TURBOJET LOW-PRESSURE COMPRESSOR ROTOR SHAFT SECTION (VERSIONS) Russian patent published in 2016 - IPC F04D29/32 F01D5/06 

FIELD: engines and pumps.

SUBSTANCE: claimed section comprises the housing with the wheel space is composed by the upstream low-pressure compressor rotor shaft first section. Claimed section comprises the rotor shaft front bearing journal, first and second stage discs and cylindrical spacer. Said section represents of single-piece structure. Every disc is composed of a single-piece element including the rim changing into circular web reinforced by the hub provided with the central bore. The disc of every disc is provided with the set of grooves for clutch with the rotor working blades. Lengthwise axis of every said groove makes the angle α with the rotor axis in projection on conditional axial plane, perpendicular to the radius drawn through the groove axis central point. The grooves are uniformly spaced apart in the disc periphery. The rim of every disc features the radius increasing from the section inlet to outlet with the gradient of radial expansion makes G_1rim = (0.31÷0.52) [m/m] and G_2rim = (0.23÷0.33) [m/m]. Note also that the disc rim of the first stage is engaged asymmetrically with the disc web to make different-arm inclined flanges. The first stage disc radius from rotor axis to the rim outer surface in the disc web medium plane makes (0.32-0.55) of that for engine flow section peripheral outline and (0.42-0.70) for the second stage disc.

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

19 cl, 2 dwg