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

FIELD: engines and pumps.

SUBSTANCE: claimed rotor shaft section comprises the housing with the wheel space and is composed by the upstream low-pressure compressor rotor shaft second section. Claimed section comprises the third stage disc and the cylindrical spacer provided with the flange. 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 rim has the set of grooves for jointing with the rotor vanes arranged at the side opposite the setting. Lengthwise axis of every said groove makes the angle α=(19÷28) degrees 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. Said disc rim features the radius with gradient of radial expansion G_vol increasing in the working fluid flow direction. Optionally, the third stage disc rim features the radius increasing toward the section outlet while the generatrix of the disc outer face makes with the shaft axis in axial plane of the final angle φ=(3÷9) degrees.

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

10 cl, 2 dwg