三组元发动机燃烧稳定性试验  

Experimental investigation on combustion instability of tripropellant rocket engine

作　　者：黄玉辉[1] 王振国[2] 周进[2] 

机构地区：[1]第二炮兵第四研究所,北京100085 [2]国防科技大学航天与材料工程学院,湖南长沙410073

出　　处：《推进技术》2003年第1期71-73,89,共4页Journal of Propulsion Technology

基　　金：国家自然科学基金资助项目 (19882 0 0 8)

摘　　要：设计了气氢 液氧 煤油三组元双工况模型发动机 ,对不同燃烧室压力、燃料比例、喷注器的结构、燃烧室长度、混合比条件下的高频燃烧稳定性进行了试验。试验中观察到低频和高频自激燃烧不稳定 ,有限的试验表明 ,较大的缩进比和较小的旋流数有利于燃烧稳定。提高燃料中氢气的比例 >10 %时 ,有利于燃烧稳定 ;但氢气对烃氧燃烧稳定性的提高不是绝对的 ,氢气在燃料中的比例达 3 9%时 ,燃烧室内仍存在压力为 0Gas hydrogen/liquid oxygen/kerosene tripropellant model engine was designed and its combustion stability was experimentally investigated under various combustor pressures, mixture ratios, injector structures and combustor lengths. Low frequency and high frequency combustion self oscillations were found in the experiments. The experimental results show that larger recess ratio and less eddy number were in favor of combustion stability. Increasing the proportion of hydrogen to the fuel is helpful for combustion stability, but hydrogen can not absolutely stabilize the hydrocarbon/oxygen combustion.

关 键 词：液体推进剂火箭发动机 燃烧稳定性 三元推进剂 燃烧试验 

分 类 号：V433.9[航空宇航科学与技术—航空宇航推进理论与工程]