TURBOJET AIRCRAFT ENGINE Russian patent published in 2020 - IPC F02K3/10 

FIELD: engine building.

SUBSTANCE: invention relates to aircraft engine building and can be used in development of jet engines intended for flight of aircrafts in atmosphere due to implementation of detonation thermodynamic cycle with high repetition rate of pulses and self-maintenance of fuel detonation process. In the known turbojet aircraft engine comprising an air intake, a gas generator, a nozzle and a detonation device adjacent to the outer engine housing, upon a proposal, detonation device is made in the form of a longitudinal annular combustion chamber with an inlet air channel from the engine air intake and an axial swirler at its inlet, flow part of the chamber is separated from the flow part of the gas generator, and on the inner side of the external wall of the annular combustion chamber there are serially arranged along the longitudinal axis of the engine belts of fuel and air mixers with ignition devices in them, wherein perimeter of each belt there are at least three air and fuel mixers with ignition devices, made in the form of tube sections, the inputs and outputs of which are directed along the air flow direction coming from the axial swirler, and axes of fuel nozzles in mixer are directed at an angle to direction of air flow in it, besides, each separate belt of mixers is tuned to its normalized mode of pulse detonation.

EFFECT: application of the engine allows increasing fuel efficiency up to 30 %, qualitatively increasing flight speed up to 5 M, providing constant specific fuel pulse 2,000–2,500 s at operation on hydrocarbon fuel without significant increase of dimensions and weight, increasing efficiency, reducing cost due to simplification of design.

6 cl, 3 dwg