GAS TURBINE ENGINE (VERSIONS) Russian patent published in 2009 - IPC F02C5/04 

FIELD: engines and pumps.

SUBSTANCE: gas turbine engine incorporates combustion chambers, fuel feed and igniting devices, bypass channels made in the turbine housing and furnished with inlet and outlet nozzles accommodating fuel feed devices and vaned rotor. The rotor vanes end faces accommodate flat shroud rings. Inlet sector openings arranged in the housing and partially aligned with the outlet sector openings adjoin the inner edges of the rotor vanes, while the aforesaid outer openings adjoin the outer edges of the said vanes. Bypass, outlet, inlet and outlet sector openings adjoining the rotor vanes inner edges are arranged in turbine housing along the rotor run. In compliance with the other version of this invention, the bypass channel openings adjoin the rotor vanes outer edges. Note here that the bypass channel inlets are aligned with the outlet sector openings, while their outlets are arranged between the said bypass channel inlet openings and output sector openings.

EFFECT: higher specific power, reliability, smaller weight and sizes.

9 cl, 7 dwg