COOLING SYSTEM OF GAS-TURBINE ENGINE IMPELLER Russian patent published in 2013 - IPC F01D5/08 

FIELD: engines and pumps.

SUBSTANCE: receiver interconnected with a secondary air supply cavity of a combustion chamber is arranged on an inner housing of a nozzle assembly. A cooling air swirling device is made in the form of a detachable right wall of the receiver with conical holes - nozzles in it. Two deflectors (right and left) of a disc with holes interconnected with channels in the disc and a moving blade are installed on the impeller disc. Two labyrinth seals located in hub and rim parts of the disc, as well as on internal and peripheral parts of the inner housing of the nozzle assembly; impeller disc bed, nozzle assembly inner housing, housing of the swirling device, left deflector of the disc, an annular gap between the swirling device and left deflector of the disc form an unloading cavity of the turbine.

EFFECT: improving cooling efficiency, reducing air leaks to a flow part, tuning of axial forces, simplifying and improving an assembly manufacturing technology.

3 cl, 4 dwg