GAS TURBINE ENGINE WITH BIROTATE FAN Russian patent published in 2018 - IPC F02K3/72 F02C3/73 F01D11/24 F01D21/06 

FIELD: engines and pumps.

SUBSTANCE: invention relates to gas turbine engines with a birotate fan for aviation applications. Gas turbine engine with a birotate fan comprises booster stages placed between the impellers of the birotate fan, as well as a birotate turbine connected by shafts to the impellers of the birotate fan. Blades of the front and the rear impellers of the birotate fan are made rotable around the radial axis, the booster birotate stages at the outlet are made with a diffuser channel, the first blade of the external rotor of the birotate turbine is made with inlet and outlet edges convex at the gas turbine engine longitudinal section in the axial direction, and the labyrinth seal between the external rotor and the stator of the birotate turbine is made with inner and outer tiers, with an intermediate air cavity between the tiers connected at the inlet with the intermediate stage of the compressor, and is equipped with an active control system for the radial clearance of the outer tier of the seal.

EFFECT: allows to increase the reliability, economy and to reduce the weight of the gas turbine engine.

1 cl, 4 dwg