冲压发动机驻涡燃烧室模型方案数值模拟研究  

Numerical simulation on trapped-vortex combustor model for ramjet engine

作　　者：费立群 张炎 牛志刚 凌文辉 

机构地区：[1]中国航天科工集团三十一研究所高超声速冲压发动机技术重点实验室,北京100074

出　　处：《推进技术》2011年第5期676-679,共4页Journal of Propulsion Technology

摘　　要：为探索适用于高推重比发动机的高性能燃烧室,在一种冲压发动机特定结构应用背景条件下,设计了一种驻涡燃烧室(Trapped-Vortex Combustor,简称TVC)技术应用模型方案,并对其进行了冷态流场数值模拟,对包括驻涡区长宽比、驻涡区长度、驻涡区进口导流结构形式、主流钝体与联焰板的结构形式与参数的影响进行了分析,探索TVC燃烧室方案在冲压发动机上的应用可行性。从三维冷态流场数值模拟结果来看,燃烧室模型方案内部形成了设计的涡系结构,能够实现初步的组织燃烧。通过不同设计参数的计算模拟,摸索出驻涡区高度、驻涡区宽高比等参数对燃烧室内部流场影响的规律。研究结果表明驻涡区宽高比控制在1.0左右驻涡区涡系结构最好,有利于组织燃烧。To explore high performance combustor which may be applied to future high thrust-weight ratio engine,this paper designed a kind of Trapped-Vortex Combustor（TVC） based on a special ramjet combustor structure constraint and carried out cold flow field numerical simulation.Research was performed to the model parameters and structures including trapped-vortex region length-width ratio,trapped-vortex region length,inlet flow guidance structure,flame holder type of main flow region and flame guide plate.By the study of different design parameters,this paper found affecting rules of some parameters including trapped vortex region height and trapped vortex width height ratio to the inner field flow.Results showed that in order to obtain best trapped vortex structure,the trapped vortex width height ratio should be set at 1.0.

关 键 词：冲压喷气发动机 驻涡燃烧室 模型 数值仿真 

分 类 号：V231.2[航空宇航科学与技术—航空宇航推进理论与工程]