Pratt-whitney Canada Corp

Kenneth D Parkman

Stephen Phillips

Daniel Alecu

Oleg Morenko

Bhawan Bhai Patel

Eduardo David Hawie

Honza Stastny

Parthasarathy Sampath

Maksim Pankratov

John Greer

Yvan Schraenen

Nicholas Guglielmin

Carol Desjardins

Jason Araan Fish

Lorin Markarian

Vittorio Bruno

Hervé Turcotte

Guy Bouchard

Saeid Oskooei

Gavin Rohiteshwar Kisun

Ryan Miskie

Anthony J Matthews

Jean-Sébastien Dick

Pierrot Duchesne

Daniel T Alecu

An aircraft engine has: a compressor section having a compressor rotor rotatable about a central axis; a diffuser downstream of the compressor rotor, the diffuser including a diffuser ring extending circumferentially around the central axis; a bearing housing secured to the diffuser ring, the bearing housing contained within a volume located radially inwardly of the diffuser ring; and an air manifold secured to the diffuser ring, the air manifold defining inlets in fluid flow communication with the compressor section and an outlet in fluid flow communication with the volume.

Diffuser ring with air manifold

A structure for a gas turbine engine includes a first engine component, a second engine component and fasteners. The component apertures include first fastener apertures and intergroup apertures. The first fastener apertures are arranged into a plurality of groups. The first group is formed by N-number of the first fastener apertures. The second group is formed by N-number of the first fastener apertures where the N-number is different than the N-number. Each of the intergroup apertures is disposed circumferentially between and adjacent a respective circumferentially neighboring pair of the groups. The second engine component includes a surface and second fastener apertures. The surface axially engages the first engine component and covers the intergroup apertures. The fasteners attach the first engine component and the second engine component together. Each of the fasteners is mated with one of the first fastener apertures and one of the second fastener apertures.

Aperture pattern for gas turbine engine component with integral alignment feature

Lubrication systems of an aircraft engine and associated methods are provided. The lubrication system includes a chamber having a fluid inlet for receiving lubricating fluid into the chamber, and a fluid outlet for draining the lubricating fluid from the chamber. The fluid outlet is disposed on a wall defining part of the chamber. A rotor is disposed inside the chamber and interacts with the lubricating fluid inside the chamber. The rotor is rotatable in a rotation direction about a rotation axis. A perforated baffle is disposed in the chamber for interacting with the lubricating fluid inside the chamber. The perforated baffle includes a base attached to the wall of the chamber. The base of the perforated baffle is disposed at an angular position preceding the fluid outlet relative to the rotation direction of the rotor.

Lubrication system of aircraft engine

A labyrinth seal assembly for a gas turbine engine having a rotatable shaft. The labyrinth seal assembly has: a housing defining a cavity for receiving a lubricant; a labyrinth seal between the housing and the rotatable shaft of the gas turbine engine, the labyrinth seal having a seal rotor securable to the rotatable shaft and a seal stator secured to the housing; and an insulation layer between the seal stator and the housing, the insulation layer composed of a material different than those used for the seal stator and the housing.

Labyrinth seal assembly

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.

Bearing cavity and method of evacuating oil therefrom

A seal and bearing assembly having a bearing received within a housing. The bearing is disposed radially outwardly of a shaft and having an inner portion and an outer portion. The outer portion has a protrusion extending at least in an axial direction. An outer diameter of the outer portion is sized to provide a radial gap between the outer diameter and the housing section. The gap receives a film of lubricant for damping movements of the bearing relative to the housing section. A sealing member has a rotating portion configured for rotation with the shaft radially spaced apart from a static portion defined by the protrusion of the bearing outer portion. There is also disclosed a method of operating such an assembly.

Seal and bearing assembly with bearing outer portion defining seal static portion

A gas turbine engine comprises bearing(s). A structure supporting the bearing defines a bearing cavity surrounding the at least one bearing, an ambient chamber and an intermediate chamber having a portion between the bearing cavity and the ambient chamber, with at least one wall forming a passage from the bearing cavity to the ambient chamber and through the portion of the intermediate chamber. A tube is received in the passage and having a first end open to the bearing cavity and a second end open to the ambient chamber, the second end adapted to be connected to a conduit for fluid communication between the bearing cavity and the through the tube, wherein a portion of or near the first end of the tube is sealingly joined to the at least one wall, and the second end of the tube contacts the at least one wall and is free to move relative to the at least one wall.

Assembly of tube and structure crossing multi chambers

An oil scavenge system of a gas turbine engine in accordance with one embodiment of the present invention, comprises a housing defined about an axis of rotation, the housing confining an air/oil mixture in motion within the housing and defining an oil scavenge area below the axis of rotation. The housing further includes an outlet at a low location of the housing. A churning damper is supported within the housing and is located in the oil scavenge area. The churning damper includes at least one plate, allowing the air/oil mixture in motion to pass over or through the plate only in a peripheral area of the at least one plate to cause flow energy dissipation.

Oil scavenge system having churning damper for gas turbine engines

A combustor liner for a gas turbine engine including first and second annular liner portions engaged to one another with an interference fit. The first liner portion includes at least one anti-rotation feature extending therefrom and engaging the second liner portion and having a threaded hole defined therethrough at least substantially perpendicularly to an adjacent radially extending surface of the second liner portion for threadingly receiving a pushing tool for pushing against that surface.

Combustor liner with integrated anti-rotation and removal feature

A combustor heat shield comprises a heat shield member defining at least one opening for receiving a fuel nozzle. A louver is received in the opening. The louver has a flow diverting portion extending radially outwardly from the opening for directing air along the hot side of the heat shield member.

Method for manufacturing a combustor heat shield

A floating collar assembly is provided comprising a substantially flat floating collar trapped between a heat shield and a dome panel of the combustor. Axial engagement between the floating collar and the fuel nozzle is maintained via a nozzle cap mounted over the fuel nozzle tip.

Interface between a combustor and fuel nozzle

A combustor liner including a dome section having a positioning hole defined at a first radial distance and sized to receive a first heat shield fastener to at least substantially prevent radial and circumferential motion of the first fastener, a circumferential slot sized to receive a second heat shield fastener to at least substantially prevent radial motion of the second fastener while allowing limited circumferential motion of the second fastener, and a clearance hole defined at a second radial distance and sized to receive a third heat shield fastener to allow limited radial and circumferential motion of the third fastener.

Combustor liner with improved heat shield retention

Combustor heat shield

A gas turbine engine combustor having a dome heat shield includes a cooling scheme having a plurality of impingement cooling holes extending through the combustor and a plurality of adjacent ejector holes for directing cooling air past the heat shield lips of the dome heat shields. The impingement and ejector holes are preferably staggered to reduce interaction therebetween.

Growing community of inventors

Mississauga, Canada

Kenneth D Parkman