Patents by Inventor Patrick VALOIS
Patrick VALOIS 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: 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: 11702954Abstract: A method is provided for an engine. During this method, a database is provided for a parameter of the engine. The database includes a plurality of values for the parameter determined over a period of time. Confidence bands are established using a probability density function on the database. An action is performed in response to a comparison of a first updated value for the parameter to the confidence bands. The engine may be configured as a gas turbine engine or another type of heat engine.Type: GrantFiled: May 13, 2022Date of Patent: July 18, 2023Assignee: Pratt & Whitney Canada Corp.Inventors: Patrick Valois, Robert Wigny
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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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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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Publication number: 20230096526Abstract: An aircraft power plant comprising: a high-pressure spool including a high-pressure compressor, a high-pressure turbine, and a high-pressure shaft drivingly engaging the high-pressure turbine to the high-pressure compressor; a low-pressure spool including a low-pressure compressor, a low-pressure turbine, and a low-pressure shaft drivingly engaging the low-pressure turbine to the low-pressure compressor; an electrical machine operable as a generator; and a transmission having a first input drivingly engaged by the high-pressure shaft, a second input drivingly engaged by the low-pressure shaft, and an output drivingly engaging the electrical machine, the transmission having a coupling system selectively interconnecting the output with one of: the first input, with the second input disconnected from the output; the second input, with the first input disconnected from the output; and both of the first input and the second input.Type: ApplicationFiled: September 24, 2021Publication date: March 30, 2023Inventor: Patrick VALOIS
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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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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: 20210388733Abstract: An hybrid aircraft power plant, has: a gas turbine engine having a high-pressure spool including a high-pressure compressor, a high-pressure turbine, and a high-pressure shaft drivingly engaging the high-pressure turbine to the high-pressure compressor, a low-pressure spool including a low-pressure compressor, a low-pressure turbine, and a low-pressure shaft drivingly engaging the low-pressure turbine to the low-pressure compressor; an electric motor drivingly engaged to the low-pressure shaft; and a torque-transmitting device operatively connected to the HP-shaft and having an engaged configuration in which the torque-transmitting device drivingly engages the electric motor to the high-pressure shaft and a disengaged configuration in which the torque-transmitting device disconnects the electric motor from the high-pressure shaft.Type: ApplicationFiled: January 25, 2021Publication date: December 16, 2021Inventors: Patrick VALOIS, Hervé TURCOTTE, Richard FREER, Jonatan TREMBLAY, Eric LATULIPE
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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: 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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Publication number: 20200141416Abstract: 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: December 17, 2019Publication date: May 7, 2020Inventors: Ghislain PLANTE, Patrick VALOIS
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Publication number: 20200141328Abstract: 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: ApplicationFiled: September 10, 2019Publication date: May 7, 2020Inventors: Ghislain PLANTE, Keith MORGAN, Stephen MAH, Patrick VALOIS, Robert PELUSO
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Publication number: 20200080516Abstract: 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: ApplicationFiled: September 10, 2019Publication date: March 12, 2020Inventors: Ghislain PLANTE, Keith MORGAN, Stephen MAH, Patrick VALOIS, Robert PELUSO
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Patent number: 10533559Abstract: 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 20, 2016Date of Patent: January 14, 2020Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Ghislain Plante, Patrick Valois
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Publication number: 20180216525Abstract: A gas turbine engine has an engine core including a low pressure compressor, a high pressure compressor, a high pressure turbine and a low pressure turbine coaxially mounted about an engine axis and fluidly connected in series by a core gaspath. The low pressure turbine is drivingly connected to the low pressure compressor via an external shaft disposed radially outwardly of the core gaspath.Type: ApplicationFiled: January 30, 2017Publication date: August 2, 2018Inventors: Ghislain PLANTE, Patrick VALOIS, Jean DUBREUIL, Daniel BLAIS
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Publication number: 20180172012Abstract: 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: December 20, 2016Publication date: June 21, 2018Inventors: Ghislain PLANTE, Patrick VALOIS