ROTOR OF AXIAL GAS TURBINE Russian patent published in 2014 - IPC F01D5/08 

FIELD: engines and pumps.

SUBSTANCE: invention relates to gas turbine engines of aviation and ground use and may be applied in turbomachines, on the rotor of which there are blades fixed, as well as their facilities for cooling and clearance of deformations and vibrations. The rotor of the axial gas turbine comprises a rotor disc, cooled working blades arranged on the disc and a cover disc. The cover disc is installed on the rotor disc to form a circular cavity and is fixed by bayonet joints and pins. The circular cavity is connected by channels in the disc with channels in the base of the tail part of each blade. The rotor is also equipped with at least three ledges with slots made above bayonet joints. Bayonet joints are formed by hooks of the rotor disc and hooks of the cover disc. In the cover disc there are at least three holes coupled with slots. Pins are rigidly fixed in holes of the cover disc and are installed into slots of the rotor disc with a radial gap. Each hook of the cover disc is installed along the radius at the distance equal to 1.4-1.8 of the inner radius of the cover disc hub.

EFFECT: invention makes it possible to improve cooling of working blades, to increase reliability of a turbine rotor and to increase resource of a gas turbine engine.

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