超燃冲压发动机燃烧室直连式实验研究  

Study of the Scramjet Combustor Experiment

作　　者：林宏军[1] 宋文艳[1] 肖隐利[1] 

机构地区：[1]西北工业大学动力与能源学院,西安710072

出　　处：《弹箭与制导学报》2008年第1期161-163,170,共4页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：文中在超燃冲压发动机燃烧室直连式实验设备上,对超音速燃烧室模型进行(Ma=2.0)冷流实验研究,比较了不同的来流条件、不同的隔离段长高比和不同的燃烧室出口反压对燃烧室内部流场以及燃烧室隔离段的抗扰动能力的影响,并利用数值模拟的方法对燃烧室内部流场进行了模拟。研究结果表明:隔离段长高比增大,其容纳反压的能力相对增强;燃烧室出口堵塞导致的流场畸变越小,对燃烧室流场压力分布的影响越小。In this paper, experimental study （Ma= 2.0 of cold flow） on a scram）et combustor model without combustion was carried on direct-connected facility. The effects of inflow parameter, length of isolator and back pressure on combustor and isolator flow field were analyzed and compared. The flow field of combustor was simulated with CFD software and the experimental results were compared. The results show that isolator configuration maximum back pressure capability is improved by length increase of the isolator, the combustor and isolator field becomes uniformity with decease of the blockage ratio in combustor＇s exit.

关 键 词：超燃冲压发动机 直连式设备 实验研究 堵塞比 数值模拟 

分 类 号：V235.2[航空宇航科学与技术—航空宇航推进理论与工程]