超燃冲压发动机燃烧室流场数值模拟  

Numerical Simulation of Flow Field of a Scramjet Combustor

作　　者：杨事民[1] 张建良[1] 

机构地区：[1]南京航空航天大学无人机学院,南京210016

出　　处：《航空发动机》2009年第4期25-28,11,共5页Aeroengine

基　　金：国家863基金(2006AA705306)资助

摘　　要：对台阶和凹腔组合的超燃冲压发动机燃烧室结构进行了数值模拟分析。在冷态流场中,分析了组合结构流场特性和激波特点,同时对以氢气为燃料的燃烧室流场进行了数值模拟。模拟结果表明:台阶下游和凹腔处存在有利于燃烧和火焰稳定的回流区,能够增强凹腔卷吸的效果,从而可以增强燃料的混合;在燃烧流场中,凹腔是火焰稳定的主要区域,燃烧效率较高,此结构能够很好地起到增强燃烧的作用。The combining structure of a scramjet combustor with the steps and the cavity was simulated numerically. The flow field and the shock characteristics of combining structure were analyzed in the cold flow fields and the numerical simulation of the combustor flow fields with hydrogen were performed. The simulation result show that the step downstream and the cavity have profitable reversed-flow region for the burning and the flame stabilization and the effect of the cavity entrainment is enhanced, and the fuel mixing is improved. The cavity is the main region of the flame stabilization in the combustor flow field and the combustion efficiency is higher. The structure has role in the enhanceding combustion.

关 键 词：超燃冲压发动机 燃烧室 数值模拟 双台阶结构 凹腔结构 

分 类 号：V235.21[航空宇航科学与技术—航空宇航推进理论与工程] TV131.4[水利工程—水力学及河流动力学]