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

FIELD: aircraft engineering.

SUBSTANCE: invention relates to aircraft engine building, namely, to aircraft turbojet engine low-pressure compressors. Third stage disc is made in the form of a single-piece element including a hub with a hole and equipped with a circular conical bearing element with an inclination angle and a radius of an output contact edge equal to response parameters of the said conical diaphragm of the shaft rear support journal. Disc includes a rim with slots for fitting the impeller blade roots and a body. Body is equipped in the upper part with circular shelves with ledges of a labyrinth seal. Disc body is made with variable in height section conically narrowing from the hub to the rim. Hub has an axial width exceeding thickness of the root part (3.5÷5.0) times. Average radius of the disc from the rotor shaft axis to the outer surface of the rim in conditional plane of symmetry of the body is (0.51÷0.73) of the radius of peripheral circuit of the engine flow section. Disc rim outer surface generatrix inclination angle to the rotor shaft axis makes φ=(5÷7)°. Slots are spaced along the perimeter of the disc rim with the angular frequency of Y_p=(7.3÷10.4) [unit/rad]. Longitudinal axis of the slot sole makes with the rotor shaft axis in projection on a plane a parallel to the rotor shaft axis, angle of α installation of the blade root defined in the range of values α=(18÷26)°.

EFFECT: technical result of the invention is improvement of efficiency and increasing life under all operating conditions of the compressor while increasing life of the disc without increasing the disc material input.

11 cl, 4 dwg