Compressor rotor stage

Details Compressor rotor stage Compressor rotor stage

1978-01-09

1979-12-04

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

416190, 416196R, 416500, F01D 522, F01D 510

Patent

active

041770137

ABSTRACT:
A rotor blade stage for a gas turbine engine comprises an annular array of aerofoil blades. Each blade is provided with circumferentially extending platforms which are arranged so as to circumferentially spaced apart from the platforms of adjacent blades. Elastomeric dampers are interposed between adjacent blades and are so adapted that upon rotation of the array of blades, each of the elastomeric dampers is centrifugally urged into engagement with the radially inner faces of adjacent platforms of adjacent blades.

REFERENCES:
patent: 3266771 (1966-08-01), Morley
patent: 3451654 (1969-06-01), Johnson
patent: 3905722 (1975-09-01), Guy et al.
patent: 3918842 (1975-11-01), Longley et al.
patent: 3936230 (1976-02-01), Helmintoller et al.

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