TURBOJET ENGINE Russian patent published in 2023 - IPC F02K3/06 F02C7/06 F01D21/04 

FIELD: aircraft engines.

SUBSTANCE: turbojet engine containing a fan, a fan shaft and a drive shaft, the fan shaft being installed in the first and second bearings, the second bearing comprising a housing containing a radial annular flange made on an axial cylindrical section, and an inclined annular section directed radially inward relative to the drive shaft , the body of the second bearing is connected to the fixed element of the first bearing on one side, and a ring is installed in the recess of the fan shaft using a tenon-groove fastening, unlike the known design, the housing of the second bearing is additionally provided with a central radial annular flange on the outer surface directed radially upwards relative to the leading shaft, and the radial annular flange and the central radial annular flange are mated with a radial stiffener, on the other side, the housing is connected with the help of fitting bolts passing through the radial annular flange and the central radial annular flange of the second bearing housing with the support flange of the outer ring of the bearing housing, the shaft ring installed with oil agitation capability due to the location of its radial outer surface further from the axis of rotation of the engine than the inner radial surface of the inclined annular section, and the ring is provided with an outer first conical surface directed towards the inclined annular section of the bearing support housing, and a second conical surface directed towards the inner ring of the bearing, the shaft ring is provided with through holes, the axis of which is directed to the inner surface of the axial cylindrical section.

EFFECT: improved reliability of operation of the turbojet engine.

2 cl, 1 dwg