TURBINE ROTOR Russian patent published in 2018 - IPC F01D5/08 F02C7/12 F01D5/30 

FIELD: motors and pumps.

SUBSTANCE: invention relates to turbine rotors of gas turbine engines for aviation and ground applications. Rotor of the turbine contains a disc of a turbine, on the rim of which the upper bayonet joint is fitted with a disk deflector, the hub of which is made with a cylindrical elastic element and with a slotted cavity with respect to the cylindrical elastic member of the disc. On the shank of the cylindrical elastic element of the deflector, radial projections directed toward the axis of the rotor of the turbine are made. On the elastic element of the disk, radial projections directed from the axis of the rotor of the turbine are formed, forming, together with the radial projections of the deflector, the lower bayonet connection fixed in the circumferential direction by the locking lock. Locking lock is provided with an axial plate-like projection, with the possibility of plastic deformation of the plate-shaped projection in the radial direction on the end surface of the shank of the cylindrical elastic element of the deflector. Radial height of the locking lock is equal to the radial height of the slotted cavity between the elastic elements of the disc and the deflector, and the locking lock is made T-shaped in plan, and the number of radial projections of the deflector in the lower bayonet connection is a multiple of or equal to the number of axial protrusions of the deflector in the upper bayonet connection.

EFFECT: invention makes it possible to improve the reliability of the turbine rotor and reduce its mass.

1 cl, 5 dwg