Gas turbine engine lubrication system

Details Gas turbine engine lubrication system Gas turbine engine lubrication system

1993-04-05

1993-12-28

Gluck, Richard E.

Power plants

Combustion products used as motive fluid

With lubricators

184 611, F02C 706

Patent

active

052728684

ABSTRACT:
A lubrication system for a gas turbine engine includes first and second coaxially rotor shafts having at least one differential bearing disposed in outer and inner seats thereof. An annular first scoop extends axially from a first portion of the first shaft, and an annular second scoop extends axially from the inner seat of the second shaft. A plurality of first holes extend axially through the first shaft and radially below the first scoop, and a plurality of second holes extend axially through the inner seat of the second shaft and below the second scoop. An annular first shell extends axially between the second scoop and the first shaft from above the first holes. And, oil is injected under the first scoop for flow by centrifugal force from rotation of the first shaft through the first holes and along the first shell into the second scoop for flow through the second holes to lubricate the bearing.

REFERENCES:
patent: 3861139 (1975-01-01), Jones
patent: 4265334 (1981-05-01), Benhase, Jr.
patent: 4378197 (1983-03-01), Cattaneo et al.
patent: 4767271 (1988-08-01), Catlow
patent: 4790133 (1988-12-01), Stuart
patent: 4860537 (1989-08-01), Taylor
patent: 5079916 (1992-01-01), Johnson

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