FIELD: engines and pumps.
SUBSTANCE: gas turbine engine rotor includes blade with airfoil and root, as well as plate with a groove in which blade root is fixed. Blade root includes a pair of side parts adjacent to corresponding side parts of the groove in the plate, and lower part attaching the above side parts. A gap between lower part of blade root and lower part of groove in the plate is sealed by means of covering located on lower part of blade root and/or on lower part of the groove in the plate. Blade is provided with possibility of being brought into operation with working fluid medium, and blade airfoil has one or more inlet cooling channels for cooling fluid medium.
EFFECT: invention allows reducing cooling medium losses.
14 cl, 9 dwg
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