SECOND 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. Second stage disc of a turbojet engine low-pressure compressor rotor: the disc is composed as a single-piece element including a hub with a central hole, a rim with slots for fitting blade roots and a body equipped with inclined shelves. Disc body is made with variable in height section conically narrowing from the hub to the rim with gradient (G)_r.t. of reduced thickness in a specified direction equal to G_r.t.=(0.05÷0.07) [m/m]. 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 (0.46÷0.65) 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=(10÷15)°. Gradient of radial expansion of the rim G_rim is determined within the range of G_rim=(0.18÷0.26) [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=(5.4÷7.7) [unit/rad]. Longitudinal axis of the slot 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=(17÷25)°.

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 second stage impeller without increasing the disc material input.

19 cl, 4 dwg