双模态超燃冲压发动机准一维流场数值模拟  

One-dimensional numerical computation of the combustor in supersonic combustion engine

作　　者：杨事民[1] 唐豪[1] 黄王月 

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《沈阳航空工业学院学报》2007年第5期5-9,共5页Journal of Shenyang Institute of Aeronautical Engineering

基　　金：国家863基金资助项目(2004AA723020)

摘　　要：使用一维模型和定比热假设,对超燃发动机在超声速状态下的几何截面的设计及在固定几何截面如何调节气动热力(燃烧速率,喷射位置等)优化工作状态进行了数值研究。采用加热规律经验公式,分析加热规律变化对燃烧室和隔离段内流动参数的影响。采用四阶龙格-库塔法对一维控制方程求解,表明几何形状及加热规律对燃烧室工作的优劣有很大的影响。通过研究发现完全可以单独通过调节加热规律达到优化燃烧工况的目的。Adopting one - dimensional model and stable Cp hypothesis, this thesis makes numerical simulation on geometry design of supersonic condition and how to optimize working conditions by adjusting thermodynamics in a fixed geometry. Experiential formula of thermodynamics releasing is cited to analyze impacts of the thermodynamics change on the flowing parameters in combustion chamber or isolator. Working out one - dimensional governing equation through R - K demonstration,which shows that geometrical configuration and thermodynamics releasing affect combustion chamber greatly. This thesis concludes that to adjust thermodynamics parameter can optimize combustion working condition.

关 键 词：超燃冲压发动机 燃烧室 隔离段 一维模拟 

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]