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为揭示空气涡轮火箭发动机燃烧室中富燃燃气与空气在涡轮局部进气条件下的混合增强机制和燃烧反应机理,对富燃燃气与空气的湍流混合及燃烧过程进行了数值模拟,并结合试验结果定量分析了两类燃烧组织方案的掺混和燃烧效率。研究结果表明:涡轮局部进气条件下波瓣混流器强化掺混的主导因素是大尺度流向涡的对流型混合,涡轮局部进气对涡系的初始空间分布及涡量强度具有显著影响,其对下游掺混质量的影响与波瓣型面相关;肼分解燃气与空气的燃烧是一种分支链锁反应,其主要反应历程是氢气的氧化反应和氨气的分解,热混合效率可作为掺混燃烧效率预测的重要参考量。
In order to reveal the mixing enhancement mechanism and combustion reaction mechanism of rich gas and air in the turbo-charged air in the rocket engine combustor, the turbulent mixing and combustion process of rich gas and air are numerically simulated, and combined with the experimental results The blending and combustion efficiency of two kinds of combustion organizations were quantitatively analyzed. The results show that the dominant factor of the turbulent flow mixing is the convective mixing of large-scale flow vortices, and the local turbulence of the turbo-charged turbulence has a significant effect on the initial spatial distribution and vorticity of the vortex system. The influence of downstream mixing quality on lobed profile is related to the combustion of the lobed profile. The combustion of hydrazine decomposition gas and air is a kind of branching chain reaction. The main reaction process is hydrogen oxidation reaction and ammonia decomposition. An important reference for predicting mixed combustion efficiency.