GAS TURBINE ENGINE GAS GENERATOR Russian patent published in 2017 - IPC F02C7/18 F02C7/12 F01D5/08 F01D5/18 

FIELD: engine devices and pumps.

SUBSTANCE: gas turbine engine gas generator includes an axial compressor, a combustion chamber, a high-pressure turbine with cooling working and main discs with holes made on its flange and carrying disc thereon with formation of annular cavity between them. The circular cavity communicates with inner spaces of cooled working blades at outlet, with the flow part of compressor intermediate stage at the inlet through the holes in the main disc flange and which is suitable by pressure level of compressor intermediate stage through shaft inner space connecting compressor rotors and a turbine. There is a radial annular gap between a cover disc and the main disc flange in which cavity a running twist device which is connected to secondary air zone of the combustion chamber at the inlet and the cavity of the radial annular gap at the outlet transforming into interdisc annular cavity.

EFFECT: increased of pressure of high-pressure turbine working blades cooling system during takeoff from the compressor intermediate stage by using air mixture which is taken from the compressor intermediate stage with air taken from the secondary air zone of the combustion chamber, increased service life of the cover disc with simultaneous reduction of its weight due to elimination of ribs.

2 dwg