FIELD: engine building.
SUBSTANCE: invention relates to rocket engine building and can be used in design of liquid-propellant rocket engines (LRE). Liquid-propellant engine comprises a combustion chamber with a cooling path and an injector head, a synthesis gas generator, a turbo-pump unit including an oxidant pump, fuel pump, water pump and turbine, input of which is connected with output of synthesis gas generator, and outlet with nozzle head, note here that combustion chamber is cooled by fuel. In compliance with this version, combustion chamber is cooled by water.
EFFECT: invention improves energy characteristics and reliability of LRE.
3 cl, 2 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| LIQUID-PROPELLANT ENGINE | 2017 |
|
RU2647937C1 |
| LIQUID PROPELLANT ROCKET ENGINE | 2016 |
|
RU2612512C1 |
| LIQUID-PROPELLANT ENGINE | 2017 |
|
RU2662028C1 |
| LIQUID-PROPELLANT ENGINE | 2018 |
|
RU2692598C1 |
| COMBINED-CIRCUIT CRYOGENIC LIQUID PROPELLANT ROCKET ENGINE (VARIANTS) | 2020 |
|
RU2755848C1 |
| LIQUID PROPELLANT ROCKET ENGINE | 2014 |
|
RU2551713C1 |
| 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 |
|
RU2197629C2 |
| 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 |
| NUCLEAR SUBMARINE AND MARINE-VERSION LIQUID-PROPELLANT ROCKET ENGINE | 2012 |
|
RU2488517C1 |
| NUCLEAR SUBMARINE | 2012 |
|
RU2494004C1 |
