Pratt-Whitney Canada Corp

Ritchie Domingo

Pierre Gauvin

Daniel Alecu

Adam Logan

Andrew Walz

Marc Jordan Adique

Patrick Thivierge

Patrick Arkinson

Robert Scandella

Tom Haslam-Jones

Mélanie Papillon

Timothy Rutke

An oil cooling system for an aircraft engine, a bypass valve and an associate method of cooling aircraft engine oil are provided. The oil cooling system includes a heat exchanger having an inlet and an outlet. The inlet is in fluid communication with a first oil conduit to receive a first oil flow from the first oil conduit. The heat exchanger facilitates heat transfer from the first oil flow to another fluid. A flow restrictor defining a constriction is operatively disposed to restrict the first oil flow through the heat exchanger. A second oil conduit receives the first oil flow from the heat exchanger. A bypass oil passage provides fluid communication between the first oil conduit and the second oil conduit to allow a second oil flow received from the first oil conduit to flow to the second oil conduit and bypass the heat exchanger.

Oil cooling system for aircraft engine

Apparatus and methods for controlling a pressure differential across one or more seals of a bearing chamber in a gas turbine engine are disclosed. In some embodiments, the apparatus comprises a scavenge pump in fluid communication with an interior of the bearing chamber for driving oil from the bearing chamber; and a venting valve. The venting valve is configured to cause venting of the interior of the bearing chamber in parallel to the scavenge pump based on the pressure differential across the one or more seals.

Apparatus and method for controlling a pressure differential across a seal of a bearing chamber

A scavenge gear pump and its method of operation is described. The scavenge gear pump includes a pump housing defining a pump chamber, an inlet passage, an outlet passage, and a fluid injection passage in fluid communication with the pump chamber. The inlet passage receives an admixed fluid at low pressure and the outlet passage the admixed fluid at high pressure from a downstream region of said pump chamber. The fluid injection passage receives a third fluid at an injection pressure for input into the pump chamber. A pair of driveable gears is disposed in the pump chamber. The third fluid is injected directly into the gear meshing area of the pump chamber through the fluid injection passage so that the third fluid fills voids at least between said intermeshing teeth of the driveable gears and so that the second fluid does not occupy the gear meshing area.

Scavenge gear pump

A lubrication system for a gas turbine engine including at least one porous element located in a cavity containing at least one rotating component receiving a flow of the lubricant, the porous element being located across a path taken by a portion of the lubricant expelled from the at least one respective rotating component such that the portion of the lubricant circulates therethrough, the at least one porous element being made of a material resistant to a temperature of the lubricant, the at least one porous element reducing a velocity of the portion of the lubricant circulating therethrough.

Lubrication system with porous element

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Markham, Canada

Ritchie Domingo