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Critical slot size for deflagration initiation by hot products discharge into hydrogen air-atmospheres

机译:通过热产品排放到氢气中引起爆燃的临界槽口尺寸

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This computational study addresses deflagration initiation of lean, stoichiometric, and moderately rich hydrogen air mixtures by the sudden discharge of a hot planar jet of its adiabatic combustion products. The objective is to determine the minimum slot size required for ignition, a relevant quantity of interest for safety and technological applications concerning the accidental ignition of hydrogen. For sufficiently small jet velocities, the numerical solution of the problem requires integration of the two-dimensional Navier Stokes equations for chemically reacting ideal-gas mixtures, supplemented by standard descriptions of the molecular transport terms and a reduced chemical kinetic mechanism suitable for hydrogen air combustion. The computations provide the variation of the critical slot size for hot-jet ignition with both the jet Reynolds number and the equivalence ratio of the mixture. In particular, it is seen that, while the Reynolds number exerts only a relatively weak effect on the ignition process, the influence of the equivalence ratio is much more pronounced, with the smallest slot widths found for stoichiometric or slightly rich conditions. The numerical results show three different ignition modes, with the flame developing from a clearly identified ignition kernel located either at the core of the leading vortex pair (mode 1), at the symmetry plane near the leading edge of the starting jet (mode 2), or at the jet stem connecting the jet exit with the starting vortex (mode 3). (C) 2016 Hydrogen Energy Publications LLC. Published by Elsevier Ltd. All rights reserved.
机译:这项计算研究通过突然排出绝热燃烧产物的热平面射流来解决稀薄,化学计量和中等浓的氢气混合气的爆燃。目的是确定点火所需的最小槽口尺寸,这是安全和涉及氢气意外点火的技术应用的相关关注量。对于足够小的射流速度,此问题的数值解决方案需要对二维Navier Stokes方程进行积分,以使理想气体混合物发生化学反应,并辅之以分子传输术语的标准描述和适用于氢气燃烧的简化化学动力学机制。该计算提供了用于热喷气点火的临界缝隙尺寸随喷气雷诺数和混合物的当量比的变化。特别地,可以看出,尽管雷诺数仅对点火过程产生相对较弱的影响,但当量比最小的狭槽宽度在化学计量比或略微浓的条件下,当量比的影响更为明显。数值结果显示了三种不同的点火模式,其中火焰由清晰识别的点火核产生,该点火核位于前涡流对的核心(模式1),靠近起始射流前沿的对称平面(模式2)。 ,或在将喷气出口与起始涡旋连接的喷气杆上(模式3)。 (C)2016氢能出版物有限公司。由Elsevier Ltd.出版。保留所有权利。

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