FIRST 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. Disc is composed as a single-piece element including a rim, a hub with a central hole and a body with variable in height cross section conically narrowing from the hub to the rim. Hub is made integral with the rotor shaft front bearing journal developed on one side to the LPC inlet. Average radius of the disc from the rotor axis to the outer surface of the rim in conditional plane of symmetry of the body is (0.37÷0.49) 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=(17÷25)°. Gradient of radial expansion of the rim G_rim is determined within the range of G_rim=(0.28÷0.38) [m/m]. Slots for fitting blade roots are uniformly spaced apart along the perimeter of the disc rim with the angular frequency of Y_p=(4.6÷6.2) [unit/rad]. Longitudinal axis of the slot sole makes with the rotor shaft axis angle of α installation of the blade root defined in the range of values α=(16÷22)°. Lateral faces of the slot are made opposite and inclined to each other to form angles β between the side face and the slot sole equal to β=(63÷78)° and are conjugated with the sole through roundings with a radius r equal to (0.33÷0.38) of width of the slot head.

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

23 cl, 5 dwg