Pratt-Whitney Canada Corp

David Harold Menheere

Andreas Eleftheriou

Daniel Alecu

Daniel Van Den Ende

Richard Alan Kostka

Jean Thomassin

Andre Julien

Anthony C Jones

Richard Ullyott

Timothy Redford

Richard Ivakitch

Santo Chiappetta

David Denis

Andrew Marshall

Paul Stone

Quantai Liu

Tim Redford

Bruno Villeneuve

Serge Dussault

Behzad Hagshenas

Luc Dionne

Serge Lafortune

Maxime Courtois

Philip Ridyard

Darius Jehangir Karanjia

Richard A Kostka

Jean Dubreuil

Enzo Macchia

Paul Aitchison

Denis Leclair

Steven Strecker

Adam Trumpour

Andreas Elfetheriou

Brent Hayward

Daniel Van Den Hende

Dennis Kim

Mark Shields

Anthony Jones

Daniel Van De Ende

Andrew R Marshall

Richard Kostka

Daniel T Alecu

An engine system is provided that includes an engine core assembly and a fuel system. The engine core assembly includes a core flowpath, a core compressor section, a core combustor section and a core turbine section. The core flowpath extends through the core compressor section, the core combustor section and the core turbine section from an inlet into the core flowpath to an exhaust from the core flowpath. The core compressor section includes a core compressor rotor. The combustor section includes a combustor. The fuel system includes a fuel flowpath, a fuel turbine section and a fuel injector. The fuel flowpath extends through the fuel turbine section to the fuel injector. The fuel turbine section includes a fuel turbine rotor coupled to and rotatable with the core compressor rotor. The fuel injector is configured to direct fuel received from the fuel flowpath into the combustor.

Gas turbine engine system with fuel driven turbine

An electric fan for producing thrust to propel an aircraft is disclosed. The electric fan comprises a stator, a fan rotor rotatably mounted relative to the stator and an electric motor mounted to the stator and drivingly engaged with the fan rotor to cause rotation of the fan rotor relative to the stator. The fan rotor comprises an annular body defining a flow passage therethrough and a plurality of fan blades disposed in the flow passage and mounted for common rotation with the annular body about a fan rotation axis. The electric motor has a motor rotation axis that differs from the fan rotation axis.

Electric fan

A compressor has: a rotor and a shroud having a internal and external sides and an air outlet; an annular case mounted to the external side and enclosing a plenum, the annular case having inner and outer sides and defining an aperture; a valve mounted to the annular case at the aperture and having: a support secured to the annular case and defining a seat surrounding a bleed passage, the seat located on the outer side, the support defining a guiding aperture, and a valve member having a head and a stem slidably received within the guiding aperture, the valve member having a closed position and an open position, the head abutting the valve seat in the closed position and offset from the valve seat in the open position; and an actuator engaged to the valve member for moving the valve member between the closed position and the open position.

Bleed valve assembly for aircraft engines

An engine system is provided that includes an engine rotating structure, an electric machine rotating structure and a flex coupler. The flex coupler rotatably connects the electric machine rotating structure to the engine rotating structure. The flex coupler includes a first mount, a second mount and a flex plate. The first mount includes a plurality of first mount fingers arranged circumferentially about an axis. The second mount includes a plurality of second mount fingers arranged circumferentially about the axis. The flex plate connects the first mount to the second mount. The flex plate includes a plurality of first flex plate fingers and a plurality of second flex plate fingers. Each of the first flex plate fingers is attached to a respective one of the first mount fingers. Each of the second flex plate fingers is attached to a respective one of the second mount fingers.

Flex coupler for hybrid gas turbine engine powerplant

An aircraft engine, has: a high-pressure spool having a high-pressure turbine drivingly engaged to a high-pressure compressor; and a low-pressure spool having: a first low-pressure turbine downstream of the high-pressure turbine; and a second low-pressure turbine downstream of the first low-pressure turbine, one or more of the first low-pressure turbine and the second low-pressure turbine drivingly engaged to a rotatable load, the first low-pressure turbine and the second low-pressure turbine radially offset from one another relative to a central axis of the aircraft engine.

Aircraft engine having two radially offset turbines

Systems and methods for delivering a buffer fluid to a shaft seal of a gas turbine engine are provided. An exemplary system includes, a buffer fluid source, one or more first conduits providing fluid communication between the buffer fluid source and the shaft seal along a first route, and one or more second conduits providing fluid communication between the buffer fluid source and the shaft seal along a second route different from the first route. A heat exchanger is also disposed along the first route to facilitate heat transfer between buffer fluid in the one or more first conduits and a cooling fluid.

Buffer fluid delivery system and method for a shaft seal of a gas turbine engine

A coupling has: a first coupler rotatable about an axis and defining first connections distributed about the axis; a second coupler defining second connections distributed about the axis, the second connections offset from the first connections; and segments distributed about the axis and extending radially from the first connections to the second connections, a segment of the segments having a first end engaging a first connection of the first connections and a second end engaging a second connection of the second connections, the first end circumferentially offset from the second end, a face of the segment abutting against a face of the first coupler when the segment is inserted into the first connection in a first orientation such that a penetration depth of the segment into the first connection in the first orientation is less than the penetration depth in a second orientation opposite the first orientation.

Torque transfer coupling

An impeller shroud assembly for a gas turbine engine includes an annular impeller shroud disposed about an axial centerline. The impeller shroud includes a shroud inducer portion and a shroud exducer portion disposed radially outward of the shroud inducer portion and extending to an outer radial end of the impeller shroud. The shroud inducer portion and the shroud exducer portion defining an impeller-facing surface of the impeller shroud. The impeller shroud has a pivot point defined between the shroud inducer portion and the shroud exducer portion. The impeller shroud assembly further includes a clearance control device connected to the shroud exducer portion of the impeller shroud proximate the outer radial end. The clearance control device is configured to pivot the shroud exducer portion of the impeller shroud about the pivot point between a first axial position and a second axial position.

Impeller shroud assembly and method for operating same

An aircraft engine comprises a casing extending circumferentially around a central axis. A support flange is secured to the casing and extends circumferentially around the axis. The support flange has an inner and an outer flange face. A component is drivingly engaged by a shaft of the engine. The component has a connecting section extending around the central axis. The connecting section has a connecting face. The inner flange face is in abutment against the connecting face. A retaining ring extends circumferentially around the central axis. The retaining ring is in abutment against the outer flange face of the support flange. The retaining ring has a coefficient of thermal expansion, which is less than that of the support flange.

Connecting arrangement between components of an aircraft engine

In accordance with at least one aspect of this disclosure, there is provided a drive shaft system. In embodiments, the drive shaft system includes a generator shaft extending along a longitudinal axis with a longitudinal bore defined through the generator shaft. A thru shaft extends through the longitudinal bore of the generator shaft. In embodiments, the thru shaft includes, a front coupler mount at a first end operative to receive torque input, and a rear coupler mount at a second end opposite the first end.

Mechanical drive shaft arrangements for tail cone generators

A vane system for an aircraft engine, comprising: an inner wall extending circumferentially about a duct axis; an outer wall extending circumferentially about the duct axis radially outward of the inner wall relative to the duct axis; at least one vane extending from an inner end attached to the inner wall to an outer end rotatably connected to the outer wall, the outer end rotatable relative to the outer wall about a vane axis at an angle to the duct axis; a ring extending circumferentially about the duct axis radially outward of the outer wall relative to the duct axis, the ring rotatable about the duct axis; and at least one transmission member located radially outward of the outer wall relative to the duct axis and coupling the ring to the outer end such that rotating the ring about the duct axis rotates the outer end about the vane axis.

Variable guide vane system

An inlet guide vane assembly for an aircraft engine includes an array of inlet guide vanes having radially inner ends at a radially inner shroud, radially outer ends at a radially outer shroud, and airfoils extending therebetween. An internal passage extends radially through the airfoil from a vane air inlet at the radially inner end to a vane air outlet at the radially outer end. The vane air inlet is in fluid communication with an inner plenum, disposed radially inwardly of the inlet guide vane and in fluid communication with an anti-icing air source. The vane air outlet in fluid communication with an outer plenum, disposed radially outwardly of the inlet guide vane and having an exhaust port. A vane anti-icing pathway is defined in a radially-outward direction from the inner plenum, through the internal passage of the vane, and into the outer plenum.

System and method of anti-icing inlet guide vanes

A bleed valve has a valve body enclosing a valve chamber defining a passageway between an inlet port and an outlet port. A panel is mounted into the valve body. The panel is deflectable under fluid pressure between a sealing position blocking the passageway when the bleed valve is in a close state, and a bleeding position allowing fluid flow communication between the inlet port and the outlet port when the bleed valve is an open state. A pressure control device is provided to vary a fluid pressure differential between opposite sides of the panel within the valve chamber and selectively open or close the bleed valve.

Actively controlled bleed valve

The gas turbine engine can have an air mover configured for generating a flow of air around a rotation axis; a surface extending around the rotation axis delimiting a passage for the flow of air downstream of the air mover; an electric machine disposed within the passage and coupled to the air mover; a coolant circuit having: an evaporator circumferentially disposed around at least part of the electric machine and in thermal communication therewith; a condenser having a surface cooler circumferentially disposed at least partially around the surface and in thermal communication therewith; a first conduit fluidly connecting an upper region of the evaporator to an upper region of the condenser; and a second conduit fluidly connecting a lower region of the condenser to a lower region of the evaporator; and a coolant fluid in the coolant circuit.

Turbofan engine, cooling system and method of cooling an electric machine

A variable guide vane control system comprises an actuator and a rolling contact joint. The joint includes a drive ring rotatable about a drive axis and at least one roller rotatable about a roller axis parallel to the drive axis and drivingly connectable to a vane. A first flexible member and a second flexible member connect the drive ring and the roller to one another. The first flexible member and the second flexible member are respectively tensioned when the drive ring rotates about the drive axis in a first direction and in a second direction opposite the first direction.

Growing community of inventors

Georgetown, Canada

David Harold Menheere