LRE CHAMBER OPERATING ON THREE COMPONENTS OF FUEL OXYGEN, HYDROGEN AND HYDROCARBON IN A CLOSED CIRCUIT WITH AFTERBURNING OF OXIDIZING GENERATOR GAS Russian patent published in 2023 - IPC F02K9/42 F02K9/62 

FIELD: liquid propellant rocket engines.

SUBSTANCE: invention relates to liquid propellant rocket engines (LRE). LRE chamber, operating on three fuel components oxygen, hydrogen and hydrocarbon in a closed circuit with afterburning of oxidizing generator gas, contains a combustion chamber with a cylindrical and tapering part, a two-cavity head block with two-component nozzles, an outer bottom with ignition devices located on it and lines for supplying components fuel, while in the combustion chamber in the cylindrical part and in the cavity of the head there is a partition with cooling channels, separating the combustion cavity of the fuel components H₂ and O₂ from the combustion cavity of the fuel components O2 and hydrocarbon and separating the injector block into an annular hydrogen block and an internal hydrocarbon block, in which (in the partition) the upper finned cavity connects the hydrogen supply line with the cavity of the nozzles located in the annular cavity of the nozzle block, and the lower finned cavity connects the hydrocarbon supply line with the internal cavity of the nozzle block, and in the side wall of the partition Longitudinal slots are made in the unit of injectors for the supply of oxidizing generator gas into the internal cavity of the injector unit. Dead ends are made in the baffle in the lower finned cavity in the region of the nozzle block in the cooling channels, behind which holes are made in the inner wall of the baffle for hydrogen to flow to cool the lower and upper fins.

EFFECT: invention provides an improvement in the specific energy characteristics of the liquid-propellant rocket engine, an increase in reliability and a reduction in material costs.

2 cl, 5 dwg