Pratt-Whitney Canada Corp

Pratt & Withney Canada Corp.

Abdelkhalek Saadi

Daniel Blais

Roger Huppe

A gas turbine engine is provided that includes a static structure, a rotating shaft, and a bearing assembly. The bearing assembly includes a bearing and a seal subassembly. The bearing has inner and outer races and a plurality of roller elements. The outer race includes a shield member. The seal subassembly includes a seal element coupled with the static structure and a seal runner coupled with the rotating shaft. Portions of the seal runner, the outer race, and the inner race define a first bearing cavity. Portions of the seal runner, the outer race, the seal element, and the static structure define a lateral bearing cavity. The lateral bearing cavity is disposed axially between the first bearing cavity and the seal element. The outer race includes a plurality of drain holes that provide fluid communication between the first bearing cavity and the lateral bearing cavity.

Bearing assembly for a gas turbine engine

A bearing system comprises a bearing configured to be mounted to a shaft. A bearing housing interfaces the bearing to a structure. An annular gap is defined between an outer annular surface of the bearing housing and the structure and configured to receive oil therein. An outlet defined in an outer section surface of the bearing housing is oriented toward a component axially spaced from the bearing. A fluid passageway between the at least one outlet and the annular gap for fluid communication therebetween. In use the fluid passageway directs pressurized oil from the annular gap to the outlet to reach the adjacent component. A method for using oil from a bearing to cool or lubricate a component axially spaced from the bearing is also provided.

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Montreal, Canada

Abdelkhalek Saadi