FIELD: aviation.
SUBSTANCE: invention relates to turbojet or turbo-propeller aircraft. Turbomachine blade wheel comprising a disc, the outer periphery of which is formed with at least one seat for installation of blade roots and insert (7) installed between each blade root and the seat bottom. Insert (7) contains at least one element (17) of bistable by position type, which can be in the first stable position of mounting or dismounting, wherein the said element has no force on the blade root, and in the second stable position, wherein the said bistable element has a radial force on the blade foot. Insert (7) also contains at least one elastic damping element (12) installed between the seat bottom and the blade root.
EFFECT: invention provides higher stability of the blade wheel.
10 cl, 7 dwg
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