FIELD: power machine building.
SUBSTANCE: invention relates to rotor of gas turbine engine compressor rotor comprises disc, on outer surface of which annular groove is made, in which dovetails of "dovetail" type of blades with flanges are installed, fixed in circumferential direction by means of inserts with retainers installed in annular slot and connected to each other by means of threaded connection. Rotor impeller comprises spacer flanges, each of which is installed between flanges of adjacent blades, above insert. On external surface of each of inserts as a whole with it is made on radial ledge with through hole forming with through hole of insert a single radial channel, in which the above retainer is installed. In the remote flanges there are through radial holes, into which radial projections are connected, which are connected to the first ones by means of threaded connections.
EFFECT: technical result achieved when using present invention is simplification of mounting / dismantling any of blades in rotor of compressor of gas turbine engine compressor and improvement of its reliability due to exclusion of mounting slots.
3 cl, 5 dwg
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