JET TURBINE ENGINE WITH RECTANGULAR NOZZLE Russian patent published in 2016 - IPC F02K1/34 F02K1/44 F02K1/78 

FIELD: engines and pumps.

SUBSTANCE: invention relates to aircraft turbojet engines intended for continuous operation at supersonic aircraft. Jet turbine engine includes a rectangular nozzle with an elongated bottom wall of the nozzle with a convex-concave duct surface at the outlet, as well as a bypass duct. Outside of the bypass duct there is an external channel at the outlet connected with the inner cavity of the outlet nozzle. Bottom elongated wall of the nozzle is made of a front and a rear flaps to make a slotted cavity between the movable flaps ends. At the inlet the slotted cavity is connected with the inner cavity of the nozzle, and at the outlet - with the supersonic duct part of the nozzle, with the possibility of changing the slotted cavity height in as per the engine modes of operation. Slotted cavity maximum height ratio to the slotted cavity minimum height makes 5...15.

EFFECT: invention allows to reduce noise of the jet turbine engine due to shielding the gas flow with a low-speed cold air flow.

1 cl, 3 dwg