Patents by Inventor Robert PELUSO
Robert PELUSO 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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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: 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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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: 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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Publication number: 20180073428Abstract: 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: September 15, 2016Publication date: March 15, 2018Inventors: Keith MORGAN, Robert PELUSO, Ghislain PLANTE, Eugene GEKHT, Eric DUROCHER, Jean DUBREUIL