非壅塞火箭冲压发动机补燃室两相流数值模拟

Two phase flow combustion modeling of secondary combustion chamber in a unchoked ducted rocket

关键词:  冲压火箭发动机  加力燃烧室  数值仿真  二相流  燃烧

Key words:  Ducted rocket engine  Afterburner  Numerical simulation  Two phase flow  Combustion

摘要:

采用颗粒轨道模型进行了非壅塞火箭冲压发动机补燃室两相流的数值模拟,其中铝颗粒的燃烧模型采用的是Davis扩散控制燃速的燃烧模型,建立了发动机补然室简单反应流模型,并在该模型下对某实验发动机进行了模拟,得出颗粒在补燃室内的分布,结果表明:与颗粒确定轨道模型相比,颗粒随机轨道模型更加适合模拟冲压发动机中的两相流动,并且颗粒的初始直径对颗粒燃烧效率有很大的影响。

Abstract:

In primary combustion chamber, highly metal loaded propellant cannot completely burn for lack of oxidant, so how to make metallic particles burning high efficiently in secondary combustion chamber is also a key technology of ducted rockets. This paper discusses the numerical computation of two phase flow in a unchoked ducted rocket based on discrete phase model. Assuming that the rate of aluminium combustion is controlled by diffusion based on the experimental work of Davis. Simple reacting flow model is established and used to simulate an experimental motor. It is shown that the diameter of initial particles has great effect on the combustion efficiency of particle.