DOUBLE-FLOW TURBINE JET ENGINE Russian patent published in 2020 - IPC F02C7/06 F01D21/04 

FIELD: machine building.

SUBSTANCE: invention relates to gas turbine engines and can be used in supports of rotors of axial fans of aircraft double-flow turbojet engines. Double-flow turbojet engine, in which housings of bearings 6 and 8 are fixed on intermediate housing 2. Housing 6 of first bearing 5 is equipped with flange 10 fixed in bore 11 of the intermediate housing in axial direction by means of pressure flange 12 fixed by screws 13 in intermediate housing 2. In radial direction flange 10 is fixed in bore 11 with shear pins 14 ("Weak Link") with provision of radial gap 15 between outer cylindrical surface of flange 10 of housing of first bearing and inner cylindrical surface of bore 11, wherein pins 14 and screws 13 axes are parallel to the fan rotor rotation axis 3 Sealing of oil cavity 9 of the support along the mating surfaces of flange 10 of housing 6 of first bearing 5 with intermediate housing 2 is provided by elastic ring 17.

EFFECT: thus, proposed design of support of rotor of fan of double-flow turbojet engine excludes rotor displacement in axial direction and provides possibility of shift of first radially-thrust ball bearing of its support in radial direction without breaching tightness of oil cavity, that minimizes considerable destruction of engine structure at break of rotor blade of its fan.

1 cl, 3 dwg