150 N气氧/煤油发动机涡流冷却技术试验
王 勇1,巨 乐2,杨伟东2,洪 流1

(1.西安航天动力研究所 液体火箭发动机技术重点实验室,陕西 西安 710100; 2.西安航天动力研究所,陕西 西安 710100)

姿控发动机; 气氧/煤油; 涡流冷却推力室; 数值仿真; 热试

Experimental investigation on vortex-cooled technology of 150 N GO2/kerosene engine
WANG Yong1, JU Le2, YANG Weidong2, HONG Liu1

(1.Science and Technology on Liquid Rocket Engine Laboratory,Xi'an Aerospace Propulsion Institute,Xi'an 710100,China; 2.Xi'an Aerospace Propulsion Institute,Xi'an 710100,China)

attitude control engine; GO2/kerosene; vortex-cooled thrust chamber; numerical simulation; hot-fire test

备注

为探索百牛量级姿控发动机采用气氧/煤油涡流冷却推力室的可行性,开展了涡流冷却技术的试验验证工作。在理论分析和数值仿真的基础上,完成了150 N气氧/煤油涡流冷却推力室设计。数值仿真结果表明:内旋流区域占燃烧室直径Dc的87.8%,燃烧化学反应发生在39%～81%Rc的环形区域。经热试考核,燃烧室点火可靠,工作稳定,燃烧效率达0.91; 形成了有效的气膜冷却,壁面和头部热防护可靠,充分验证了内外双漩涡结构的存在。

In order to explore the feasibility of GO2/kerosene vortex-cooled thrust chamber used in the attitude control engine with a hundred Newton level, an experimental verification of vortex-cooled technology was carried out. Based on the theoretical analysis and the numerical simulation, the design of 150 N GO2/kerosene vortex-cooled thrust chamber was completed. The numerical simulation results show that the internal swirling area accounts for 87.8% of the chamber diameter, and the combustion chemical reaction occurs in the annular region with 39%～81% of chamber radius. Through the hot-fire test, the combustion chamber achieves the reliable ignition, stable operation and combustion efficiency of 0.91. An effective gas film cooling is formed and the thermal protection of thrust chamber wall and head is reliable, which fully indicates the existence of internal and external double vortex structure.