Pratt-Whitney Canada Corp

Pratt & Whitney Canada Corp.

Daniel Alecu

David Harold Menheere

Andreas Eleftheriou

Ivan Sidorovich Paradiso

Laslo Diosady

Enzo Macchia

Dana Tomescu

Kenneth D Parkman

Sam Cutrara

Bryan William Olver

Barry Barnett

Jason Araan Fish

Richard Alan Kostka

Adam Logan

Michel Labbe

Kevin Ng

Dean Carpenter

Marc Jordan Adique

Darius Jehangir Karanjia

Patrick Thivierge

Victor Sa Melo

Ahmad Cheikhzen

Penny Nicolaidis

Ignatius Theratil

Ninad Joshi

Pierre-Yves Legare

Xiaoliu Liu

Pierre Gauvin

Daniel Van Den Ende

Gabriel Naccache

Quantai Liu

Roberto Brito

Rose Beaulieu

Dave Menheere

Nashed Youssef

Philippe Bonniere

Sylvain Brouillet

Andrew Walz

Michael Conciatori

Steven Strecker

Felix Gauthier

Ritchie Domingo

John Watson

Nick Stina

Audrey Brouillet

Gordon Ferch

Kimberley Ann Macdonald

Zoran Markovic

Jean-Sébastien Dick

Phillipe Bonniere

Dileepan Sivalingam

Carmine Forgione

Patrick Beauchamp

Sean Downard

David Hill

Charlie Molina

Marc Jordon Adique

David Menheere

Bryan W Olver

Gas turbine engines include an engine core having compressor, combustor, and turbine sections arranged within an engine casing. A transfer tube is arranged on an exterior of the casing and configured to define a fluid conduit for fluid to be transferred about the engine. A fitting is connected to the transfer tube and a seal assembly is arranged between the fitting and the transfer tube. The seal assembly provides a fluid seal between the fluid conduit and an ambient environment at a connection between the fitting and the transfer tube. The seal assembly includes a primary seal arranged in a gap between the fitting and the transfer tube and a secondary seal arranged in the gap between the primary seal and an ambient environment. The secondary seal is configured to expand into engagement with the fitting and the transfer tube when exposed to temperatures of at least 800° F.

Flame protection seals for gas turbine engines

An accessory power unit assembly includes a combustor assembly that includes a pulse detonation tube that defines a curved passage between an inlet that receives a compressed airflow and a discharge end. The detonation tube operates as a resonant cavity to sustain a standing pressure wave. Fuel injected into the pulse detonation tube is timed to coincide with movement of a standing wave toward a discharge end. The standing wave provides an increase in pressure of an output exhaust gas driving the turbine without a corresponding increase in load.

Auxiliary power unit with pulse detonation combustion

A de-aerator has: a housing defining an air-oil inlet, an oil outlet, and an air outlet; a rotor within the housing and rotatable about a rotation axis and having: inner and outer rims and blades, passages between the blades and communicating with the air-oil inlet; a conduit extending around the rotation axis and defining a central passage extending axially and communicating with the air outlet, the conduit being radially spaced apart from the outer rim by radial passages communicating with the oil outlet; and openings located inwardly of the blades and communicating with the central passage, wherein one or more of: a cross-sectional area of the central passage taken on a plane transverse to the rotation axis increasing in an axial direction away from the air-oil inlet; and the openings located at least partially radially between an inner face of the conduit and an outer face of the inner rim.

Active de-aerator for aircraft power plant

A heat management system for a thermal engine includes a source of hydrogen, a first hydrogen conduit flowing a first flow of hydrogen therethrough, the first hydrogen conduit fluidly coupling the source of hydrogen to a fuel system of the thermal engine, and a second hydrogen conduit flowing a second flow of hydrogen therethrough. The second hydrogen conduit is in thermal communication with an engine exhaust conduit to transfer heat from the engine exhaust conduit to the second hydrogen conduit. The second hydrogen conduit is also in thermal communication with the first hydrogen conduit to transfer heat from the second hydrogen conduit to the first hydrogen conduit.

Heat management system and method for hydrogen-fueled engine

An aircraft engine, has: an oil circuit fluidly connecting an oil reservoir to components of the aircraft engine; and a de-aerator fluidly connected to the oil circuit and located downstream of the components relative to a flow of the oil through the oil circuit, the de-aerator feeding the flow of the oil into the reservoir, the de-aerator having: a nozzle extending from a nozzle inlet to a nozzle outlet along a flow passage delimited by a peripheral wall, the peripheral wall extending around a central axis of the nozzle, a flow circulating area of the flow passage decreasing from the nozzle inlet to the nozzle outlet; and a deflector projecting from the peripheral wall of the nozzle at the nozzle outlet, the deflector having a curved section extending between a proximal end at the nozzle outlet and a distal end, the deflector intersected by the central axis of the nozzle.

Oil de-aerator for aircraft engine

An aircraft assist system described herein includes an aircraft coupling counterpart attached to a strut of a landing gear of an aircraft, and an assist vehicle. The assist vehicle includes a frame, ground-engaging wheels mounted to the frame, a power source for driving one or more of the ground-engaging wheels, and a vehicle coupling counterpart for engagement with the aircraft coupling counterpart. The aircraft coupling counterpart and the vehicle coupling counterpart define a swivel connection for transferring a propulsive force from the takeoff assist vehicle to the aircraft. The aircraft coupling counterpart is disengageable from the vehicle coupling counterpart by upward movement of the aircraft coupling counterpart relative to the vehicle coupling counterpart.

Assist system and method for aircraft ground operation

An assembly is provided for a gas turbine engine. This assembly includes a rotating structure of the gas turbine engine, a stationary structure of the gas turbine engine and a volume formed by and extending between the rotating structure and the stationary structure. The rotating structure is rotatable about an axis. The rotating structure includes a seal land and a fluid nozzle. The stationary structure includes a seal element. The seal element is arranged with the seal land to form a seal assembly that seals an annular gap between the stationary structure and the rotating structure. The volume is adjacent the seal element and the seal land. The fluid nozzle is configured to direct a fluid jet out from the rotating structure and into the volume.

Disrupting flow vortices to attenuate resonant tones within a gas turbine engine

An electric motor is provided that includes a housing, a stator, a rotor, and a coolant. The rotor has an output shaft. The rotor is disposed radially inside of the stator and is configured for rotation relative to the stator about a rotational axis. The stator includes an outer radial ring portion and a plurality of stator poles. Each stator pole extends radially inward from the outer radial ring portion to a distal end. The stator includes a plurality of stator cooling circuits. Each stator cooling circuit includes a circumferentially extending outer radial channel located in the outer radial ring portion of the stator and a stator pole channel disposed in each stator pole. The stator pole channel is in fluid communication with the outer radial channel. The stator pole channel extends radially within the respective stator pole. The coolant has magnetic properties disposed in the stator cooling circuits.

Electric motor with stator cooling

An aircraft engine, comprising: a shaft; a bearing housing extending around the shaft and defining a bearing cavity; a bearing in the bearing cavity and rotatably supporting the shaft; a squeeze film damper including: a first seal proximate a first end of the bearing, and a second seal proximate a second end of the bearing; an annulus between the first seal and the second seal, the annulus having a damping fluid in the annulus; and wherein at least the first seal includes a sealing ring received within a groove extending axially from an outer groove wall to an inner groove wall, the inner groove wall located axially between the outer groove wall and the annulus, the sealing ring having an outer ring face facing the outer groove wall and an inner ring face facing the inner groove wall, the inner ring face being movable relative to the outer ring face.

Aircraft engine with squeeze film damper

Blowdown valves and associated methods for separating oil and air in a lubrication system of an aircraft engine are provided. A method includes receiving a mixture of air and oil at a blowdown valve including a valve member movable between a valve-closed position and a valve-open position. With the valve member in the valve-open position, the method includes impinging the mixture against the valve member. A first portion of the mixture having a first fraction of oil is released from the blowdown valve upstream of the valve member. A second portion of the mixture having a second fraction of oil greater than the first fraction of oil is guided around and past the valve member. The second portion of the mixture is released from the blowdown valve downstream of the valve member.

Blowdown valve with air-oil separation

The heat exchanger can include one or more Helmholtz resonator having a cavity internal to the skin of the vehicle, the cavity delimited by a wall, the Helmholtz resonator having an aperture formed across the skin and fluidly connecting the cavity to the atmosphere, the cavity extending in the forward orientation of motion relative the aperture, an open cell structure filling at least a portion of the cavity; and a fluid passage internal to the skin, the fluid passage in thermal communication with the cavity via the wall of the cavity.

Heat exchanger and method of operation

The coupling can have a female member having a plurality of female member connections circumferentially arranged along a radially inner face; a male member having a plurality of male member connections circumferentially arranged along a radially outer face; and a coupling member extending annularly around the axis, the coupling member having a strip, the strip having, circumferentially relative the axis, an alternating sequence of outer folds and inner folds, the outer folds connected to the female member via respective ones of the female member connections, the inner folds connected to the male member via respective ones of the male member connections, the inner folds being circumferentially offset from the outer folds in a given angular direction.

Coupling and associated method of transferring torque

An oil filler assembly, has: a filler tube extending from a bottom end to a top end; a non-return valve having a tube side and a tank side; a cap assembly including a cap removably secured to the filler tube and a dipstick projecting from the cap; a vent having an inlet connected to the tank side and an outlet connected to the tube side, the vent defining a flow path bypassing the non-return valve; and a safety valve connected to the vent and having an open configuration in which fluid flow is permitted and a closed configuration in which fluid flow is prevented, the safety valve being engageable by the cap assembly to bias the safety valve in the open configuration when the cap is secured to the top end, the safety valve being in the closed configuration when the cap assembly is detached from the top end.

Filler-cap activated valve in filler-neck oil vent

An oil filler assembly for an aircraft engine, has: a filler tube extending from a bottom end to a top end; a valve having a tube side fluidly connected to the filler tube and a tank side; a cap removably secured to the top end; a dipstick secured to the cap and extending into the filler tube; and a piston secured to the dipstick, the piston having: a sealing configuration in which the piston sealingly engages the filler tube to fluidly disconnect the top end from the valve, the piston being in the sealing configuration when the cap is secured to the top end of the filler tube; and a venting configuration in which the piston permits fluid communication between the top end and the valve, the piston being in the venting configuration when the cap is moved away from the top end of the filler tube.

Oil filler tube assembly for aircraft engine

The seal assembly can have a support ring having an annular shape defined around a seal axis, and a plurality of strips of a metal material, each strip of the plurality of strips being folded along a length of the strip forming a fold and a pair of segments extending radially inwardly from the fold, relative the seal axis, the fold secured at the support ring, the fold having a bending radius defined around a bending axis, the bending axis oriented parallel to the seal axis, the plurality of strips being arranged circumferentially relative one another, around the seal axis.

Seal assembly and method of manufacturing

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Toronto, Canada

Daniel Alecu