TURBOJET LOW-PRESSURE COMPRESSOR LAST STAGE DISC Russian patent published in 2015 - IPC F04D29/32 F01D5/06 

FIELD: engines and pumps.

SUBSTANCE: claimed disc is composed of monoelement including the ring changing into circular web reinforced with hub which has the central bore. Said ring is asymmetrically connected with disc web to make different-arm circular conical inclined flanges. Disc web can be articulated via spacer with the disc flange of the previous stage. Disc ring features the radius increasing toward working fluid flow in low-pressure compressor axial cross-section and the angle of the ring outer surface generatrix relative to rotor shaft axis. Disc ring is provided with the system of grooves for securing of blades. Lengthwise axis of every groove makes with rotor shaft axis in projection on arbitrary axial plane perpendicular to the blade root radial axis the pitch angle α of the blade butt. Grooves are uniformly spaced apart in disc perimeter at claimed angular frequency and provided with side faces in cross-section to make the element of lock joint with the blade butt.

EFFECT: higher efficiency and longer life under all operating conditions of the compressor last stage impeller without increase in disc material input.

4 cl, 3 dwg