FIELD: engines and pumps.
SUBSTANCE: gas turbine rotor comprises drum and blades with their root retained in the drum ring groove and two stiffness ribs with lateral bearing surfaces. Lateral bearing surfaces of stiffness ribs can retain the platform axially at the drum and decreased air circulation. Platform circular edges gave cross-platform bearing surface resting on adjacent cross-platform bearing surface. The platform occupies ring sector and has bores spaced apart in circle. Every said bores can receive blade root to make a multiblade platform separated from said blades. Invention covers also the blade fitted with the help of aforesaid platform at the drum and including the blade and root with blade platform arranged there between. Another invention of this set relates to vaned rotor, drum with ring groove to retain blade root and multiple above said platforms each being retained multiple blades in said drum. Other invention of the set relate to compressor and gas turbine incorporating aforesaid rotor.
EFFECT: simplified assembly/disassembly.
9 cl, 14 dwg
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