双模态冲压发动机燃烧室流场数值模拟研究  

Study on numerical simulation of the dual-mode scramjet combustor

作　　者：武渊[1] 田维平[1] 乐发仁[1] 余贞勇[1] 

机构地区：[1]中国航天科技集团公司四院四十一所,西安710025

出　　处：《固体火箭技术》2003年第4期41-44,共4页Journal of Solid Rocket Technology

摘　　要：在三维、粘性、湍流及有化学反应的Navier Stokes方程基础上,通过有限化学反应速率/涡扩散模型模化湍流燃烧,对以H2为燃料的双模态冲压发动机燃烧室流场进行了研究,分析了空燃比、燃料入射角、飞行马赫数对燃烧室工作模态的影响,并分析了燃烧室隔离段的作用。On the basis of 3-D viscous, turbulent and reactive Navier-Stokes numerical equation, the finite-rate chemistry/eddy-dissipation model for modeling the turbulent combusion is established. The fluid dynamic mechanisms of the dual-mode scramjet combustor using hydrogen as the fuel is studied. The effects of the ratio of the air to fuel, fuel injection angle and flight Mach number on the dual-scramjet working mode are analyzed, and the function of the isolator is analyzed too.

关 键 词：双模态冲压发动机 燃烧室 流场 数值模拟 飞行马赫数 超音速燃烧 

分 类 号：V439[航空宇航科学与技术—航空宇航推进理论与工程]