FIELD: mechanical engineering; turbojet engines.
SUBSTANCE: invention relates to high-pressure compressors of turbojet engines and makes it possible to provide conformity to some criteria related to disk with system of blades, for instance, vibration stability, service life and loss of blades. Invention concerns coupling between some first part D1 terminating in first ring 12 provided with set of holes and cutouts. Axis of first ring is centered on axis of rotation of compressor rotor to provide possibility of its connection to inlet part of compressor rotor and system formed by second part D2 of rotor secured on third part 30 of rotor. Second part D2 forms inlet part of compressor rotor terminating in second ring with holes behind in direction of flow. Third part terminates in third ring 32 before in direction of flow provided with holes. Second and third rings are arranged one opposite to the other to provide registering of their holes, said rings being interconnected by first fasteners. First circular ring 12 is arranged before in direction of flow and opposite to system formed by second and third part of rotor to provide enclosing of first fasteners of system formed by second and third parts of rotor by said cutouts and to arranged at least some of holes of first ring opposite to holes made in system formed by second and third parts of rotor. Second fasteners lock first circular ring 12 on system formed by second and third parts of rotor.
EFFECT: provision of sufficient service life and resistance to loss of blades.
12 cl, 8 dwg
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