FOURTH 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 hub with a central hole, a rim with front and rear shelves separated by an annular slot and a body. Rim front shelf is provided with a circular element with labyrinth ledges, and the disc circular element end face is made for a non-detachable connection with a mating circular connecting element of the third stage. Disc body is made with variable in height section narrowing from the hub to the rim. Hub has an axial width exceeding thickness of the root part (5.5÷7.3) 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 (0.54÷0.78) of the radius of peripheral circuit of the engine flow section.

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 last fourth stage impeller without increasing the disc material input.

3 cl, 1 dwg