ROTOR OF AXIAL GAS TURBINE Russian patent published in 2018 - IPC F01D5/30 F01D5/08 

FIELD: engines and pumps.

SUBSTANCE: rotor of an axial gas turbine belongs to aircraft engine construction, namely to the design of gas turbine engine turbines. Rotor of the axial gas turbine comprises a main disc with cooled working blades mounted thereon and a cover disc attached to it by a bayonet connection and forming channels for supplying the cooling air to the shank part of the blades. In the rim of the main disc, at least one radial slot is made between the working blades, a reciprocating slot is made in the cover disc forming a cavity with the slot of the disc, where a lock is installed. On the cover disc, grooves are provided on both sides of the slot in the transverse direction, wherein each lock is provided with a plate contacting with the middle portion thereof, and the ends of the plate are located in the grooves and contact the adjacent blades.

EFFECT: invention makes it possible to reduce the stresses in the discs occurring in the area of the axial holes in the discs during the engine operation, and thus improve the reliability of the rotor and the axial gas turbine as a whole.

1 cl, 2 dwg