ROTOR OF GAS TURBINE ENGINE COMPRESSOR, COMPRISING FACILITIES OF CENTRIFUGAL AIR INTAKE AND GAS TURBINE ENGINE Russian patent published in 2013 - IPC F01D5/06 

FIELD: engines and pumps.

SUBSTANCE: rotor of a gas turbine engine compressor comprises at least two coaxial discs, facilities of centrifugal air intake and radial ribs. Blades are installed on discs. Discs are connected to each other substantially with a cylindrical coaxial rotation wall. Facilities of centrifugal air intake comprise air passages crossing the wall and opening into a circular chamber. The chamber is formed inside the wall between discs. Radial ribs are arranged on one of the discs. Ribs are spaced in axial direction from the disc and are substantially levelled with the wall passages in the radial direction. Ribs are connected only by one of their axial ends with support facilities fixed on this disc. Also the object of this invention is a gas turbine engine comprising the above specified compressor rotor.

EFFECT: invention makes it possible to avoid losses of head and to reduce consumption of a gas turbine engine, and temperature of captured air.

13 cl, 5 dwg