COMBUSTION GAS DISCHARGE NOZZLE FOR ROCKET ENGINE, ROCKET ENGINE WITH SUCH NOZZLE AND AIRCRAFT WITH SAID ENGINE Russian patent published in 2018 - IPC F02K1/80 F02K9/97 F02K9/86 

FIELD: fuel combustion devices.

SUBSTANCE: combustion gas discharge nozzle for a rocket engine comprises a stationary part, a moving part, extending the stationary part, as well as a sealing device. Moving part is made of flaps and is positioned at the outlet of the stationary part and forms an extension of the nozzle. Sealing device is positioned between the stationary part and the moving part and is in the form of a soft membrane withstanding a local temperature of the combustion gases at the nozzle outlet and connects the end of the stationary part to a border of the flaps forming the moving part. Soft membrane forms an annular tubing. Sealing device is provided with means for injecting exhaust gases from a turbine of a turbine pump at the level of a soft membrane between the stationary part and the moving part extending said nozzle. Other inventions of the group relate to a rocket engine comprising said exhaust nozzle, as well as an aircraft having such a rocket engine.

EFFECT: group of inventions allows to reduce the flow loss between the stationary part and the moving parts of the nozzle.

17 cl, 6 dwg