FIELD: engines and pumps.
SUBSTANCE: liquid-propellant rocket engine comprises chamber, gas generator, fuel pump, two-stage turbine fed with generator gas. In compliance with this invention, turbine first stage outlet is communicated with the chamber nozzle head while turbine second stage outlet communicates with pump inlet for one of fuel components or with atmosphere.
EFFECT: higher efficiency of rocket engine with generator gas afterburning.
2 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| LIQUID PROPELLANT ROCKET ENGINE | 2014 |
|
RU2544684C1 |
| LIQUID-PROPELLANT ENGINE WITH GENERATOR GAS STAGED COMBUSTION CYCLE | 2012 |
|
RU2520771C1 |
| THROTTLEABLE OXYGEN-HYDROCARBON LIQUID-PROPELLANT ROCKET ENGINE WITH AFTERBURNING OF RECOVERY GAS | 2002 |
|
RU2238423C2 |
| 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 |
| LIQUID PROPELLANT ROCKET ENGINE | 2011 |
|
RU2450153C1 |
| 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 |
| LIQUID-PROPELLANT ENGINE OF OPEN CONFIGURATION | 2010 |
|
RU2459970C2 |
| METHOD OF OPERATION OF CLOSED CYCLE LIQUID ROCKET ENGINE WITH AFTERBURNING OF OXIDIZING AND REDUCING GENERATOR GASES WITHOUT COMPLETE GASIFICATION AND LIQUID ROCKET ENGINE | 2022 |
|
RU2801019C1 |
| TURBO-PUMP SUPPLY SYSTEM FOR LIQUID-PROPELLANT ROCKET ENGINE | 2002 |
|
RU2246023C2 |
| LIQUID-PROPELLANT ROCKET REHEAT ENGINE | 1999 |
|
RU2158839C2 |
