一次燃气混合比对引射火箭二次燃烧火焰稳定的影响  

Influence of mixture ratio of primary flow on secondary combustion flame stability of ejector rocket motor

作　　者：李强[1] 刘佩进[1] 陈剑[1] 

机构地区：[1]西北工业大学燃烧流动和热结构国家级重点实验室,西安710072

出　　处：《固体火箭技术》2009年第4期427-430,435,共5页Journal of Solid Rocket Technology

摘　　要：在综合分析引射火箭燃烧组织模式的基础上,针对固定结构的引射火箭发动机,借助双燃烧室冲压发动机的原理,开展了SMC+DAB混合燃烧组织模式的数值分析和发动机直连实验研究,详细分析了富燃一次燃气对二次燃烧火焰稳定的作用及其对发动机性能的影响。结果表明,SMC+DAB混合燃烧模式具有一定的优点,合适的一次燃气混合比可起到稳定二次燃烧火焰和提高发动机性能的作用,偏高和偏低的一次燃气混合比都不利于发动机性能的提高。在文中给定的实验条件和参数条件下,一次燃气混合比应为0.7左右。Based on comprehensive analysis for combustion mode of ejector rocket, the numerical analysis of SMC ＋ DAB hybrid combustion mode and direct connected experiments for the ejector rocket motor with fixed structure were carryied out by means of the essential principle of dual-combustor ramjet. The influences of primary gas flow mixture ratio on the secondary combustion flame stability and properties of motor were analyzed. The results show that the SMC ＋ DAB hybrid combustion mode is reasonable, and a proper primary gas flow mixture ratio tends to stabilize the secondary combustion flame and improve properties of motor. Either higher or lower primary gas flow mixture ratio is adverse. The appropriate primary gas flow mixture ratio under given test and parameter condition in this paper is about 0.7.

关 键 词：引射火箭发动机 燃烧火焰稳定 燃气混合比 数值分析 

分 类 号：V436[航空宇航科学与技术—航空宇航推进理论与工程]