/air火焰精度更高;Xiao机理模拟NH₃/H₂/air、NH₃/air精度适中,计算时间较短。此外,开展了当量比、燃料混合物组分比例、压力等参数对含NH₃燃料燃烧时烟气中NO浓度影响的研究。研究发现：含NH₃燃料燃烧时NO主要通过OH、H、O自由基和O₂分子的消耗而生成,主要通过与NH_i（i=0, 1, 2）自由基反应消耗;含NH₃燃料在富燃状态下燃烧可有效减少NO排放,但富燃燃烧效率低,可采用富燃-贫燃分级燃烧技术来提高燃烧效率,同时保持NO的低排放;掺有较多NH₃的含NH₃燃料在中高压下燃烧时可有效减少NO排放。     

Ignition and Combustion of Aluminum–Air Suspensions in a Reactor for High-Temperature Synthesis of Alumina Powder

A method for flame stabilization in a reactor for synthesis of metal oxides is developed by analyzing combustion of dispersions of metal powders. An experimental reactor designed to implement this method is described. Ignition and combustion of commercial aluminum powders (ASD-1 and ASD-4) in air were studied, and their reliable ignition and stable combustion in the reactor combustion chamber were confirmed. It is shown that efficient combustion of an aluminum–air mixture depends on powder dispersity, flow mixing conditions, and combustion chamber pressure. Key words: aluminum, powder, suspension, flame, stabilization, combustion, synthesis, oxide.     

Ignition and combustion of pyrotechnic compositions based on micro- and nanoparticles of aluminum diboride in air flow in a two-zone combustion chamber

This paper presents the experimental study of ignition and combustion of micro- and nanoparticles of aluminum diboride as part of pyrotechnic energy-saturated compositions in a gas generator with an air afterburner chamber and the thermodynamic calculations of combustion of pyrotechnic compositions based on aluminum diboride in air. The discharge of the combustion products from the afterburner chamber is recorded on video. It is shown that replacing micron aluminum diboride by powdered diboride with a mass-average diameter of particles equal to ≈270 nm in the pyrotechnic composition and increasing the pressure in the afterburner chamber cause the combustion efficiency in air to increase by 5–20%.     

Ignition and combustion of a hydrogen-air mixture in a rapid-compression combustor

In a rapid-compression combustor with a freely moving piston, the efficiency of thermomechanical conversion of energy was determined in the detonation combustion regime of a stoichiometric hydrogen-air mixture under conditions close to those observed during operation of a piston engine of internal combustion in the starting regime. It is shown that this regime of heat release is characterized not only by a dramatic pressure increase in the combustion chamber, but also by its subsequent rapid decrease caused by heat transfer to the cylinder walls and partial condensation of water vapors. The intensity of these components of the thermal process depends progressively on the pressure and temperature of the combustion products, which, in turn, depend on the parameters of the mixture immediately before its ignition. However, the relative increase in combustion pressure turns out to be minimum when the ignition is initiated near the top dead center. It is also shown that the coefficient of thermomechanical conversion of energy (an analog of the indicated efficiency of an internal combustion engine) reaches the maximum value of 31% if the mixture is ignited at a time of approximately 3/4 of a period of oscillations of the piston group after the beginning of compression of an air charge. Translated fromFizika Goreniya i Vzryva, Vol. 35, No. 6, pp. 3–14, November–December 1999.     

新型高能叠氮硝胺发射药高压燃烧稳定性研究

为了研究高能发射药膛内燃烧规律,通过半溶剂法制备了一种火药力高达1240J/g的新型高能叠氮硝胺发射药(ADR),采用高压密闭爆发器和30mm高压模拟试验装置,分别研究了不同温度下ADR发射药定容高压燃烧性能和装填密度、温度以及石墨光泽处理对ADR发射药膛内高压燃烧稳定性的影响。结果表明,不同温度条件下(-40、20和50℃)ADR发射药静态及动态燃烧性能稳定性良好,燃烧过程无异常;随着温度的增加,ADR发射药点火性能提高,增加了膛内燃烧稳定性;装填密度0.48~0.64g/cm³范围内,随着装填密度的增加,ADR发射药膛内压力波强度逐渐增加,但增长幅度减小;对发射药进行石墨光泽处理,增加了ADR发射药起始缓燃效果,使不同温度下膛内压力波强度明显降低;与RGD7发射药相比,ADR发射药火药力较高,爆温较低,发射装药膛内高压燃烧稳定性相当,在高膛压环境中应用前景较好。     

Emissions and wall temperatures for lean prevaporized premixed gas turbine combustor

Experimental studies are carried out for investigating emission and wall temperature for traditional gas turbine combustor converted to lean premixed prevaporized (LPP) combustor. Vortex chamber, air preheating system, flat flame burner and inlet temperature control system are designed. Vortex chamber was maintained at the main air inlet port for controlling secondary air flow rate and wall temperature. Kerosene/air mixture temperature at exit from burner and entering combustion chamber was kept constant at 650 K for all runs. Special considerations were given for measuring NO_X, UHC, CO, local A/F ratio, flame temperature, exhaust gases temperature and wall temperature. For swirl and non swirl cases, secondary air ratio and primary zone air/fuel ratio were varied. The different operating parameters affecting flame temperature through it is affecting on local A/F ratio which is the main parameter for controlling flame temperature, emissions and walls temperatures. Flat flame burner and vortex chamber are useful tools for reducing emission and controlling walls temperatures. The inner liner wall temperatures are more affected by primary zone equivalence ratio while the outer liner wall temperatures are more affected by secondary air flow rate. Semi empirical correlations for NO_X, UHC and CO concentrations, exhaust gases temperature and maximum inner liner wall temperature are carried out. Good agreement between the measured and the calculated results are obtained. The present results are useful for further development of the traditional gas turbine combustor converted to LPP combustor.     

Numerical simulation of the combustion of hydrogen-air mixture in micro-scaled chambers. Part I: Fundamental study

Understanding of micro-scale combustion mechanism is very essential to the development of combustion-based micro-power devices, which may supply much higher energy density than the batteries used nowadays. In part I of this paper, Computational Fluid Dynamics (CFD)-based numerical simulations have been performed to study the combustion of premixed hydrogen-air mixture in a series of chambers with same shape aspect ratio but various dimensions from millimetre to micron level. The transition of the combustion phenomena in the chambers from relatively large scale to micro-scale has been studied numerically to investigate the micro-combustion mechanism. The combustion model of premixed hydrogen-air mixture represents the detailed reaction mechanism with 19 reversible elementary reactions and nine species. The effect of various heat transfer conditions at chamber wall, e.g. adiabatic wall, with heat loss and heat conduction within the wall, on the combustion is analysed. These thermal conditions have strong effects on the combustion especially when the chamber dimension goes smaller and the ratio of surface area to volume becomes larger. Both factors, such as larger heat loss through the chamber wall and smaller chamber dimension size, may lead to the thermal quenching of micro-scale combustion. The simulation results also indicate that the stable combustion in a micro-scaled chamber may be sustained through increasing the ratio of flow residence time in chamber to chemical reaction time, and maintaining proper thermal condition. In part II of this paper, the numerical modelling method developed here is applied to analyse the micro-combustion characteristics in a three-dimensional micro-combustor based on the prototype developed by the MIT group for a micro gas turbine engine.