非壅塞固体火箭冲压发动机二次燃烧试验研究  

Experimental Investigation on Secondary Combustion in Unchoked Ducted Rocket

作　　者：夏智勋[1] 胡建新[1] 王志吉[1] 郭健[1] 张炜[1] 姜春林[1] 

机构地区：[1]国防科学技术大学航天与材料工程学院,湖南长沙410073

出　　处：《航空动力学报》2004年第5期713-717,共5页Journal of Aerospace Power

摘　　要：通过直连式试验研究非壅塞固体火箭冲压发动机二次燃烧影响因素。试验结果表明,当空燃比在一定范围内变化时,若空燃比变大,则燃烧效率升高,当空燃比达到一定程度后再增加,则燃烧效率降低;对于铝镁贫氧推进剂取较小的后置长度时燃烧效率较高;与两股燃气射流向外喷射相比,两股燃气射流向内喷射的燃烧效率明显高;燃气射流与空气流在进气道出口直接撞击不利于燃烧效率的提高。Some experimental investigations have been done on a direct-connect test bed. The experimental investigation is aimed at exploring factors that affect unchoked ducted rocket combustor efficiency. Aluminum/magnesium-loaded fuel-rich HTPB (hydroxyl terminated polybutadiene) propellant was used. The effects of factors such as air/fuel ratio, dome height and angle of gas injector on performance of the combustor and the engine was examined. In a definite range of air-fuel ratio, with the increase of air-fuel ratio, combustion efficiency increases. After air-fuel ratio reaches some definite point, further increase of air-fuel ratio, a decrease trend of combustion efficiency is observed. Decreasing the dome height increases combustion efficiency. The impinging jet injection device improves combustion efficiency. If the fuel streams impinge with the airstream directly at the exit of air-inlet, it makes negative effect on combustion efficiency.

关 键 词：整体式固体火箭冲压发动机 燃烧试验 突扩燃烧室 空燃比 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]