FIELD: mechanical engineering; gas-turbine engines.
SUBSTANCE: invention relates to compressors of gas-turbine engines of aircraft and ground application. Novelty is that in rotor of compressor with working blades secured by leaf lock with bending on lock shank to rotor axle bending disk rim, said lock arranged on last working blade of last disk of compressor is provided with T-shaped projection from side opposite to bend, and cavity with surfaces enclosing lock shank bend is made in working ring adjoining disk rim.
EFFECT: improved reliability of compressor by excluding deformation of lock when engine is operating.
4 dwg
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