Pratt-whitney Canada Corp

Orthosoft, Inc.

Louis Brillon

Michel Desjardins

Pierre Gauvin

Rose Beaulieu

Bruno Martin

Sean Powers

Julien Simard-Bergeron

Joanna Radon

David Gagnon-Martin

Jean Dubreuil

Guy Bouchard

Paul Weaver

Martin Poulin

Sébastien Jutras

Benoît Pelletier

Marcin Rejman

Alain Carrieres

Mateusz Kesek

Benoît Chouinard

Jean-François Belanger

Kevin White

A powerplant is provided for an aircraft. This aircraft powerplant includes an aircraft engine, and the aircraft ending includes a shaft and an anode. The shaft is configured to rotate about an axis. The shaft is configured from or otherwise includes a shaft material with a first anodic potential. The anode is mounted to and electrically coupled with the shaft. The anode is configured from or otherwise includes an anode material with a second anodic potential that is greater than the first anodic potential.

Aircraft powerplant rotating assembly with sacrificial anode(s)

An accessory gearbox of an aircraft engine includes a cover mounted thereto. The cover defines a centrally extending axis and has an outer surface with accessory mounts disposed thereon. First and second accessory devices are mounted to the gearbox at first and second mounts spaced apart on the cover. A planar linking member dynamically couples the first accessory device to the second accessory device. The linking member extends transversally relative to the axis and has a first side opposite a second side with a first opening extending therethrough. The first opening is aligned and matingly receiving at least a portion of the first accessory device therethrough. The linking member has a second opening extending therethrough. The second opening is aligned and matingly receiving at least a portion of the second accessory device therethrough. The linking member mechanically interconnects the first and second accessory devices independently from the cover.

Accessory gearbox cover with planar linking member

The method can include analyzing the composition of the particulate polymer debris, including ascertaining a presence of at least one main polymer element and a presence or absence of at least one signature polymer element in the particulate debris; establishing a correlation between the particulate polymer debris and a set of components, including matching the ascertained presence of the at least one main polymer element to a family of polymers from which the components of the set, including the source component, are made; and determining the source component amongst the components of the set, including matching the ascertained presence or absence of the at least one signature polymer element to a polymer composition of the source component.

Method of identifying a source component of particulate debris in an aircraft engine

A filter housing for containing a cartridge assembly having a filter cartridge secured to a filter cover, the filter housing has a peripheral wall extending around a longitudinal axis, and end wall secured to the peripheral wall, the filter housing defining a cavity partially enclosed by the peripheral wall and the end wall, the peripheral wall defining a cartridge-receiving section extending from the end wall along the longitudinal axis and sized for receiving the filter cartridge and a cover-receiving section extending along the longitudinal axis from the cartridge-receiving section to an open end of the filter housing opposed to the end wall and sized for receiving the filter cover, a portion of the cover-receiving section recessed radially outwardly from the cartridge-receiving section relative to the longitudinal axis, a lubricant outlet of the filter housing extending through the portion of the cover-receiving section of the peripheral wall.

Filter assembly for gas turbine engine

The present disclosure relates to a housing for an engine component. The housing comprises a wall made of a light alloy. An epoxy primer coating having at least one layer of a primer containing at least 80 wt. % epoxy covering the wall. An intumescent paint coating having at least one layer of intumescent paint directly covering the epoxy primer. And, an epoxy top coat directly covering the intumescent paint coating, the epoxy top coat having at least one layer of a top coat containing at least 80 wt. % epoxy.

Housing having intumescent coating and process of production

A powerplant system is provided that includes a gas turbine engine system and an actuation system. The gas turbine engine system includes a rotating structure, a stationary structure and one or more bearings rotatably mounting the rotating structure to the stationary structure. The actuation system is configured to passively rotate the rotating structure about a rotational axis during transportation of the gas turbine engine system.

Passively rotating a rotating structure of a gas turbine engine during transportation

A fluid filter arrangement, with protection against external contamination, the filter arrangement comprising: a fluid circulating system; a filter cartridge having an exterior surface; a housing having an internal fluid chamber surrounding the exterior surface of the filter cartridge, an open end through which the filter cartridge can pass along a housing axis; and a cover sealed over the open end of the housing in a closed position, the cover in an open position exposing the open end of the housing, the cover including a fluid passage in communication with the internal fluid chamber in the closed position, the cover fluid passage being in communication with the fluid circulating system in the closed position and in the open position.

Filter cover protection against external contamination

A gas turbine engine, has: a shaft rotatable about a central axis and engaged at an end thereof to a rotatable load via a spline; a reference tube circumferentially extending around the shaft, the reference tube secured at a first end to the shaft for rotation therewith and a second end free relative to the shaft for measuring a deformation of the shaft, the reference tube defining at least one tube aperture therethrough; an oil nozzle fluidly connected to a source of lubricant, the oil nozzle defining an exit flow axis intersecting the at least one tube aperture for injecting oil through the reference tube, the shaft defining at least one shaft aperture extending therethrough, the oil nozzle aligned with the spline via the at least one tube aperture and the at least one shaft aperture.

Systems and methods for internal spline lubrication

A method of operating a gas turbine engine in a multi-engine aircraft, the gas turbine engine having an engine shaft mounted for rotation in a bearing and a gearbox connected to the engine shaft for torque transmission therebetween, includes axially preloading the bearing using an axially biasing element disposed between the gas turbine engine and the gearbox. The axially biasing element reacts against the gearbox to exert an axial preload force on the bearing and the engine shaft of the gas turbine engine.

Bearing preload using external gearbox reaction

The method can include analyzing the composition of the particulate metal debris, including ascertaining a presence of at least one main alloy element and a presence or absence of at least one signature alloy element in the particulate debris; establishing a correlation between the particulate metal debris and a set of components, including matching the ascertained presence of the at least one main alloy element to a family of alloys from which the components of the set, including the source component, are made; and determining the source component amongst the components of the set, including matching the ascertained presence or absence of the at least one signature alloy element to an alloy composition of the source component.

The gas turbine engine can have a set of components, the components of the set all being made of material compositions of the same type having a common at least one main material element, the material compositions having distinct signatures in the form of a varying trace amount of one or more signature element, the distinct signatures varying from one component of the set to another.

A filter assembly for an engine, has: a housing having a longitudinal axis and defining an internal volume, the housing having an open end; and a cartridge assembly receivable within the internal volume via the open end of the housing and securable to the housing, the cartridge assembly including a filter cartridge, a cover removably secured to the filter cartridge, and a sealing member between the cover and the filter cartridge, a locking engagement between the cover and the filter cartridge to limit an axial movement of the cover relative to the filter cartridge upon removal of the cartridge assembly from the housing.

A journal bearing assembly for rotatably supporting at least one gear, comprising a pin and a journal shaft. The journal shaft includes an inner cavity receiving the pin and an outer surface including a plurality of contact surfaces supporting the at least one gear and at least one annular groove separating adjacent contact surfaces. The pin is configured to support the journal shaft at a support position in the inner cavity.

Dual land journal bearings for a compound planetary system

A gas turbine engine with a rotor having a shaft mounted to the engine with a plurality of electrically insulating bearings is provided. The electrically insulating bearings are coupled to the shaft to support the rotor in the engine. There is at least one electrically conductive bearing coupled to the shaft and that further support the rotor in the engine. An electrically conductive path is defined between the rotor and an electrical ground of the engine. The electrically conductive path is defined through the electrically conductive bearing to reach the electrical ground of the engine. A method for electrostatically discharging a rotor supported in the gas turbine engine is also provided.

Turbine engine bearing used as a static electricity leak path

A gas turbine engine comprising a gearbox, the gearbox having gear(s). A journal bearing assembly rotatably supports the gear, the journal bearing assembly having at least a pin, and a journal having a tubular body defining a pin-receiving inner cavity having an inner surface, a first cavity and a second cavity defined in the inner surface of the pin-receiving inner cavity, a rib support located between the first cavity and the second cavity, the rib support being aligned with a longitudinal center of the tubular body, with the first cavity and the second cavity on opposed axial sides of the rib support.

Growing community of inventors

Varennes, Canada

Louis Brillon