气氢亚燃冲压发动机突扩燃烧室数值模拟研究

A NUMERICAL STUDY ON DUMP COMBUSTION CHAMBER OF GASEOUS HYDROGEN SUBSONIC COMBUSTION RAMJET

关键词:  冲压火箭发动机  氢燃料  亚音速燃烧  突扩燃烧室  数值模拟

Key words:  Ducted rocket engine  Hydrogen fuel  Subsonic combustion  Dump combustion chamber  Numerical simulation

摘要:

对气氢亚燃冲压发动机突扩燃烧室进行了数值模拟研究。研究发现、喷嘴节距Ｓ／Ｄ和喷嘴离台阶的距离是设计试验件所需的重要参数，它们影响氢射流的穿透深度、氢浓度分布的均匀性和回流区内的氢浓度。氢射流和空气进口条件的改变也对氢气穿透深度有重要影响。

Abstract:

Work has been underway to develop a subsonic combustion ramjet that is capable ofpropelling a vehicle at hypersonic speeds in the atmosphere or beyond. A recent part of the researchhas been directed toward the optimization of arrangement and inlet condition of hydrogen jet orificesin a dump ramjet combustor. This paper describes a study of H2/Air mixing and reaction in a gaseoushydrogen subsonic combustion ramjet and discussed several parameters influencing the penetration ofH2 jets. Based on the results of this study, an alternate H2 injection configuration was computionallydesigned, which significantly increases the H2 penetration.