GAS TURBINE ENGINE WORKING WHEEL OF ROTOR Russian patent published in 2019 - IPC F01D5/30 F01D5/02 

FIELD: turbines or turbomachines.

SUBSTANCE: invention relates to turbomachinery, in particular, it can be used in construction of impellers of axial compressors (mainly low-pressure axial compressors) gas turbine engines (hereinafter GTE). Rotor impeller of a gas turbine engine compressor contains blades with shelves mounted with dovetail shanks in the circumferential groove of the disk. Wheel is also provided with spacers mounted on the outer surface of the disk between the blades, and the opposite side surfaces of the blades are made in contact with the side surfaces of the adjacent spacers. Between the blades and the outer surface of the disk, as well as between the lower ends of the shanks of the blades and the surface of the circumferential groove gaps are made. From the side of one of the ends of each of the spacers, on the part of their side surfaces radial shoulder are made under the flanges of the blades, and from the side of the other end, on the inner surface of each of the flanges of the blades is made along the radial thrust to the outer surface of the disk. Radial grooves, each having a groove, are made along the circumference under each of the spacers on at least part of the end surface of the disk, from the side of one of the side walls of the circumferential groove. Each of the spacers is provided with two projections made on their inner surfaces, first of which are in contact with at least a part closest to the spacers conical with respect to the longitudinal axis of the rotor impeller of the compressor with the inner surface of another of the side walls of the circumferential groove. Second protrusions are made with an L-shaped profile and installed in the above-mentioned radial grooves with grooves. In the axial direction, each of the spacers is fixed relative to the disk by means of a spacer ring mounted in an annular groove, made around the circumference of the inner surfaces in the protrusions of the disk formed between the said radial grooves and in the projections of the L-shaped profile of the spacers.

EFFECT: simplification of mounting/dismounting of any of the blades in the rotor wheel of a gas turbine engine compressor.

1 cl, 6 dwg