氢氧全流量补燃循环发动机富燃预燃室试验

推进技术 ›› 2008, Vol. 29 ›› Issue (3): 273-277.

氢氧全流量补燃循环发动机富燃预燃室试验

金平,俞南嘉,邬志岐,张国舟,蔡国飙

北京航空航天大学宇航学院北京100083;北京航空航天大学宇航学院北京100084;北京航空航天大学宇航学院北京100085;北京航空航天大学宇航学院北京100086;北京航空航天大学宇航学院北京100087

发布日期:2021-08-15

Experimental investigation of fuel-rich preburner of hydrogen/oxygen FFSC cycle engine

School of Astronautics,Beijing Univ.of Aeronautics and Astronautics,Beijing 100083,China;School of Astronautics,Beijing Univ.of Aeronautics and Astronautics,Beijing 100084,China;School of Astronautics,Beijing Univ.of Aeronautics and Astronautics,Beijing 100085,China;School of Astronautics,Beijing Univ.of Aeronautics and Astronautics,Beijing 100086,China;School of Astronautics,Beijing Univ.of Aeronautics and Astronautics,Beijing 100087,China

Published:2021-08-15

摘要/Abstract

摘要： 为了获得全流量补燃循环发动机的富燃预燃室可靠点火、稳定燃烧和均匀的出口燃气,对富燃预燃室头部喷注器排布方案展开了研究。对设计的中心燃烧区和环形燃烧区两种不同头部方案进行了试验,得到了富燃预燃室的压力曲线和预燃室出口的温度分布。试验结果表明:相比中心燃烧区结构方案,环形燃烧区结构方案更容易获得可靠的点火和稳定的燃烧,有更好的燃气均匀度。相比常规的富燃预燃室,全流量补燃循环发动机的富燃预燃室工作温度更低、混合比更小。相比使用液氧的方案,使用气氧的富燃预燃室在启动、关机过程更迅速、平稳。

关键词: 全流量补燃循环发动机+;预燃室;喷注器排布方案+;试验

Abstract: In order to get reliable ignition,stable combustion and homogeneous combustion products of FPB,research of injector layouts was conducted.The GOX-center-combustion-zoned and LOX-ring-combustion-zoned injector layouts were selected.The hot-firings demonstrate reliable ignition and stable combustion in both the LOX and GOX FPB.Fuel-rich preburner(FPB) of Full Flow Staged Combustion(FFSC) cycle engine,as one of the promising propulsion systems of Reusable Launch Vehicles,is featured with lower mixture ratio and lower combustion temperature than ordinary ones.The results also show that quicker response and smoother start-up were gained with GOX,while easier ignition and better mixing in the LOX FPB.

Key words: Full flow staged combustion cycle engine+;Precombustion chamber;Injector layout;Test

金平,俞南嘉,邬志岐,张国舟,蔡国飙. 氢氧全流量补燃循环发动机富燃预燃室试验[J]. 推进技术, 2008, 29(3): 273-277.