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

FIELD: engines and pumps.

SUBSTANCE: proposed engine comprises turbine second stage cooled nozzle vane with inner cavity. Vane inner cavity inlet communicates with compressor intermediate stage via cooling air flow rate control shutter while its outlet is communicated with turbine flow section upstream of second stage vane via second stage nozzle vane as well as via jet channel in nozzle vane inner flange and labyrinth seal between inner flange and turbine rotor intermediate disk. Relation of cooling air flow control shitters area in take-off conditions F_{shut.take-off} to cooling air flow control shitters area in cruising conditions F_shut.cruis. makes 3…5. Relation of labyrinth seal flow area between second stage nozzle vane and rotor intermediate disk F_lab with flow area of jet channels in nozzle vane inner flange jet channels F_jet equals 3…5.

EFFECT: higher reliability and efficiency.

2 dwg