TURBOJET ENGINE Russian patent published in 2009 - IPC F02K1/06 

FIELD: engines and pumps.

SUBSTANCE: invention relates to aircraft engineering, particularly to aircraft engine production. Turbojet engine comprises high- and low-pressure compressors, combustion chambers with front devices, daisy mixer and monoblock jet nozzle. Said mixer has shroud ring jointed, along ring edges, to nozzle. The latter is made up of encased lengthwise plates, the casing being jointed, via adapter, to shroud ring. Casing accommodates actuators of nozzle angular-radial motion and nozzle plate radial-diametral motion. Nozzle actuators represent two drive rings linked up in diametral plane. Each ring seats on the housing circular ledge and has toothed rim arranged along its edges, said rim being in mesh, via gear shaft, with servo drive. Inner spherical surface of drive rings makes base surface to mate cam-ring surface. Each drive ring is furnished, every 90°, with two opposed drive pins that enter the cam-ring drive slots. Cam-rim inner surface feature cylindrical recesses to accommodate, at least eight pins with ears to turn radially therein and be linked up with driven plates. Pin era axes are aligned with drive ring jointing plane. Nozzle plate actuators comprise annular pneumatic cylinder pin-jointed to rim-cam end face. Pneumatic cylinder rods are coupled with drive plates and furnished with drive pins, on their outlet side. Driven plates have drive slots. Lateral sides of driven plates and mating drive plates feature incline of lateral sides through 6° to 8° from hinge joint axis to provide maximum diametre of nozzle exhaust end face. Outside of annular pneumatic cylinder is closed by corset daisy collet-type cartridge with its petals in sliding contact with nozzle plates in outlet area.

EFFECT: higher operating performances.

7 dwg