Patents by Inventor Jean Dubreuil
Jean Dubreuil has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Patent number: 11827368Abstract: 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.Type: GrantFiled: March 26, 2020Date of Patent: November 28, 2023Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Jean Dubreuil, Richard Ullyott
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Patent number: 11773785Abstract: 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.Type: GrantFiled: January 12, 2023Date of Patent: October 3, 2023Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Keith Morgan, Robert Peluso, Ghislain Plante, Eugene Gekht, Eric Durocher, Jean Dubreuil
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Publication number: 20230151772Abstract: 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.Type: ApplicationFiled: January 12, 2023Publication date: May 18, 2023Inventors: Keith Morgan, Robert Peluso, Ghislain Plante, Eugene Gekht, Eric Durocher, Jean Dubreuil
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Publication number: 20230137264Abstract: 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.Type: ApplicationFiled: December 21, 2022Publication date: May 4, 2023Applicant: Pratt & Whitney Canada Corp.Inventors: Eric LaTulipe, Jean Thomassin, Xiaoqin Wang, Jean Dubreuil, Luc Dionne, Andre Julien
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Patent number: 11560233Abstract: 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.Type: GrantFiled: August 31, 2021Date of Patent: January 24, 2023Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Jean Dubreuil, Richard Ullyott
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Patent number: 11555453Abstract: 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.Type: GrantFiled: July 6, 2021Date of Patent: January 17, 2023Assignee: Pratt & Whitney Canada Corp.Inventors: Keith Morgan, Robert Peluso, Ghislain Plante, Eugene Gekht, Eric Durocher, Jean Dubreuil
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Patent number: 11535392Abstract: 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.Type: GrantFiled: December 6, 2019Date of Patent: December 27, 2022Assignee: Pratt & Whitney Canada Corp.Inventors: Eric LaTulipe, Jean Thomassin, Xi Wang, Jean Dubreuil, Luc Dionne, Andre Julien
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Patent number: 11485503Abstract: 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.Type: GrantFiled: March 26, 2020Date of Patent: November 1, 2022Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Jean Dubreuil, Richard Ullyott
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Patent number: 11453508Abstract: 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.Type: GrantFiled: December 20, 2021Date of Patent: September 27, 2022Assignee: Pratt & Whitney Canada Corp.Inventors: Jean Dubreuil, Eric LaTulipe
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Patent number: 11415063Abstract: 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.Type: GrantFiled: September 15, 2016Date of Patent: August 16, 2022Assignee: Pratt & Whitney Canada Corp.Inventors: Keith Morgan, Robert Peluso, Ghislain Plante, Eugene Gekht, Eric Durocher, Jean Dubreuil
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Patent number: 11408352Abstract: 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.Type: GrantFiled: October 22, 2020Date of Patent: August 9, 2022Assignee: Pratt & Whitney Canada Corp.Inventors: Keith Morgan, Robert Peluso, Ghislain Plante, Eugene Gekht, Eric Durocher, Jean Dubreuil, Stephen Mah, Philippe Beauchesne-Martel
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Publication number: 20220185494Abstract: 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.Type: ApplicationFiled: December 20, 2021Publication date: June 16, 2022Applicant: Pratt & Whitney Canada Corp.Inventors: Jean Dubreuil, Eric LaTulipe
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Publication number: 20220119119Abstract: 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.Type: ApplicationFiled: August 31, 2021Publication date: April 21, 2022Inventors: Jean DUBREUIL, Richard ULLYOTT
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Patent number: 11305883Abstract: 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.Type: GrantFiled: December 6, 2019Date of Patent: April 19, 2022Assignee: United Technologies Advanced Projects, Inc.Inventors: Jean Dubreuil, Eric LaTulipe
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Publication number: 20210404388Abstract: 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.Type: ApplicationFiled: July 6, 2021Publication date: December 30, 2021Inventors: Keith Morgan, Robert Peluso, Ghislain Plante, Eugene Gekht, Eric Durocher, Jean Dubreuil
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Patent number: 11186378Abstract: 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.Type: GrantFiled: March 26, 2020Date of Patent: November 30, 2021Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Jean Dubreuil, Richard Ullyott
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Publication number: 20210270183Abstract: 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.Type: ApplicationFiled: October 22, 2020Publication date: September 2, 2021Inventors: Keith MORGAN, Robert PELUSO, Ghislain PLANTE, Eugene GEKHT, Eric DUROCHER, Jean DUBREUIL, Stephen MAH, Philippe BEAUCHESNE-MARTEL
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Patent number: 11041443Abstract: 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.Type: GrantFiled: September 26, 2019Date of Patent: June 22, 2021Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Eric Durocher, Keith Morgan, Lazar Mitrovic, Jean Dubreuil, Martin Poulin
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Patent number: 11035293Abstract: 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.Type: GrantFiled: January 17, 2017Date of Patent: June 15, 2021Assignee: PRATT & WHITNEY CANADA CORP.Inventor: Jean Dubreuil
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Patent number: 10815899Abstract: 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.Type: GrantFiled: November 15, 2016Date of Patent: October 27, 2020Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Lazar Mitrovic, Jean Dubreuil, Eric Durocher, Keith Morgan, Michel Desjardins