发明名称 |
TWO-DIRECTION REGENERATIVE COOLING COMBUSTION CHAMBER FOR LIQUID PROPELLANT ROCKET ENGINE |
摘要 |
A bidirectional regenerative cooling combustion chamber for a liquid rocket engine is provided to reduce the outermost diameter of an engine by positioning a fuel inlet pipe between the one end and head of a nozzle so that fuel bidirectionally flows in case two or more combustor are assembled. A bidirectional regenerative cooling combustion chamber(200) for a liquid rocket engine comprises: a fuel inlet pipe(110) being formed so that fuel flows into one side; a fuel ring which uniformly supplies the fuel flowed through the fuel inlet pipe to a cooling channel; an orifice inducing the supplied fuel to a head direction cooling channel or a nozzle direction cooling channel; and a return cooling channel inducing the fuel, supplied to the nozzle direction cooling channel, to the head direction in the end of the nozzle.
|
申请公布号 |
KR20090073334(A) |
申请公布日期 |
2009.07.03 |
申请号 |
KR20070141251 |
申请日期 |
2007.12.31 |
申请人 |
KOREA AEROSPACE RESEARCH INSTITUTE |
发明人 |
LEE, KWANG JIN;KIM, JONG GYU;KIM, SEONG KU;HAN, YEOUNG MIN;CHOI, HWAN SEOK |
分类号 |
F02K9/64;F02K9/60;F02K9/62 |
主分类号 |
F02K9/64 |
代理机构 |
|
代理人 |
|
主权项 |
|
地址 |
|