Damping device for turbojet engine fan blades

Details Damping device for turbojet engine fan blades Damping device for turbojet engine fan blades

1982-12-03

1985-01-22

Powell, Jr., Everette A.

Fluid reaction surfaces (i.e., impellers)

Rotor having flow confining or deflecting web, shroud or...

Axially extending shroud ring or casing

416193A, 416500, F01D 510

Patent

active

044949090

ABSTRACT:
A damping device for the turbojet engine fan blades which includes a wedge placed between the platforms of the blades, the shanks of the blades, and the disc. The wedge consists of a hollow, bellows-shaped body fitted with an axial stop member, the body being inflated after mounting so that it takes up all the space between the platforms of the blades, the blade shanks and the teeth of the disc. The invention is used for damping device of turbojet engine blades.

REFERENCES:
patent: 2877980 (1959-03-01), Stalker
patent: 2936155 (1960-05-01), Howell et al.
patent: 3119595 (1964-01-01), Wilson
patent: 3612718 (1971-10-01), Palfreyman et al.
patent: 3905722 (1975-09-01), Guy et al.

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