Pratt-whitney Canada Corp

Hamilton Sundstrand Corporation

Other

Pratt & Whitney Canada Corp.

United Technologies Advanced Projects, Inc.

Jean Thomassin

Andre Julien

Mike Louis Fontaine

Richard Ullyott

Bruno Villeneuve

Anthony C Jones

David Gagnon-Martin

Edwin Schulz

Sebastien Bolduc

Serge Dussault

Eugene Gekht

David Harold Menheere

Sylvain Lamarre

Michael Gaul

Nigel Caldwell Davenport

Luc Dionne

Pierre-Yves Legare

Stephane Berube

Serge Lafortune

Todd A Spierling

Mark Cunningham

Lazar Mitrovic

Michael Lanktree

Ilya Medvedev

Sergey Usikov

Andrey Zolotov

Etienne Plamondon

Daniel Van Den Ende

Eric LaTulipe

Jean-Gabriel Gauvreau

Anthony Jones

Tatjana Pekovic

André Julien

Joseph Brent Staubach

Behzad Hagshenas

Jean Dubreuil

Sebastien Bergeron

Xi Wang

Glenn C Lemmers, Jr

David S Behling

Jason Nichols

Eric Latulipe

Pierre Bertrand

Luc Landry

Patrick Rousseau

Eric-Pierre Martel

Maxime Courtois

David Meisels

Joseph Kehoe

Manuel Acuna

Sorin Bengea

Lena Raykowski

Chad M Henze

Robert A Bayles

André Denis Leblanc

Xiaoqin Wang

Ahmed Abdelrahman

Charles Faubert

Jade Bilodeau

Sébastien Bolduc

Gilles Begin

Eric Taillon

Marc Kirner

Serge LaFortune

Andrew D Smith

Gordon Saby

Marie-Claude Vallieres

John Perera

Daniel Van Den Hende

Mike L P Fontaine

Marc-Andre Gareau

Ilya B Medvedev

Andre D Leblanc

Edwin Schultz

Nigel Davenport

Joseph Staubach

David Gagnon - Martin

Daniel Van De Ende

Marc-André Gareau

An aircraft propulsion system including at least first airmover, an electric motor configured to at least partially power the at least first airmover, wherein the first airmover includes a propeller having at least a first position configured to provide thrust to the aircraft and a second position configured to recharge a power source, wherein the second position is a reverse windmilling position, and a heat engine configured to at least partially power the first air mover or a second air mover.

Aircraft propulsion system and methods of feathering

A hybrid electric engine control module (ECU) configured to be operatively connected to a hybrid electric aircraft powerplant having a heat engine system and an electric motor system to control a torque output from each of the heat engine system and the electric motor system. The ECU can be configured to receive a torque command and split output power between the electric motor system and the heat engine system. Additionally and/or alternatively, the ECU can be configured to balance a total torque against a second total torque of a second aircraft powerplant.

Torque balancing for hybrid electric propulsion systems and aircraft utilizing hybrid electric propulsion systems

An engine assembly includes a propulsor, a gearbox, an engine, a gas turbine engine, and an electric control assembly. The gearbox includes a gear assembly coupled with the propulsor. The engine includes an air inlet, an exhaust outlet, and an engine output shaft. The engine output shaft is coupled with the gear assembly and configured to drive rotation of the propulsor through the gear assembly. The gas turbine engine includes a first rotational assembly, a compressor section, a turbine section, and a combustor. The compressor section is connected to the air inlet. The combustor is connected to the exhaust outlet. The combustor is configured to direct a combustion gas through the turbine section to drive rotation of the first rotational assembly. The electric control assembly includes a first electric motor. The first electric motor is coupled with the gear assembly. The first electric motor is configured to selectively apply a rotational force to the gear assembly to further drive rotation of the propulsor.

Engine assembly for an aircraft propulsion system

A system is provided for an aircraft. This aircraft system includes a propulsion system, and the propulsion system includes a first thermal engine, a second thermal engine and a first electric machine. The propulsion system is configured to operate the first thermal engine and the second thermal engine, without operating the first electric machine, during a first mode of operation to provide aircraft thrust. The propulsion system is configured to operate the first electric machine and the second thermal engine, without operating the first thermal engine, during a second mode of operation to provide the aircraft thrust.

Multi-drive unit propulsion system for an aircraft

A hybrid propulsion system includes a heat engine configured to drive a heat engine shaft. An electric motor is configured to drive an electric motor shaft. A transmission system includes at least one gearbox. The transmission system is configured to receive rotational input power from each of the heat engine shaft and the electric motor shaft and to convert the rotation input power to output power.

Architectures for hybrid-electric propulsion

A hybrid electric engine control module (ECU) can be configured to be operatively connected to a hybrid electric aircraft powerplant having a heat engine system and an electric motor system to control a torque output from each of the heat engine system and the electric motor system. The ECU can be configured to determine whether at least one of the electric motor system or the heat engine system are in a normal mode such that one of the electric motor system and/or the heat engine can provide a predetermined amount of torque. The ECU can be configured to switch to a degraded mode if either of the electric motor system or the heat engine system cannot provide the predetermined amount of torque. In the degraded mode the ECU can be configured to control the electric motor system and the heat engine system differently than in the normal mode or to not control one or both of the electric motor system or the heat engine system.

Degraded mode operation of hybrid electric propulsion systems

The aircraft includes a fuselage and at least one wing extending from the fuselage. The wing includes first and second original portions and a plug portion positioned between the first and second original portions. A propulsion system is positioned on the at least one wing. The propulsion system includes at least one electric powerplant and at least one combustion powerplant. Each powerplant delivers power to a respective air mover for propelling the aircraft. The electric powerplant and/or the combustion powerplant is positioned outboard from the plug portion.

Systems and methods for aircraft wing plug

There is described a ventilator for ventilating an airway of a patient. The ventilator is generally configured to perform a series of respiration cycles, wherein each respiration cycle includes the delivery of a main volume of fresh respiratory gas into the patient's airway, followed by the evacuation of a corresponding volume of used respiratory gas, and to further perform a series of subcycles during a corresponding one of the respiration cycles, wherein each subcycle includes the delivery of an auxiliary volume of fresh respiratory gas into the patient's airway, followed by the evacuation of a corresponding volume of used respiratory gas, the auxiliary volume being smaller than, and distinct from, the main volume.

Patient ventilator, method of ventilating an airway of a patient, and associated computer program product

An aircraft power system comprises a turbocharger, the turbocharger including a compressor for supplying combustion air to an internal combustion engine, a turbine operatively connected to an internal combustion engine to receive an exhaust flow from the internal combustion engine and convert energy of the exhaust flow into rotational power and, a turbo shaft operatively connecting the turbine to the compressor to transfer at least some of the rotational power to the compressor. A generator is operatively connected to the turbo shaft to receive at least some of the rotational power from the turbo shaft for generating electrical power. At least one electrically powered air-mover is electrically connected to the generator to receive at least some of the electrical power to produce thrust.

Electric distributed propulsion using exhaust recovery power

A hybrid electric aircraft powerplant arrangement can include a first wing pair of powerplants for a first wing of an aircraft, the first wing pair comprising a first electric powerplant configured to drive a first air mover and a first heat engine powerplant configured to drive a second air mover separate from the first air mover. The arrangement can include a second wing pair of powerplants for a second wing of the aircraft, the second wing pair comprising a second electric powerplant configured to drive a third air mover separate from the first and second air movers, and a second heat engine powerplant configured to drive a fourth air mover separate from the first, second, and third air movers.

Hybrid electric aircraft and powerplant arrangements

Aircraft power plants including combustion engines, and associated methods for recuperating waste heat from such aircraft power plants are described. A method includes transferring the heat rejected by the internal combustion engine to supercritical CO(sCO) used as a working fluid in a heat engine. The heat engine converts at least some the heat transferred to the sCOto mechanical energy to perform useful work onboard the aircraft.

Aircraft power plant with supercritical COheat engine

The aircraft includes a fuselage and at least one wing extending from the fuselage. The wing includes first and second original portions and a plug portion positioned between the first and second original portions. A propulsion system is positioned on the at least one wing. The propulsion system includes at least one electric powerplant and at least one combustion powerplant. Each powerplant delivers power to a respective air mover for propelling the aircraft. The electric powerplant and/or the combustion powerplant is positioned outboard from the plug portion. A method for retrofitting an aircraft includes segmenting a wing of an aircraft into two original portions, positioning a plug portion between the two original portions, and connecting the plug portion to one of the two original portions, the first nacelle and/or the second nacelle.

A hybrid propulsion system includes a heat engine configured to drive a heat engine shaft. An electric motor is configured to drive a motor shaft. A transmission system includes at least one gear box. The transmission system is configured to receive rotational input power from each of the heat engine shaft and the motor shaft and to convert the rotation input power to output power. The motor shaft includes a disconnect mechanism to allow the heat engine to rotate with the electric motor stopped. The heat engine shaft includes a disconnect mechanism to allow the electric motor to rotate with the heat engine stopped.

Mechanical disconnects for parallel power lanes in hybrid electric propulsion systems

A hybrid electric engine control module (ECU) configured to be operatively connected to a hybrid electric aircraft powerplant having a heat engine system and an electric motor system to control a torque output from each of the heat engine system and the electric motor system, the ECU being configured to determine whether the electric motor system and/or the heat engine system are in a normal mode such that the electric motor system and/or the heat engine can provide a predetermined amount of torque (e.g., full power). The ECU can be configured to receive a total torque setting and split output power between the electric motor system and the heat engine system in accordance with the normal mode as a function of the total torque setting. The ECU can be configured to detect and command recharging or regenerating of the battery system in some flight conditions.

Normal mode operation of hybrid electric propulsion systems

An aircraft propulsion system is disclosed that includes at least one hybrid-electric powerplant for delivering power to an air mover for propelling the aircraft, wherein the at least one hybrid-electric powerplant includes a heat engine and an electric motor arranged in a parallel drive configuration or an in-line drive configuration.

Distributed propulsion configurations for aircraft having mixed drive systems

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Ste-Julie, Canada

Jean Thomassin