| 摘要 |
<p>The invention relates to a rocket engine (100), which includes an antechamber and combustion chamber (14), two supply lines (22A, 22B) for the engine, and two turbopumps (20A, 20B). The engine is a staged-combustion engine. A jet pump (102A, 102B) is arranged in at least a first supply line (12A, 12B). After being pressurized, a portion of the fluid circulating in the first supply line is directed towards the jet pump, so as to enable said pump to convey the fluid circulating in said first supply line to the intake of said first pump, thereby increasing the pressure at the supply port of the pump.</p> |
