FIELD: engines and pumps.
SUBSTANCE: invention relates to turbo machines building and can be used in designs of multistage axial compressors and gas turbine engines turbines, power plants, steam- and hydro turbines. Gas turbine engine compressor rotor comprises discs, connected to each other, with working blades installed on them. On disc rim part, at least, two working blades rims are installed, and between working blades rims circular recesses are arranged with locks of “circular dovetail” type made in them, in which segmented inserts are mounted and locked against movement in circumferential direction by retainers. Segmented inserts form required shape of disc outer surface.
EFFECT: invention allows to improve reliability and reduce turbomachine manufacturing labor intensity, increase service life and improve turbomachine specific characteristics (specific power, thrust, fuel consumption).
1 cl, 3 dwg
