FIELD: mechanical engineering. SUBSTANCE: proposed gas-turbine engine rotor blade installed in slot of rotor disk has profile, flat made integral with profile and dovetail lock made integral with said flat. Lock has neck of minimum cross section area located between pair of projecting parts of dovetail lock whose shape permits getting into disk slot. Each projecting part has outer surface pointed outwards for engagement with corresponding inner surfaces of slot in disk between corresponding borders of contact, and relief grooves made in projecting parts within the limits of contact. Gas-turbine engine rotor with rotor disk contains great number of posts distributed over periphery and separated by corresponding dovetail slots to receive corresponding locks of blades. Each post has opposite first and second projecting parts with inner surfaces pointed radially inwards for engagement with corresponding outer surfaces of blade locks within the limits of contact, and outer surfaces of relief grooves located in projecting parts outside the limits of contact. EFFECT: reduced contact stresses. 20 cl, 3 dwg
