FIELD: engines and pumps.
SUBSTANCE: Liquid-propellant rocket engine comprises combustion chamber integrated with auxiliary chamber operated at excess of one of fuel components. In compliance with this invention turbopump unit with inlet connected with auxiliary chamber. Besides, said engine incorporates extra gas generator operated at excess second fuel component, its output being connected with combustion chamber nozzle head.
EFFECT: higher power output.
2 cl, 2 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| METHOD OF OPERATION OF LIQUID-PROPELLANT ROCKET ENGINE WITH TURBOPUMP DELIVERY OF CRYOGENIC PROPELLANT ON BASIS OF OXYGEN OXIDIZER AND HYDROCARBON FUEL AND LIQUID- PROPELLANT ROCKET ENGINE IMPLEMENTING SAID METHOD | 2001 |
|
RU2197628C2 |
| METHOD OF OPERATION OF LIQUID-PROPELLANT ROCKET ENGINE WITH TURBOPUMP DELIVERY OF CRYOGENIC PROPELLANT ON BASIS OF FUEL AND OXYGEN OXIDIZER AND LIQUID-PROPELLANT ROCKET ENGINE FOR IMPLEMENTING SAID METHOD | 2001 |
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