GAS TURBINE ENGINE Russian patent published in 2012 - IPC F02C7/12 

FIELD: engines and pumps.

SUBSTANCE: bypass gas turbine engine comprises high-pressure compressor with rotor and stator, unloading chamber adjoining the compressor, combustion chamber, cooled nozzle vanes, high- and low-pressure turbines with wheel space, interdisk cavity and its cooling channel communicated with inlet feed manifold. Interdisk cavity cooling cannel is separated from turbine wheel space by labyrinth seal and slot clearance. Interdisk cavity cooling channel feed manifold is communicated with compressor unloading space via low-pressure turbine nozzle vane cooling system and engine second stage heat exchanger. Nozzle vanes are provided with inner cavities communicated with cooling system. Interdisk space cooling channel manifold is separated from inner cavities of cooled nozzle vanes and communicated with vanes cooling system inlet manifold via transit tube arranged inside said vanes with clearance relative to their walls. Transit tubes have parts with calibrated flow section. Perforated deflector is arranged between transit tube and vane walls. Said deflector is made up of shell embracing lather part of vane inner cavity cross-section with congruent approximation to cavity inner surface to make clearance sufficient for washing walls by cooling air on the side of cavity and discharging said air via slot in vane rear. Interdisk cavity cooling channel is made up of cooling chambers of central and root sections of hiogh- and low-pressure turbine disks separated by labyrinth seal.

EFFECT: higher reliability, longer life.

2 cl, 4 dwg