GAS FLOW FLARE REFLECTOR OF SOLID-PROPELLANT ROCKET ENGINE Russian patent published in 2020 - IPC F02K9/34 F02K9/30 

FIELD: astronautics.

SUBSTANCE: invention relates to rocket engineering and can be used in solid-propellant rocket engines, in which it is necessary to deploy gas flow inside combustion chamber by angle of more than 90°, including in rocket engine of separation of propulsion system of emergency rescue of astronauts. Solid-propellant rocket engine consists of a housing having a cylindrical shape and made integral with a rear hemispherical bottom, a front bottom, combined with a nozzle block and attached to the cylindrical housing by means of a key connection. Cover with ignition unit is fixed in rear bottom. Nozzle unit combined with the front bottom is made in the form of a hemisphere with nozzles located at an angle to the engine axis and symmetrically to each other. Inner surfaces of rear bottom, front bottom and nozzle block have heat-insulating coating. In the front bottom there is a gas flow reflector which is made of a heat-resistant material. Introduction of a deflector in the formation of a stagnant zone of combustion gases of powder gases, due to their turning through an angle of more than 90°, makes it possible to direct a gas flow towards the nozzles and, thus, to prevent its braking in the area of the front bottom.

EFFECT: as a result, this technical solution allows to eliminate stagnant zone of gas flow, reduce heat load on structural elements of rocket engine and improve manufacturability of its production.

1 cl, 2 dwg