FLOW MIXER WITH VARYING SECTION FOR DOUBLE-CIRCUIT TURBOJET ENGINE OF SUPERSONIC AIRCRAFT Russian patent published in 2012 - IPC F02K1/28 F02K1/38 F02K1/46 

FIELD: machine building.

SUBSTANCE: flow mixer includes a central circular body around its longitudinal axis, a primary circular shell coaxially surrounding the central body with formation of primary circular channel and secondary circular shell coaxially surrounding the primary shell with formation of secondary circular channel coaxial with the primary channel. Also the mixer includes an annular nozzle centred along the longitudinal axis and is located in the longitudinal direction on a line with the secondary shell. The nozzle has a multitude of holes for outdoor air intake that are distributed over its entire circumference and opening into an area of convergence of streams. The holes are in the primary and secondary channels and inside the holes are blades capable of moving between two different positions: a closed position in which they obstruct the nozzle holes and an open position in which they open up these holes and pass radially into the nozzle. All blades have a common azimuthal component in the same direction to make the outdoor air rotate that enters the convergence zone when the blades are in the second position. Additionally, the mixer comprises a multitude of longitudinal grooves occupying a part of the central body with all the grooves having a common azimuthal component in the same direction which is opposite to the one of the azimuthal component of the blades. Another subject of the invention is a turbojet engine comprising a flow mixer described above.

EFFECT: invention reduces the jet noise from the nozzle during take-off without adversely affecting the turbojet engine thrust.

4 cl, 6 dwg