二次进气流量比对固冲发动机燃烧效率的影响

推进技术 ›› 2005, Vol. 26 ›› Issue (5): 401-403.

二次进气流量比对固冲发动机燃烧效率的影响

田维平,刘佩进,何国强

西北工业大学航天工程学院陕西西安710072;西北工业大学航天工程学院陕西西安710072;西北工业大学航天工程学院陕西西安710072

发布日期:2021-08-15

Influence of air mass flow rate ratio on combustion efficiency of solid rocket ramjet with two air inlets

Coll.of Astronautics,Northwestern Polytechnical Univ.,Xi’an 710072,China;Coll.of Astronautics,Northwestern Polytechnical Univ.,Xi’an 710072,China;Coll.of Astronautics,Northwestern Polytechnical Univ.,Xi’an 710072,China

Published:2021-08-15

摘要/Abstract

摘要： 采用k-ε湍流模型及单步涡扩散化学反应模型,对二次进气结构的固体冲压发动机补燃室的反应流场进行数值模拟,分析了二次进气流量比对燃烧效率与温度场分布的影响。结果表明,在合适流量比下,采用二次进气后补燃室内燃烧效率明显提高,且温度场分布有利于内壁面热防护。

关键词: 固体火箭冲压发动机;二次进气;燃烧效率;数值模拟

Abstract: Using k-ε turbulence model and one step eddy-dissipation model,numerical studies on the reacting flow field of solid rocket ramjet with secondary air inlets were carried out.Influence of mass flow ratio on combustion efficiency and temperature field was analyzed.Numerical results show that combustion efficiency increases with a proper mass flow rate ratio,and temperature field is of benefit to thermal protection.

Key words: Solid rocket ramjet;Secondary air inlets;Combustion efficiency;Numerical simulation

田维平,刘佩进,何国强. 二次进气流量比对固冲发动机燃烧效率的影响[J]. 推进技术, 2005, 26(5): 401-403.