ROTOR OF COMPRESSOR OF GAS TURBINE ENGINE AND GAS TURBINE ENGINE Russian patent published in 2013 - IPC F01D5/08 

FIELD: engines and pumps.

SUBSTANCE: rotor of a compressor of a gas turbine engine comprises at least two coaxial discs, on which blades are installed, and which are connected to each other with a substantially cylindrical coaxial wall of rotation and facilities of centrifugal air intake. Facilities of air intake comprise air passages crossing the wall and opening into a chamber formed inside the wall of rotation between two discs. The guide wall for air is installed in the chamber and comprises substantially a cylindrical part. The cylindrical part stretches along the wall of rotation at the small radial distance from it to form a circular passage together with this wall for axial flow of air going out from passages to one of rotor discs. Another subject of this invention is a gas turbine engine, for instance, a turbojet or a turboprop aircraft engine, comprising a compressor rotor described above.

EFFECT: reduced air flow and lower consumption of turbomachines.

14 cl, 5 dwg