DOUBLE-FLOW GAS TURBINE ENGINE Russian patent published in 2011 - IPC F02C7/12 F01D3/02 

FIELD: engines and pumps.

SUBSTANCE: double-flow gas turbine engine includes high pressure compressor, annular supply header, inter-labyrinth cavity adjacent to side surface of peripheral part of disc of high pressure turbine, which is separated from flow part of turbine with labyrinth seal, with inter-disc cavity separated from inter-labyrinth cavity with labyrinth seal and interconnected with flow part of turbine through cavity of slot channel in the area of peripheral part of disc of low pressure turbine. Compressor cavity is connected through the channel passing through inner cavities of blades of LP turbine nozzle diaphragm. Inter-disc cavity is divided into discharge cavity of HP turbine, discharge cavity of LP turbine, which are separated from each other with a wall fixed along outer diametre on nozzle diaphragm of LP turbine and labyrinth seal on the side of inner diametre of wall and cavity of slot channel, which is separated from discharge cavity of LP turbine with labyrinth seal. Discharge cavity of HP turbine is connected to cavity of slot channels with transit tubes. Discharge cavity of LP turbine is interconnected with annular supply header through channels.

EFFECT: invention provides the change and adjustment of axial forces acting on turbine rotors.

9 cl, 4 dwg