FIELD: engines and pumps.
SUBSTANCE: gas turbine engine disk incorporates the blades arranged in a tapered channel and fastened therein by hammer-like appliances. Every blade has a platform with its outer surface limiting the gas flow channel and its inner surface is furnished a front and rear stiffening ribs arranged in planes perpendicular to the disk rotation axis. The disk edges are furnished with a front and rear tight rings arranged radially nearby the said ribs. The rear stiffening rib thickness exceeds that of the rear ring.
EFFECT: reliable attachment of the blade to the gas turbine engine rotor disk.
3 cl, 2 dwg
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