FIELD: engines.
SUBSTANCE: invention relates to rocket building and can be used in liquid propellant rocket engines (LPRE) and power plants of various purposes. The combined-circuit cryogenic liquid-propellant rocket engine comprises a chamber with a head and a cooling path, an oxidiser turbine pump unit comprised of an oxidiser pump and a turbine, a fuel turbine pump unit comprised of a fuel pump and a turbine, the turbine inlet whereof is connected with the outlet of the cooling path of the chamber and the outlet whereof is connected with the inlet of the head of the chamber, an oxidiser line and a high-pressure fuel line, wherein a gas generator generating a working gas for the turbine drive is installed at the inlet of the turbine of the oxidiser turbine pump unit, wherein the inlet of the gas generator is connected with the oxidiser line and the high-pressure fuel line. Described is a second variant of a combined-circuit cryogenic LPRE containing a chamber with a head and a cooling path, an oxidiser turbine pump unit comprised of an oxidiser pump and a turbine, a fuel turbine pump unit comprised of a fuel pump and a turbine, an oxidiser line and a high-pressure fuel line, wherein a gas generator generating a working gas for the turbine drive is installed at the inlet of the turbine of the oxidiser turbine pump unit, wherein the inlet of the gas generator is connected with the oxidiser line and the high-pressure fuel line, a heat exchanger is installed at the outlet of the turbine of the oxidiser turbine pump unit, the inlet whereof is connected with the outlet of the cooling path of the chamber and the outlet whereof is connected with the fuel inlet of the turbine of the turbine pump unit.
EFFECT: invention provides an increase in the pressure in the combustion chamber, simplification of forcing and regulation of the engine, increase in the efficiency, reduction of the weight and dimensions.
8 cl, 8 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| METHOD FOR COMPENSATION OF FUEL PHYSICAL PROPERTIES DIFFERENCES IN UNIVERSAL GENERATOR-FREE LIQUID-PROPELLANT ROCKET ENGINE AND LIQUID-PROPELLANT ROCKET ENGINE (VERSIONS) | 2008 |
|
RU2358142C1 |
| LIQUID-PROPELLANT ENGINE | 2015 |
|
RU2579295C1 |
| LIQUID PROPELLANT ROCKET ENGINE (VERSIONS) | 2006 |
|
RU2301352C1 |
| 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 |
| CRYOGENIC-LIQUID-PROPELLANT ROCKET ENGINE | 1996 |
|
RU2118684C1 |
| LIQUID-PROPELLANT ENGINE WORKING ON CRYOGENIC COMPONENTS OF PROPELLANT WITH CLOSED LOOP OF DRIVE OF TURBINE OF TURBO-PUMP UNIT | 2000 |
|
RU2190114C2 |
| LIQUID CRYOGENIC PROPELLANT ROCKET ENGINE WITH CLOSED LOOP OF TURBINE DRIVE OF TURBOPUMP UNIT (VERSIONS) | 1999 |
|
RU2155273C1 |
| LIQUID-PROPELLANT ROCKET ENGINE AND THE METHOD OF ITS STARTING | 2006 |
|
RU2299345C1 |
| LIQUID-PROPELLANT ROCKET ENGINE | 2006 |
|
RU2302547C1 |
| 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 |
