Retractable damping device for blades of a turbojet

Details Retractable damping device for blades of a turbojet Retractable damping device for blades of a turbojet

1983-05-18

1985-05-14

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, F01D 522

Patent

active

045169101

ABSTRACT:
A retractable damping device for the blades of a turbojet, located between two consecutive blades against the lower face of the platforms of said blades. The damping element, mounted to rotate by one of its ends in the middle part of the space formed between the blades and a rotor disk positioned along an axis perpendicular to a radial axis of the disk, exhibits an upper part which constitutes a projecting dihedral that takes the form of the protruding dihedral consisting of the platforms of the two consecutive blades under the action of centrifugal force.

REFERENCES:
patent: 3112915 (1963-12-01), Morris
patent: 3266771 (1966-08-01), Morley
patent: 3318573 (1967-05-01), Matsuki et al.
patent: 3709631 (1973-01-01), Karstensen et al.
patent: 3972645 (1976-08-01), Kasprow
patent: 4101245 (1978-07-01), Hess et al.
patent: 4177013 (1979-12-01), Patterson et al.
patent: 4182598 (1980-01-01), Nelson
patent: 4183720 (1980-01-01), Brantley

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