TURBOJET ENGINE Russian patent published in 2023 - IPC F02C7/32 F02C7/36 

FIELD: aviation engineering.

SUBSTANCE: aircraft turbojet engine (TJE) containing a drive unit. TJE contains a fan, a low-pressure compressor, a high-pressure compressor, between which there is a separation housing, a low-pressure turbine, a high-pressure turbine, a combustion chamber, a drive assembly box (DAB) with drive assemblies, an engine nacelle having an asymmetrical shape relative to the X axis and a symmetrical shape relative to the Y axis. With the ability to select torque from the high-pressure compressor shaft, the TJE contains a bevel gear of the central drive and a bevel gear of the angular bevel drive, while the central spur gear of the DAB, the hollow power rack of the separating housing and the splined shaft passing inside it are placed on the axisβ, located at an angleα equal to 60°…75°, clockwise or counterclockwise relative to the vertical Y axis, and the drive units, including the largest units, such as the aircraft generator and starter, as well as the spur gears driving these units, are located to the right and left of the central spur gear of the control unit, and the distance B between the maximum contours of the dimensional units is equal to 5…50 mm. The width of the crown of the central cylindrical gear is 1.0…1.1 from the width of the spur gear of the kinematic chain, which transmits the greatest torque. The widths of the spur gears ensure the transmission of torque to drive the units of the kinematic chain located to the left or right of the central spur gear with the required safety margin.

EFFECT: increasing the TJE reliability, obtaining the optimal shape of the engine nacelle with minimal air resistance, reducing the number of bevel gears, which lowers the labor intensity of manufacturing, and the rational placement of the largest units on DAB makes it possible to obtain gears with an optimal width to obtain the minimum mass of DAB.

9 cl, 7 dwg