Pratt-whitney Canada Corp

United Technologies Advanced Projects, Inc.

Jean Dubreuil

Keith Morgan

Eric Durocher

Richard Ullyott

Lazar Mitrovic

Ghislain Plante

Eugene Gekht

Eric LaTulipe

Robert Peluso

Michel Desjardins

Stephen Kenny

Jean Thomassin

Andre Julien

Philippe Beauchesne-Martel

Johnny Vinski

Luc Dionne

Martin Poulin

Ilya Medvedev

Denis Leclair

Kevin Allan Dooley

David Harold Menheere

Louis Brillon

Richard Alan Kostka

Eric Latulipe

Guy Bouchard

Daniel Blais

Xi Wang

Patrick Valois

Stephen Mah

Nashed Youssef

Kevin Ng

Darius Jehangir Karanjia

Xiaoqin Wang

Eric Wintgens

Lazar Miltrovic

Ilya B Medvedev

Stephen Christopher Kenny

Richard Kostka

Nashed Azer Youssef

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

An aircraft power plant has a hybrid propulsion system having an electric motor, an output shaft drivingly connectable to a thrust generator, a combustion engine, a compressor, and a planetary gear train having an Auxiliary Power Unit (APU) mode in which the electric motor is in driving engagement with the compressor via the planetary gear train while the combustion engine is disengaged from the output shaft, and a propulsion mode in which the combustion engine and the electric motor are in driving engagement with the output shaft via the planetary gear train.

Hybrid aircraft propulsion power plants

A gas turbine engine has a first spool having a low pressure compressor section disposed forward of an air inlet along a direction of travel of the engine, and a low pressure turbine section disposed forward of the low pressure compressor section and drivingly engaged thereto. A second spool has a high pressure compressor section disposed forward of the low pressure compressor section, and a high pressure turbine section disposed forward of the high pressure compressor section and drivingly engaged thereto. The high pressure turbine section is disposed aft of the low pressure turbine section. An output drive shaft drivingly engages the low pressure turbine section and extends forwardly therefrom to drive a rotatable load. A method of operating a gas turbine engine is also discussed.

Reverse-flow gas turbine engine

An aircraft power plant has: an electric motor; a compressor; a combustion engine; an output shaft drivingly engageable to a thrust generator for propelling an aircraft equipped with the aircraft power plant; and a transmission including a gearbox having a first input drivingly engaged by the electric motor, a first output drivingly engaging the compressor, a second input drivingly engageable by the combustion engine, and a second output drivingly engageable to the output shaft, wherein the transmission has: a propulsion configuration in which the output shaft and the compressor are drivingly engaged to the electric motor and to the combustion engine via the gearbox, and an auxiliary power unit configuration in which the combustion engine and the output shaft are at rest while the electric motor drivingly engages the compressor.

An aircraft power plant has a hybrid propulsion system having an electric motor, a combustion engine, an output shaft drivingly connectable to a thrust generator, a compressor, and a transmission having a first transmission drive path and a second transmission drive path, the combustion engine and the output shaft in driving engagement with the first transmission drive path, the electric motor selectively drivingly engageable to the compressor via either the first drive path or via the second drive path.

A hybrid propulsion system includes a heat engine configured to drive a heat engine shaft. An electric motor configured to drive a motor shaft. A transmission system is connected 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. A first lubrication/coolant system is connected for circulating a first lubricant/coolant fluid through the heat engine. A second lubricant/coolant system in fluid isolation from the first lubrication/coolant system is connected for circulating a second lubricant/coolant fluid through the electric motor.

Circulating coolant fluid in hybrid electrical propulsion systems

A gas turbine engine has a first spool having a low pressure compressor section in fluid communication with an air inlet, the low pressure compressor section including a first plurality of variable guide vanes therein, and a low pressure turbine section drivingly engaged to the low pressure compressor section. A second spool has a high pressure compressor section in fluid communication with the low pressure compressor section to receive pressurized air therefrom, the high pressure compressor section including a second plurality of variable guide vanes at an entry thereof, and a high pressure turbine section drivingly engaged to the high pressure compressor section, the high pressure turbine section disposed upstream of the low pressure turbine section and in fluid communication therewith. An output drive shaft drivingly engages the low pressure turbine section and is adapted to drivingly engage a rotatable load of the gas turbine engine.

An aircraft power plant has: a hybrid propulsion system having an electric motor, an output shaft drivingly connectable to a thrust generator, a combustion engine, a compressor, and a transmission having a first transmission drive path and a second transmission drive path selectively engageable to the first transmission drive path, the electric motor and the compressor in driving engagement with the first transmission drive path, the combustion engine and the output shaft in driving engagement with the second transmission drive path.

A multi-spool gas turbine engine comprises a low pressure (LP) spool and a high pressure (HP) spool independently rotatable about a central axis extending through an accessory gear box (AGB). The LP spool has an LP compressor, which is axially positioned between the HP compressor of the HP spool and the AGB. A tower shaft drivingly connects the HP spool to the AGB.

Multi-spool gas turbine engine architecture

A gas turbine engine has an engine case housing a low pressure compressor drivingly connected to a low pressure turbine by a low pressure compressor shaft extending along an engine axis. The low pressure turbine is disposed forward of the low pressure compressor. A low pressure turbine shaft is drivingly connected to the low pressure turbine and extends forwardly of the low pressure turbine. A reduction gear box (RGB) is drivingly connected to the low pressure turbine shaft. The RGB is offset from the engine axis to free an access to low pressure compressor shaft connection. The offset positioning of the RGB allows to provide an access port in an axially forwardly facing surface of the engine case to access the low pressure compressor shaft and more particularly a connection thereof to the low pressure turbine.

Reverse flow gas turbine engine with offset RGB

A gas turbine engine has an in-line mounted accessory gear box (AGB) and an accessory drivingly connected to the AGB, the accessory being oriented transversally to the engine centerline.

Gas turbine engine accessories arrangement

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Boucherville, Canada

Jean Dubreuil