超燃冲压发动机隔离段流场抗反压能力数值模拟  

Numerical Simulation of the Flow Field for Resistance Pressure in Scramjet Isolator

作　　者：杨事民[1] 唐豪[1] 黄玥[1] 

机构地区：[1]南京航空航天大学能源与动力学院,南京210016

出　　处：《长春理工大学学报（自然科学版）》2008年第1期127-131,共5页Journal of Changchun University of Science and Technology(Natural Science Edition)

基　　金：国家863计划资助项目(2004AA723020)

摘　　要：隔离段是双模态超燃冲压发动机实现双模态和模态转换的一个重要部件,同时,它把进气道和燃烧室隔离开,以防止燃烧室高压干扰进气道,引起进气道不启动。为了更清楚地捕捉流道内复杂激波链,本文使用三阶精度迎风MUSCL格式,K-湍流模型,对隔离段进行了数值计算。考虑到燃烧室的不同结构,本文主要针对几种燃烧室结构模型中隔离段抗反压能力进行了计算比较分析,特别是台阶结构可以有效的缓解燃烧室压力对隔离段的影响。Isolator is a key component ofscramjet to achieve dual-mode and mode transition, and it separates inlet from combustion chamber to prevent the effect of combustion back pressure on inlet, becanse the back pressure could result in non-start for engine. In this paper, the flow fields inside isolator has been simulated using three order up-wind MUSCL scheme, and K-ω turbulence model, so it is easy to catch the shock train in the isolator flow field. The resistance pressure ability of different combustion chamber structure on flow fields will be computed and analyzed, Especially step structure could prevent the effect that pressure of combustion chamber transfer to isolator.

关 键 词：超燃冲压发动机 隔离段 数值模拟 燃烧室模型 激波链 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]