不同入口空气流量对冲压发动机二次燃烧的影响  

Effect of Different Air Inlet Mass Flow Rate on Secondary Combustion of Ramjet

作　　者：郑凯斌[1] 陈林泉[1] 张胜勇[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：《弹箭与制导学报》2008年第3期173-174,180,共3页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：采用涡团耗散模型和化学动力学控制的碳粒子燃烧模型对中心进气固体火箭冲压发动机反应流场进行数值计算,分析了不同入口空气流量对冲压发动机二次燃烧的影响,并与试验结果进行比较。研究结果表明:随着入口空气流量的增加,补燃室尾部压强升高,燃烧效率增加,而补燃室尾部温度降低。The reacting flow field of solid rocket ramjet with central air-inlet mode was numerically calculated by eddydissipation model and combustion model of carbon particles by kinetic-limited rate. The effect of different air inlet mass flow rate on secondary combustion of the ramjet was analyzed and compared with the test data. The results show that the pressure and combustion efficiency in the secondary combustor increase and the tail end temperature decreases while air inlet mass flow increases.

关 键 词：固体火箭冲压发动机 数值计算 燃烧效率 

分 类 号：V435.12[航空宇航科学与技术—航空宇航推进理论与工程]