Pratt & Whitney Canada Corp.

Eric Durocher

Guy Lefebvre

John Pietrobon

Keith Morgan

Nicolas Grivas

Jean Dubreuil

Eugene Gekht

Lazar Mitrovic

Ghislain Plante

Rene Paquet

Richard Bouchard

Robert Peluso

Lam Nguyen

Michel Desjardins

Pierre-Yves Legare

Gabriel Naccache

Denis Leclair

Martin Jutras

Oleg Morenko

Bhawan Bhai Patel

Remy Synnott

Philippe Beauchesne-Martel

Michel Labrecque

Paul Weaver

Ian Alexander MacFarlane

Scott Smith

Martin Poulin

Scott Walker Smith

Stephen Mah

Johnny Vinski

Panagiota Tsifourdaris

Sri Sreekanth

Marc Tardif

Guy Bouchard

Bruno Chatelois

Assaf Farah

Jason Herborth

Roger Huppe

Kevin Ng

Anca Mateescu

John Walter Pietrobon

Dany Blais

Alan Juneau

Zenon Szlanta

Alessandro Ciampa

Martin Clermont

John Watson

Mohamad Sleiman

Guillaume Landry-Drolet

John Wilson

Maxime Demers

Yves Caron

Dennis English

Laurent Letourneau

Tania Fauchon

Philippe Bauchesne-Martel

An assembly is provided for a gas turbine engine. This engine assembly includes a vane array and a heat exchanger integrated with the vane array. The vane array includes an inner platform, an outer platform and a plurality of vanes. The inner platform extends circumferentially about a centerline and forms an inner peripheral boundary of a flowpath through the vane array. The outer platform extends circumferentially about the centerline and forms an outer peripheral boundary of the flowpath through the vane array. The vanes extend across the flowpath between the inner platform and the outer platform. The vanes include a first vane and a second vane. The heat exchanger includes a first vane passage and a second vane passage fluidly coupled with and downstream of the first vane passage. The first vane passage extends through the first vane. The second vane passage extends through the second vane.

Gas turbine engine component with integral heat exchanger

A system is provided for an aircraft. This aircraft system includes a powertrain and a first lubrication system. The powertrain includes a powerplant, a bladed rotor and a clutch system operatively coupling the powerplant to the bladed rotor. The powerplant is configured to drive rotation of the bladed rotor through the clutch system when the clutch system is engaged. The first lubrication system is fluidly coupled with and is configured to deliver first lubricant to the powerplant and the clutch system.

Lubrication system for aircraft powerplant and clutch system

An assembly for a propulsion system of an aircraft includes a gearbox module, an electric motor assembly, a first accessory load assembly, and a propulsor. The gearbox module includes a gear assembly and an output shaft. The gear assembly includes a main gear and a plurality of offset gears. The electric motor assembly includes an electric motor. The electric motor includes a rotor. The rotor is mounted to a first offset gear of the plurality of offset gears. The rotor is configured for rotation about a rotational axis to drive rotation of the gear assembly and the output shaft. The first accessory load assembly includes at least one first accessory load. The at least one first accessory load is mounted to a second offset gear of the plurality of offset gears. The propulsor is coupled to the output shaft.

Electric motor propulsion system for an aircraft

A propulsion system for an aircraft includes a gas turbine engine and an engine power extraction system. The gas turbine engine includes a first rotational assembly. The first rotational assembly includes a propeller and a first shaft coupled to the propeller. The first shaft is configured for rotation about a rotational axis of the propulsion system. The engine power extraction system includes a fluid pump, a fluid motor, and a generator. The fluid pump is operably coupled to the first shaft. The fluid pump is in fluid communication with the fluid motor. The fluid pump is configured to pressurize and direct a hydraulic fluid to the fluid motor causing the fluid motor to rotatably drive the generator to generate an electrical power output.

Engine power extraction system and method for using same

An apparatus is provided for a gas turbine engine. This engine apparatus includes a lubricant reservoir, a lubricant circuit and a compressed air circuit. The lubricant reservoir includes an internal cavity, a compressed air passage and a reservoir wall at least partially forming an outer peripheral boundary of the internal cavity. The internal cavity is configured to contain lubricant. The compressed air passage extends within the reservoir wall along at least a portion of the outer peripheral boundary of the internal cavity. The lubricant circuit is fluidly coupled with the internal cavity. The compressed air circuit is fluidly coupled with the compressed air passage.

Lubricant reservoir with integrated heat exchanger

An aircraft propulsion system is provided that includes a turbine engine and an exhaust gas heat exchanger. The exhaust gas heat exchanger includes a central conduit, an outer radial plenum, fluid conduits, and inter-conduit passages. The fluid conduits are disposed in a nested arrangement. Each fluid conduit has inner and outer radial walls that extend axially between the forward and aft ends. The inner and outer radial walls are radially separated to form an internal fluid passage. Each fluid conduit is radially spaced apart from adjacent fluid conduits to define an axially extending exhaust gas passages. The inter-conduit passages include at least one inter-conduit passage that provides fluid communication between the central conduit and a first fluid conduit, and at least one inter-conduit passage that provides fluid communication between first and second fluid conduits. A serpentine fluid flow path extends through the fluid conduits and the inter-conduit passages.

Aircraft propulsion system with turbine engine and exhaust heat exchanger

A heat exchanger assembly for an aircraft includes a housing, a heat exchanger, and a nozzle. The housing includes an inner flow path wall, an outer flow path wall, an inner inflatable diaphragm, and an outer inflatable diaphragm. The inner flow path wall and the outer flow path wall form an air inlet and an air outlet. The inner inflatable diaphragm and the outer inflatable diaphragm form a venturi channel between the air inlet and the air outlet. The heat exchanger is disposed downstream of the venturi channel within the air flow path. The nozzle includes a nozzle housing disposed within the air flow path. The nozzle housing forms a nozzle inlet and a nozzle outlet. The nozzle outlet is disposed at the venturi channel.

Heat exchanger assembly for an aircraft

An apparatus is provided for a gas turbine engine. This gas turbine engine apparatus includes a hot section structure of the gas turbine engine. The hot section structure is configured with a plurality of surfaces respectively forming boundaries of a gas path through the hot section structure. The surfaces include a first surface and a second surface. The hot section structure includes metal and thermal barrier material. The first surface is formed by the metal. The second surface is formed by the thermal barrier material.

Selectively coated gas path surfaces within a hot section of a gas turbine engine

A turboshaft engine for a rotorcraft includes a first spool and an independently rotatable second spool. The first spool includes a low pressure compressor, a first set of variable guide vanes disposed at an entry of the low pressure compressor, and a low pressure turbine drivingly engaged to the low pressure compressor. The second spool includes a high pressure compressor, a second set of variable guide vanes disposed at an entry of the high pressure compressor, the second set of variable guide vanes independently operable relative to the first set of variable guide vanes, and a high pressure turbine drivingly engaged to the high pressure compressor. One or both of the low pressure compressor and the high pressure compressor includes a mixed flow rotor.

Turboshaft gas turbine engine

In accordance with at least one aspect of the present disclosure, there is provided a fuel system of an aircraft engine, comprising: a fuel conduit interface connecting a fuel conduit to a component of the fuel system; and a sweep line structure. The sweep line structure includes an inner surface facing toward, extending around, and defining a cavity around the fuel conduit interface, and an outer surface opposite the inner surface, the cavity being fluidly sealed relative to the outer surface.

Sweep flow structures for fuel systems

The aircraft can include a rotary airfoil device having an output shaft rotatable around an airfoil rotation axis; an electric engine having a source shaft drivingly coupled to the output shaft; a controller in communication with the electric engine; a low voltage electric system operable to power the controller; a high voltage electric system having a high voltage battery operable to power the electric engine, the high voltage battery further operable to power the low voltage electric system via a voltage converter; and an electromagnetic generator having a generator shaft coupled to the output shaft, the electromagnetic generator operable to power the low voltage electric system.

Aircraft and associated method of controlling an electric aircraft powerplant

An apparatus is provided for a gas turbine engine. This apparatus includes a lubricant reservoir, a heat exchanger, a lubricant circuit and a compressed air circuit. The lubricant reservoir includes an internal cavity for storing lubricant. The heat exchanger includes a heat exchange conduit and a compressed air passage. The heat exchange conduit is arranged in the internal cavity. The compressed air passage extends longitudinally through the heat exchange conduit. The lubricant circuit is fluidly coupled with the internal cavity. The compressed air circuit is fluidly coupled with the compressed air passage.

In accordance with at least one aspect of this disclosure, there is provided a heat exchange system. The heat exchange system includes a first heat exchanger and a second heat exchanger. The first heat exchanger includes an engine fluid conduit fluidly connecting an engine fluid inlet to an engine fluid outlet. A first internal buffer fluid conduit fluidly connects a first buffer fluid inlet to a first buffer fluid outlet where the engine fluid conduit is in fluid isolation from the first internal buffer fluid conduit but is in thermal communication with the first internal buffer fluid conduit for heat exchange between the engine fluid and the buffer fluid.

Buffer heat exchangers for hydrogen engines

A labyrinth seal assembly comprising: an outer seal having a radially inner cavity surface, and an axial cavity surface inward of the radially inner cavity surface; a floating seal received by the outer seal so as to be movable in a radial direction relative to the outer seal, the floating seal having a radially outer seal surface spaced inwardly from the radially inner cavity surface, a radially inner surface inward of the radially outer seal surface, and an axial seal surface bearing against the axial cavity surface; and an inner seal received by the floating seal, the inner seal having a radially outer surface spaced inwardly from the radially inner surface, a first one of the radially outer surface and the radially inner surface defining one tooth projecting toward a second one of the radially outer surface and the radially inner surface to inward of the axial seal surface.

Labyrinth seal

A method of operating a multi-engine system of a rotorcraft includes, during a cruise flight segment of the rotorcraft, controlling a first engine to provide sufficient power and/or rotor speed demands of the cruise flight segment; and controlling a second engine to by providing a fuel flow to the second engine that is between 70% and 99.5% less than a fuel flow provided to the first engine. A turboshaft engine for a multi-engine system configured to drive a common load is also described.

Multi-engine system and method

Growing community of inventors

Vercheres, Canada

Eric Durocher