Bearing cavity and method of evacuating oil therefrom
AssigneePratt & Whitney Canada Corp.
InventorsJean-Sébastien Dick, Daniel Alecu, Kenneth Parkman
Life of this patent
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Abstract
The bearing chamber assembly can have a bearing chamber wall extending annularly and having a drain aperture, the drain aperture connecting a scavenge line, and a baffle, the baffle having an apertured sheet connected at one end to the bearing chamber wall, extending from the connected end over and past the scavenge port to a free edge, the free edge spaced from the bearing chamber wall.
Claims20
A bearing chamber assembly for an aircraft engine, the bearing chamber assembly comprising a bearing chamber wall extending annularly and having a drain orifice at a bottom of the bearing chamber wall, the drain orifice connecting a scavenge line, and a baffle, the baffle having an apertured sheet and extending along a circumferential direction relative to an axis of the bearing chamber wall from a first circumferential edge to a second circumferential edge, the first circumferential edge connected downstream of the drain orifice to the bearing chamber wall, the baffle extending from the first circumferential edge in an upstream direction, over and past the drain orifice to the second circumferential edge being a free edge, the free edge spaced from the bearing chamber wall.
A method of operating a gas turbine engine, the method comprising rotating a rotor within a casing of the gas turbine engine via bearings, supplying the bearings with oil, capturing the oil exiting the bearings in a bearing cavity, the rotation of the rotor entraining a standing circumferential flow of air with oil droplets in the bearing cavity, collecting oil droplets carried by the air along a baffle generally extending along a circumferential direction relative to an axis of the bearing cavity from a first circumferential edge to a second circumferential edge, the first circumferential edge connected downstream of a scavenge port to a bearing chamber wall, the baffle extending from the first circumferential edge circumferentially and axially upstream, over and around the scavenge port to the second circumferential edge being spaced apart from the bearing chamber wall, collected oil droplets being pushed along a radially-inner surface of the baffle, reaching apertures in the baffle, moving across the apertures and into the scavenge port.
A gas turbine engine comprising in serial flow configuration a compressor, a combustor, and a turbine, the compressor and turbine having rotating components mounted on at least one rotor, said rotor being rotatably held in the gas turbine engine via at least one bearing housed in a bearing chamber, an oil delivery system including an oil recirculation loop to send oil to the bearing, to be captured in the bearing chamber and guided into a scavenge line across a scavenge port, the scavenge port at a bottom of the bearing chamber;
- and a baffle, the baffle having an apertured sheet extending along a circumferential direction relative to an axis of a bearing chamber wall from a first circumferential edge to a second circumferential edge, the first circumferential edge connected to the bearing chamber downstream of the scavenge port, the apertured sheet extending from the first circumferential edge in an upstream direction, over and past the scavenge port to the second circumferential edge being a free edge, the free edge spaced from the bearing chamber wall.
Dependencies are inferred from the claim text.