Patents by Inventor Ghislain Plante
Ghislain Plante 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: 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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Patent number: 11719247Abstract: A reverse flow gas turbine engine has a low pressure (LP) spool and a high pressure (HP) spool arranged sequentially in an axial direction. The LP spool comprises an LP compressor disposed forward of an LP turbine and drivingly connected thereto via an LP compressor gear train. The HP spool comprises an HP compressor in flow communication with the LP compressor, and an HP turbine disposed forward of the HP compressor and drivingly connected thereto via an HP shaft.Type: GrantFiled: August 19, 2021Date of Patent: August 8, 2023Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Ghislain Plante, Patrick Valois
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Publication number: 20230243310Abstract: A gas turbine engine having: an engine core having, in serial flow communication, a low-pressure compressor, a high-pressure compressor, a high-pressure turbine drivingly connected to the high-pressure compressor, and a low-pressure turbine drivingly connected to an output shaft; and a clutch having a disengaged configuration in which the low-pressure turbine is drivingly disconnected from the low-pressure compressor such that, in the disengaged configuration, the clutch disengages the low-pressure turbine from the low-pressure compressor, and an engaged configuration in which the low-pressure turbine is drivingly connected to the low-pressure compressor, the low-pressure turbine drivingly connected to the output shaft in both of the engaged and disengaged configurations of the clutch.Type: ApplicationFiled: April 13, 2023Publication date: August 3, 2023Inventors: Ghislain PLANTE, Patrick VALOIS
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Patent number: 11668245Abstract: A gas turbine engine having: an engine core having, in serial flow communication, a low-pressure compressor, a high-pressure compressor, a high-pressure turbine drivingly connected to the high-pressure compressor, and a low-pressure turbine drivingly connected to an output shaft; and a clutch having a disengaged configuration in which the low-pressure turbine is drivingly disconnected from the low-pressure compressor such that, in the disengaged configuration, the clutch disengages the low-pressure turbine from the low-pressure compressor, and an engaged configuration in which the low-pressure turbine is drivingly connected to the low-pressure compressor, the low-pressure turbine drivingly connected to the output shaft in both of the engaged and disengaged configurations of the clutch.Type: GrantFiled: January 28, 2020Date of Patent: June 6, 2023Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Ghislain Plante, Patrick Valois
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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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Patent number: 11629665Abstract: An aircraft engine has a high pressure spool including a high pressure turbine drivingly connected to a high pressure compressor. A low pressure spool including a low pressure compressor is fluidly connected to the high pressure compressor. A low pressure turbine is drivingly connected to the low pressure compressor to drive the low pressure compressor. A load is drivingly connected to the low pressure turbine, the load consisting of one of a propeller and a helicopter rotor. A method of creating classes of an aircraft engine from an engine platform is disclosed.Type: GrantFiled: September 10, 2019Date of Patent: April 18, 2023Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Ghislain Plante, Keith Morgan, Stephen Mah, Patrick Valois, Robert Peluso
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Patent number: 11578663Abstract: A method of providing an engine family includes providing a first engine having a low pressure turbine driving a low pressure compressor at a first speed ratio, and a high pressure turbine driving a high pressure compressor. The method includes providing a second engine by changing the first speed ratio of the first engine to a second speed ratio.Type: GrantFiled: September 10, 2019Date of Patent: February 14, 2023Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Ghislain Plante, Keith Morgan, Stephen Mah, Patrick Valois, Robert Peluso
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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: 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: 20220074349Abstract: A turboprop or turboshaft gas turbine engine includes a low pressure turbine drivingly engaged to an output shaft for driving a rotatable load. A low pressure compressor is de-coupled from the low pressure turbine, the low pressure compressor and turbine rotating independently from one another. A high pressure compressor is disposed downstream from the low pressure compressor and is in fluid communication therewith to receive pressurized air therefrom. A high pressure turbine is disposed downstream from the high pressure compressor and is drivingly engaged thereto via a high pressure shaft. The high pressure turbine is disposed upstream from the low pressure turbine and is in fluid communication therewith. An electric motor receives power from a power source, is drivingly engaged to the low pressure compressor, and is operable to drive the low pressure compressor independently from the low pressure turbine, the high pressure compressor and the high pressure turbine.Type: ApplicationFiled: September 8, 2020Publication date: March 10, 2022Inventors: Patrick VALOIS, Hervé TURCOTTE, Ghislain PLANTE
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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: 11199096Abstract: A turbomachine airfoil element comprises an airfoil having: an inboard end; an outboard end; a leading edge; a trailing edge; a pressure side; and a suction side. A span between the inboard end and the outboard end is 1.75-2.20 inches. A chord length at 50% span is 1.05-1.35 inches. At least two of: a first mode resonance frequency is 2400±10% Hz; a second mode resonance frequency is 4950±10% Hz; a third mode resonance frequency is 7800±10% Hz; a fourth mode resonance frequency is 8700±10% Hz; and a fifth mode resonance frequency is 12500±10% Hz.Type: GrantFiled: January 15, 2018Date of Patent: December 14, 2021Assignee: Raytheon Technologies CorporationInventors: Michael Leslie Clyde Papple, David A. Niezelski, Daniel Lecuyer, XingYun Haggard, Domenico Di Florio, Francois Caron, John R. Battye, Panagiota Tsifourdaris, Ghislain Plante, Timothy J. Jennings, Rene Paquet
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Publication number: 20210381517Abstract: A reverse flow gas turbine engine has a low pressure (LP) spool and a high pressure (HP) spool arranged sequentially in an axial direction. The LP spool comprises an LP compressor disposed forward of an LP turbine and drivingly connected thereto via an LP compressor gear train. The HP spool comprises an HP compressor in flow communication with the LP compressor, and an HP turbine disposed forward of the HP compressor and drivingly connected thereto via an HP shaft.Type: ApplicationFiled: August 19, 2021Publication date: December 9, 2021Inventors: Ghislain PLANTE, Patrick VALOIS
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Patent number: 11125239Abstract: A reverse flow gas turbine engine has a low pressure (LP) spool and a high pressure (HP) spool arranged sequentially in an axial direction. The LP spool comprises an LP compressor disposed forward of an LP turbine and drivingly connected thereto via an LP compressor gear train. The HP spool comprises an HP compressor in flow communication with the LP compressor, and an HP turbine disposed forward of the HP compressor and drivingly connected thereto via an HP shaft.Type: GrantFiled: December 17, 2019Date of Patent: September 21, 2021Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Ghislain Plante, Patrick Valois
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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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Publication number: 20210239053Abstract: Herein provided are methods and systems for controlling an engine having a variable geometry mechanism. A pressure ratio between a first pressure at an inlet of the engine and a predetermined reference pressure is determined. An output power for the engine is determined. The output power is adjusted based at least in part on the pressure ratio to obtain a corrected output power. A position control signal for a variable geometry mechanism of the engine is generated based on the corrected output power and the pressure ratio. The position control signal is output to a controller of the engine to control the variable geometry mechanism.Type: ApplicationFiled: March 29, 2021Publication date: August 5, 2021Inventors: Philippe Beauchesne-Martel, Poi Loon Tang, Andrew Thompson, Ghislain Plante
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Publication number: 20210231058Abstract: A gas turbine engine having: an engine core having, in serial flow communication, a low-pressure compressor, a high-pressure compressor, a high-pressure turbine drivingly connected to the high-pressure compressor, and a low-pressure turbine drivingly connected to an output shaft; and a clutch having a disengaged configuration in which the low-pressure turbine is drivingly disconnected from the low-pressure compressor such that, in the disengaged configuration, the clutch disengages the low-pressure turbine from the low-pressure compressor, and an engaged configuration in which the low-pressure turbine is drivingly connected to the low-pressure compressor, the low-pressure turbine drivingly connected to the output shaft in both of the engaged and disengaged configurations of the clutch.Type: ApplicationFiled: January 28, 2020Publication date: July 29, 2021Inventors: Ghislain PLANTE, Patrick VALOIS
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Patent number: 10961919Abstract: Herein provided are methods and systems for controlling an engine having a variable geometry mechanism. A pressure ratio between a first pressure at an inlet of the engine and a predetermined reference pressure is determined. An output power for the engine is determined. The output power is adjusted based at least in part on the pressure ratio to obtain a corrected output power. A position control signal for a variable geometry mechanism of the engine is generated based on the corrected output power and the pressure ratio. The position control signal is output to a controller of the engine to control the variable geometry mechanism.Type: GrantFiled: July 11, 2018Date of Patent: March 30, 2021Assignee: PRATT & WHITNEY CANADA CORPInventors: Philippe Beauchesne-Martel, Poi Loon Tang, Andrew Thompson, Ghislain Plante
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Patent number: 10808624Abstract: A method and a turbine rotor system for reducing over-speed potential of a turbine of a gas turbine engine involve mechanically connecting the turbine to at least two mechanical loads via first and second mechanical drives extending in opposite directions from the turbine.Type: GrantFiled: February 9, 2017Date of Patent: October 20, 2020Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Jean Dubreuil, Ghislain Plante, Philippe Beauchesne-Martel