LIQUID PROPELLANT ROCKET ENGINE Russian patent published in 2014 - IPC F02K9/48 

FIELD: engines and pumps.

SUBSTANCE: invention relates to rocket engineering. Liquid propellant rocket engine comprises a turbopump set, which contains in its turn the following components installed on a shaft: a turbine, oxidant and fuel pumps, and a combustion chamber having a cylindrical part with oxidant and fuel nozzles and a nozzle with the main header of fuel and a system of regenerative cooling, according to the invention, the turbopump set and the combustion chamber are installed coaxially, the combustion chamber is made as two-zone and comprises the first circular zone with a circular nozzle block and an upper fuel header, and the second zone with a central nozzle block, having additional fuel nozzles, and the turbine is installed between the first and second zones of the combustion chamber. The outlet from the oxidant pump is connected by the pipeline comprising an oxidant valve with a combustion chamber. The outlet from the fuel pump is connected by pipelines with the main and upper fuel headers. The turbine is made as consisting of the nozzle block, an impeller and a straightening unit with a cavity inside of it, a central nozzle block is made as hollow, and its cavity is connected by axial holes via the cavity inside the straightening unit with a gap of regenerative cooling of a nozzle and the second zone of the combustion chamber.

EFFECT: invention provides for improvement of specific characteristics of an engine and also its increased reliability.

5 cl, 3 dwg