常规推进剂发动机高压富氧燃气燃烧处理方法与试验  

Combustion treatment method and test of high pressure oxidizer-rich gas of conventional propellant LRE

作　　者：肖虹[1] 房喜荣 李悦 李龙飞[1] 孙海雨[1] 王焕燃 XIAO Hong;FANG Xirong;LI Yue;LI Longfei;SUN Haiyu;WANG Huanran(Xi'an Aerospace Propulsion Institute,Xi'an 710100,China)

机构地区：[1]西安航天动力研究所,陕西西安710100

出　　处：《火箭推进》2023年第1期87-92,共6页Journal of Rocket Propulsion

基　　金：国家自然科学基金(U1967203)。

摘　　要：针对大推力常规推进剂补燃发动机燃气发生器试验的高压富氧燃气的无毒化排放处理需求,设计了国内首个大流量高压富氧燃气实时燃烧处理装置,实现了某补燃发动机富氧发生器试验燃气的燃烧处理。处理装置采取快速降压和混水补燃的技术方案,首先采用超声速拉法尔喷管和多孔阻尼板,使排气的压力大幅下降,并通过整流装置保证排气流场参数均匀,为下游燃烧室提供低压低速的稳定气流;然后采用分级燃烧室,在燃烧室轴线的不同位置多次喷射混水燃料,实现与富氧排气进行补燃,通过控制混合比和燃烧温度,保证NO_(x)转化为N_(2)和CO_(2)。试验结果表明,处理装置燃烧稳定,结构可靠,排气压降比超过95%,补燃效率超过0.9,实现了无毒化处理能力超过每秒百千克量级。In order to detoxify the oxidizer-rich exhaust gas produced by the N_(2)O_(4)/UDMH gas generator of high-thrust staged combustion cycle rocket engine,a real-time combustion treatment device for high-pressure semi-system test of a liquid engine was developed.Technologies of rapid depressurization and secondary combustion with water-mixed fuel were adopted.The device consists of stabilization chamber and secondary combustion chamber.A significant pressure drop was obtained when the exhaust gas flows through supersonic nozzle and multi-orifice plate in stabilization chamber.The exhaust flow becomes uniform before it flows into the secondary combustion chamber downstream.The water-mixed fuel is sprayed at different positions in the secondary combustion chamber.By controlling mixing ratio and combustion temperature,NO_(x) in the exhaust gas is converted into N_(2) and CO_(2).Test results present that the secondary combustion is stable and the structure is reliable.The pressure drop ratio is higher than 95% and the secondary combustion efficiency is over 0.9.The non-toxic treatment is realized,and the treatment flow rate of exhaust gas exceeds 100 kg/s.

关 键 词：常规推进剂 富氧燃气 降压 混水燃料 补燃 无毒处理 

分 类 号：V434.3[航空宇航科学与技术—航空宇航推进理论与工程]