AIRCRAFT TURBOJET ENGINE Russian patent published in 2021 - IPC F02K3/00 F02K3/06 F02K5/00 

FIELD: aviation.

SUBSTANCE: invention relates to aircraft turbojet engines. The proposed aircraft turbojet engine contains an air intake 1, in a cylindrical body 2 along the axis of which a shaft 3 is installed, which is connected in series with a multistage compressor 4 and a turbine 6, as well as a pressurization unit, a combustion chamber 5, a kinematic connection with a start drive 9 and an outlet device 7. The pressurization unit is made autonomous, installed in the air intake 1 along the axis of the housing 2 by means of three radial brackets 10 through the gap in front of the compressor 4 and is not connected to the shaft 3, the pressurization unit consists of single assembly: an electric motor 11, a gearbox and a two-blade propeller 12. The electric motor 11 is connected to the onboard electrical network through the body 16 of the autonomous manual step control, combined with the body 18 of the aircraft turbojet engine control. The space between the plane of rotation of the propeller 12, the wall of the cylindrical body 2 and the plane of the first stage of the compressor 4 is a receiver 14, and a pressure gauge 15 is connected to the inner space of the receiver 14.

EFFECT: invention makes it possible to increase the compression ratio of the compressor and improve the characteristics of the turbojet engine.

1 cl, 3 dwg