替代燃料二甲醚的燃烧特性及其污染物甲醛的生成消耗机理研究

化石燃料的不可再生性决定了其不能长久为全球经济和科技的发展提供能源动力，从可持续发展和能源战略的角度考虑，能够替代石油及其衍生品的清洁替代燃料研究已经成为提高能源供应安全、改善环境污染问题、应对气候变化的重要措施，对替代燃料的研究和应用已经成为各方关注和开发的热点。 二甲醚(DME、CH3OCH3)是一种最简单的醚类，它不含C-C健，可以由天然气、煤、生物质燃料等大量制备，而且具有较高的辛烷值(55-60)，较低的碳氢化合物、CO排放，没有PM排放，因而被认为是一种非常有发展前景的发动机替代燃料，已经受到了广泛的关注。但是，在发动机燃用DME的实验研究表明，在其排气中有非常规污染物甲醛(HCHO)、乙醛(CH3CHO)，甲酸甲酯(HCOOCH3)等排放，这些有机污染物会对环境和人类健康产生严重的危害，在环保要求日益严格的趋势下，这就制约了二甲醚的规模化应用。因此，对二甲醚燃烧性能、氧化中间产物甲醛等的产生和排放机理、相关污染物抑制技术需要进行着重研究，这对二甲醚燃料规模化应用、相关二甲醚燃烧器设计、燃烧性能的优化以及污染物控制技术的研究等都有着重要的理论指导意义和参考价值。 为了充分理解二甲醚燃料的燃烧特性、非常规污染物甲醛的产生和消耗机理，本文以实验和二甲醚化学反应动力学机理为指导，对二甲醚预混燃烧的燃烧特性、相关污染物和甲醛产生和消耗的机理做了详细的研究；并针对二甲醚燃料的不同应用背景，对二甲醚燃料低温下的氧化和甲醛生成特性、DME与LPG掺混燃烧特性和甲醛生成消耗机理进行了深入的研究，具体工作有： 研究了二甲醚预混燃烧特性、火焰中甲醛等污染物的产生特性，建立了火焰中甲醛取样、测量的方法和实验平台。并对当量比和燃料流量对二甲醚预混燃烧的燃烧特性、甲醛生成特性影响进行了考察，实验结果表明二甲醚是一种优良的替代燃料，在二甲醚火焰中甲醛是其重要的中间产物，甲醛浓度分布与当量比和预混气流速密切相关。当量比一定时，随着预混气流速的增加，火焰中甲醛产生的范围变窄，且甲醛浓度峰值逐渐移向燃烧器出口，而甲醛产生的浓度峰值数值上相差不大，甲醛在形成峰值后被快速消耗，其浓度在0.1mm内下降到几乎为零；在二甲醚流量一定时，随着当量比的增加，火焰中产生了更多的甲醛，火焰中甲醛分布的范围也变宽，而且当量比越大，甲醛的消耗也变缓，在当量比为0.8时，甲醛浓度从峰值到被消耗距离变为2mm，远大于当量比0.6和0.7下0.1mm的消耗距离。 对二甲醚预混燃烧进行数值研究和化学动力反应机理分析后发现，在二甲醚燃烧中，二甲醚的氧化反应途径主要是通过脱氢生成CH3OCH2和在高温下的直接裂解反应而进行，其中脱氢反应是低温下二甲醚消耗的主要途径，而在高温反应阶段(T>1000K)，DME的直接裂解和燃料的脱氢反应共同起主导作用；非常规污染物甲醛通过DME脱氢产物CH3OCH2的裂解和外部氧化而生成，在高温时通过DME直接裂解后被氧化产生；甲醛的消耗反应则是通过与H、O、OH和CH3基的氧化反应而完成，其中与O、OH基的反应在燃烧中起主要作用。因此二甲醚燃烧中甲醛的抑制关键在燃烧中甲醛的消耗阶段，采取有效的技术措施，如优化燃烧器结构提高二甲醚燃烧室内的温度、在燃烧区保证充足的氧气供应等措施，加快甲醛的消耗速度以促进其被完全氧化，可以实现二甲醚燃烧中甲醛的零排放。 针对柴油发动机燃用DME燃料时，燃料在燃烧室停留时间过短，造成部分未燃二甲醚随尾气排放，对DME在低温下(<800K)的氧化特性和甲醛生成特性进行了实验研究。结果表明，二甲醚在200℃左右就开始发生氧化反应，在200~400℃温度范围内被氧化而生成大量中间产物甲醛，且在此温度范围内甲醛不易被氧化分解，而发动机尾气温度（一般在200~600℃之间）处于甲醛最易生成的范围，因此未燃二甲醚在尾气中发生低温氧化反应生成的甲醛，是发动机燃用DME而排放高浓度甲醛的重要来源。研究结论为柴油发动机燃用DME抑制非常规污染物甲醛的排放提供了新的参考。 DME作为替代燃料，部分替代及与其他石化系燃料掺混燃烧是目前的重要应用方向，对DME与LPG掺混燃烧特性和甲醛生成特性进行了实验研究，结果表明，在DME与LPG掺混燃烧中，固定当量比和燃料质量流量的条件下，两种燃料存在一个最佳掺混比，在此掺混比例下，混合燃料着火提前，燃料燃烧性能最佳；DME与LPG混合燃料中，二甲醚是燃烧中甲醛产生的主要来源，控制DME的完全氧化和燃烧是抑制DME与LPG掺混燃烧排放甲醛的主要途径，这为更好地应用DME与LPG混合燃料提供了参考。 能否清洁高效燃烧是决定替代燃料DME应用规模和途径中的关键任务，本文对DME燃烧特性、非常规污染物甲醛的生成排放特性、低温下DME的氧化特性、DME与LPG掺混燃烧特性的研究，从不用的应用方向和领域对DME清洁高效燃烧进行了探讨和研究，研究成果可以为清洁高效利用二甲醚、抑制甲醛排放，以及开发相关燃烧技术、燃烧器提供实验依据和理论指导。本文在DME燃烧特性和非常规污染物甲醛的产生与排放方面取得了具有创新性的研究结果。

Experimental studies on self-ignition of hydrogen/air supersonic combustion

Self-ignition tests of a model scramjet combustor were conducted by using parallel sonic injection of gaseous hydrogen from the base of a blade-like strut into a supersonic airstream, The vitiated air was produced by burning H-2, O-2, and air to a stagnation temperature of 1000-2100 K and a stagnation pressure of 0.8-1.6 MPa, The effects of different parameters on the self-ignition limits were analyzed, In addition, the effects of the combustor's different wall configurations on self-ignition limits were specifically studied. It was found that the wall configurations of the combustor had a significant effect on self-ignition limits, which might have variations of 420-840 K deg in stagnation temperature; however, the local static temperature in the recirculation zones for different wall configurations remained the same at approximately 1100 K, It was found that self-ignition could initiate at the exit of the combustor and this can be considered as a weak self-ignition characteristic.

Coflow jets with large velocity difference - a new aerodynamic principle of flame stabilization and combustion intensification

A new aerodynamic principle of flame stabilization and combustion intensification, the coflow jets with large velocity difference, is described. One or more small high-velocity jets of air or steam, injected off the axis and in the same direction as the low-velocity main fuel-air flow into the combustor, create a large recirculation zone of high turbulence intensity in which the combustibles and high temperature gases are effectively mixed, so that stable and intensive combustion can be maintained even for fuels with poor ignition. A pulverized coal combustor based on the principle mentioned above is shown to be characteristic of excellent combustoom and a simple structure. A number of precombustors of this type are in operation at some power stations and industrial boilers of China. Using such precombustor, successtul startups and part-load operation of the boilers have become available under conditions of unpreheated air and low-grade coal with volatiles as low as 15% and ash content as high as 30%. This principle shows good promise as an attractive new technology of combustion.

Characteristic Dimensionless Numbers in Multi-Scale and Rate-Dependent Processes

For this sake, the macroscopic equations of mechanics and the kinetic equations of the microstructural transformations should form a unified set that be solved simultaneously. As a case study of coupling length and time scales, the trans-scale formulation

Investigation of kerosene combustion characteristics with pilot hydrogen in model supersonic combustors

Experimental investigations on the ignition and combustion stabilization of kerosene with pilot hydrogen in Mach 2.5 airflows were conducted using two test combustors, with cross sections of 30.5 x 30 and 51 x 70 mm, respectively. Various integrated modules, including the combinations of different pilot injection schemes and recessed cavity flameholders with different geometries, were designed and tested. The stagnation pressure of vitiated air varied within the range of 1.1-1.8 NiPa, while the stagnation temperature varied from 1500 to 1900 K. Specifically, effects of the pilot hydrogen injection scheme, cavity geometry, and combustor scaling on the minimally required pilot hydrogen equivalence ratio were systematically examined. Results indicated that the cavity depth and length had significant effects on the ignition and flameholding, whereas the slanted angle of the aft wall was relatively less important. Two cavities in tandem were shown to be a more effective flameholding mechanism than that with a single cavity. The minimally required pilot hydrogen equivalence ratio for kerosene ignition and stable combustion was found to be as low as 0.02. Furthermore, combustion efficiency of 80% was demonstrated to be achievable for kerosene with the simultaneous use of pilot hydrogen and a recessed cavity to promote the ignition and global burning.

Study of Gas Combustion in a Vented Cylindrical Vessel

Complicated interaction of a flame front with a turbulent flow induced by venting is studied during combustion of the stoichiometric propane/air mixture in a relatively large vented cylindrical vessel. Flame position, its shape, and combustion pressure were measured as a function of time and vent parameters. The experimental data were used to verify numerical simulation of the combustion process. The proposed numerical model satisfactorily simulates the main features of combustion in a closed and vented vessel such as flame configuration, flow and temperature fields, and pressure variation pattern. Simulated velocity and temperature distribution are very useful pieces of information because they are not available from experiments.

Numerical Simulation of Nox Formation in Coal Combustion with Inlet Natural Gas Burning

A full two-fluid model of reacting gas-particle flows and coal combustion is used to simulate coal combustion with and without inlet natural gas added in the inlet. The simulation results for the case without natural gas burning is in fair agreement with the experimental results reported in references. The simulation results of different natural gas adding positions indicate that the natural gas burning can form lean oxygen combustion enviroment at the combustor inlet region and the NOz concentration is reduced. The same result can be obtained from chemical equilibrium analysis.

Oxyhydrogen combustion and detonation driven shock tube

The performance of combustion driver ignited by multi-spark plugs distributed along axial direction has been analysed and tested. An improved ignition method with three circumferential equidistributed ignitors at main diaphragm has been presented, by which the produced incident shock waves have higher repeatability, and better steadiness in the pressure, temperature and velocity fields of flow behind the incident shock, and thus meets the requirements of aerodynamic experiment. The attachment of a damping section at the end of the driver can eliminate the high reflection pressure produced by detonation wave, and the backward detonation driver can be employed to generate high enthalpy and high density test flow. The incident shock wave produced by this method is well repeated and with weak attenuation. The reflection wave caused by the contracted section at the main diaphragm will weaken the unfavorable effect of rarefaction wave behind the detonation wave, which indicates that the forward detonation driver can be applied in the practice. For incident shock wave of identical strength, the initial pressure of the forward detonation driver is about 1 order of magnitude lower than that of backward detonation.

An Experimental Study of Kerosene Combustion in a Supersonic Model Combustor Using Effervescent Atomization

Investigation of kerosene combustion in a Mach 2.5 flow was carried out using a model supersonic combustor with cross-section area of 51 mm × 70 mm and different integrated fuel injector/flameholder cavity modules. Experiments with pure liquid atomization and with effervescent atomization were characterized and compared. Direct photography, Schlieren imaging, and planar laser induced fluorescence (PLIF) imaging of OH radical were utilized to examine the cavity characteristics and spray structure. Schlieren images illustrate the effectiveness of gas barbotage in facilitating atomization and the importance of secondary atomization when kerosene sprays interacting with a supersonic crossflow. OH PLIF images further substantiate our previous finding that there exists a local high-temperature radical pool within the cavity flameholder, and this radical pool plays a crucial role in promoting kerosene combustion in a supersonic combustor. Under the same operation conditions, comparison of the measured static pressure distributions along the combustor also shows that effervescent atomization generally leads to better combustion performance than the use of pure liquid atomization. Furthermore, the present results demonstrate that the cavity characteristics can be different in non-reacting and reacting supersonic flows. As such, the conventional definition of cavity characteristics based on non-reacting flows needs to be revised.

Effects of the Spanwise Characteristic Length on the Transition Feature in the Wake of a Cylinder

The transition features of the wake behind a uniform circular cylinder at Re = 200, which is just beyond the critical Reynolds number of 3-D transition, are investigated in detail by direct numerical simulations of 3-D incompressible Navier-Stokes equations. The spanwise characteris-tic length determines the transition features and global properties of the wake.

A Study on the Microstructure Characteristic of the Cold-Rolled Deformed Nanocrystalline Nickel

In this paper the microstructure characteristic of the cold-rolled deformed nanocrystalline Nickel metal has been studied by transmission electron microscopy (TEM). The results show that there were step structures near by grain boundary (GB), and the contrast of stress field in front of the step corresponds to the step in the shape. It indicates that the interaction between twins and dislocations is not a necessary condition to realizing the deformation. In the later stage of the deformation when the grain size became about 100 nm, the deformation occurs only depend upon the moving of the boundary of the stack faults (SFs) which result from the imperfection dislocations emitted from GBs. In the other word, the movement of the boundary dislocations of SFs results to growing-up of the size of the SFs, therefore realizes deformation. However, when the size of stack faults grows up, the local internal stress which is in front of the step gradually becomes higher. When this stress reach a critical value stopping the gliding of the partial dislocations, the SFs will stop growing up and leave a step structure behind.

Pulverized-coal combustion in Wall-Protecting-Jets combustor (WPJC)

A new type of pulverized-coal combustor, called "Wall-Protecting-Jets Combustor" (hereafter, WPJC has been proposed, designed and studied with both CFD (Computational Fluid Dynamics) and experimental methods. The WPJC is based on a novel concept in which all inlet jets are along the combustor wall. Pilot combustion experiments were conducted to investigate the combustion performance of WPJC. Two-phase flows and pulverized-coal combustion were simulated to study the mechanism of),WPJC using the commercial software FLUENT. The results show that the WPJC has many remarkable advantages: wall-protection by the cold jets without the use of refractory materials; low-temperature and three-stage combustion with low NOx emission; negligible ash/slag-deposition; multiple functions with convenient switching between them; effective adjustment of the combustion intensity and the ignition position.

Investigation of Vaporized Kerosene Injection and Combustion in a Supersonic Model Combustor

Injection and combustion of vaporized kerosene was experimentally investigated in a Mach 2.5 model combustor at various fuel temperatures and injection pressures. A unique kerosene heating and delivery system, which can prepare heated kerosene up to 820 K at a pressure of 5.5 MPa with negligible fuel coking, was developed. A three-species surrogate was employed to simulate the thermophysical properties of kerosene. The calculated thermophysical properties of surrogate provided insight into the fuel flow control in experiments. Kerosene jet structures at various preheat temperatures injecting into both quiescent environment and a Mach 2.5 crossflow were characterized. It was shown that the use ofvaporized kerosene injection holds the potential of enhancing fuel-air mixing and promoting overall burning. Supersonic combustion tests further confirmed the preceding conjecture by comparing the combustor performances of supercritical kerosene with those of liquid kerosene and effervescent atomization with hydrogen barbotage. Under the similar flow conditions and overall kerosene equivalence ratios, experimental results illustrated that the combustion efficiency of supercritical kerosene increased approximately 10-15% over that of liquid kerosene, which was comparable to that of effervescent atomization.