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

FIELD: engines and pumps.

SUBSTANCE: turbojet engine low-pressure compressor rotor shaft represents a drum-disc design composed of a four-stage, hence, four-disc structure. The shaft is made in three steps. At the first stage, the assembly units, i.e. the shaft front and rear bearing journals, discs and spacers. At the second stage, said unit are assembled to three mounting sections to be coupled to compose the rotor shaft. Every section is a non-separable structure. The rotor shaft front bearing journal, first stage disc, second stage disc and spacer are fitted in the first section and coupled therein. The second section comprises the third stage disc with the rotor shaft rear gearing journal and spacer permanently jointed thereto. The third section makes the fourth stage disc. At the third stage, mounting sections are coupled via the spacers to complete the rotor shaft assembly at articulation of the second section spacer with the third section. The discs of all stages are composed of a single-piece element including the rim changing into a circular web with the hub provided with the central bore. Said rim is inscribed in the conditional surface of truncated cone diverging in working fluid flow direction with intermediate radius at the disc web conditional plane equal to design radius of the engine setting inner outline in said section if measured from the shaft axis to the rim outer surface. Rim of every disc has grooves for rotor vanes to be uniformly distributed over the edges and inclined to the shaft axis. The amount and frequency of grooves location are increased in direction of working fluid flow from disc to disc, from the first and third section. Besides, the groove lengthwise axes are located in the disc rotor at claimed angular frequency and inclination to the rotor axis in the projection on the arbitrary axial plane, perpendicular, to the radius drawn through the groove axis central point.

EFFECT: perfected manufacture parameters, higher efficiency and gas dynamic stability, longer rotor shaft life without increase in the input of material.

13 cl, 2 dwg