Patents by Inventor Etienne PLAMONDON
Etienne PLAMONDON 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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Publication number: 20240141826Abstract: A rotary engine rotor and a method for supplying rotary engine rotors are provided. The rotary engine rotor has a center axis, a rotor body, a plurality of peripheral surfaces, and a plurality of recess members. The rotor body has a central bore that extends along the center axis. The plurality of peripheral surfaces are disposed around an exterior perimeter of the rotor body. Each of the plurality of recess members are disposed in a respective one of the plurality of peripheral surfaces. Each recess member includes an interior cavity open to an exterior of the rotor.Type: ApplicationFiled: October 28, 2022Publication date: May 2, 2024Inventors: Etienne Plamondon, Michel Bousquet, Ninad Joshi, Vincent Savaria
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Publication number: 20240141838Abstract: A control method is provided for an engine. During this control method, a lambda target parameter indicative of a ratio between a stoichiometric air-to-fuel ratio and an actual air-to-fuel ratio is determined. A control signal is determined using the lambda target parameter. A component of the engine is operated based on the control signal to regulate airflow within a compressor section of the engine.Type: ApplicationFiled: November 1, 2022Publication date: May 2, 2024Inventor: Etienne Plamondon
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Patent number: 11939073Abstract: A method includes using an electric motor to start a thermal engine. The electric motor and thermal engine are connected to one another as the electric motor and the thermal engine of a hybrid-electric power plant in an aircraft. The electric motor can be connected to a combining gear box. The thermal engine can be connected to the combining gear box so that the electric motor and the thermal engine can provide torque to the combining gear box in a parallel hybrid-electric configuration. The combining gearbox can output torque to an air mover for providing thrust to the aircraft.Type: GrantFiled: October 30, 2020Date of Patent: March 26, 2024Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Paul C. Imel, Sebastien Bergeron, Etienne Plamondon, Samuel Gosselin-Brisson, Leonid Guerchkovitch
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Patent number: 11905836Abstract: A rotary engine, has: an outer body defining a rotor cavity; a rotor rotatable within the rotor cavity and in sealing engagement with walls of the outer body and defining at least one chamber of variable volume in the rotor cavity; a pilot subchamber defined by the outer body, the pilot subchamber having an outlet in fluid flow communication with the rotor cavity; and a fuel injector having a tip in communication with the rotor cavity at a location spaced apart from the outlet of the pilot subchamber, the tip of the fuel injector having: a first outlet in fluid communication with the rotor cavity independently of the pilot subchamber; and a second outlet in fluid communication with the rotor cavity through the pilot subchamber.Type: GrantFiled: June 8, 2023Date of Patent: February 20, 2024Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Jonathan Brulatout, Etienne Plamondon
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Patent number: 11459958Abstract: A rotodynamic pump for pumping a fluid includes an impeller, a housing surrounding the impeller, and a pressure regulating mechanism. The pressure regulating mechanism is configured to adjust the clearance between the impeller and the impeller housing to regulate pressure of the fluid downstream of the impeller. A method of regulating the delivery pressure is also disclosed.Type: GrantFiled: March 22, 2019Date of Patent: October 4, 2022Assignee: PRATT & WHITNEY CANADA CORP.Inventors: David Waddleton, Benjamin Renaud, Sebastien Bergeron, Etienne Plamondon, Jean-Gabriel Gauvreau
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Patent number: 11428128Abstract: A rotary internal combustion engine with a housing having a fluid passage defined therethrough opening into a portion of its inner surface engaging each peripheral or apex seal of the rotor. An injector has an inlet for fluid communication with a pressurized lubricant source and a selectively openable and closable outlet in fluid communication with the fluid passage for delivering the pressurized lubricant to each seal through the fluid passage. A housing for a Wankel engine and a method of lubricating peripheral seals of a rotor in an internal combustion engine are also discussed.Type: GrantFiled: April 14, 2021Date of Patent: August 30, 2022Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Edwin Schulz, Etienne Plamondon, Jean Thomassin
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Publication number: 20220135240Abstract: A method includes using an electric motor to start a thermal engine. The electric motor and thermal engine are connected to one another as the electric motor and the thermal engine of a hybrid-electric power plant in an aircraft. The electric motor can be connected to a combining gear box. The thermal engine can be connected to the combining gear box so that the electric motor and the thermal engine can provide torque to the combining gear box in a parallel hybrid-electric configuration. The combining gearbox can output torque to an air mover for providing thrust to the aircraft.Type: ApplicationFiled: October 30, 2020Publication date: May 5, 2022Applicant: Pratt & Whitney Canada Corp.Inventors: Paul C. Imel, Sebastien Bergeron, Etienne Plamondon, Samuel Gosselin-Brisson, Leonid Guerchkovitch
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Patent number: 11280342Abstract: A method of controlling a delivery pressure of an aircraft engine fuel system includes operating a rotodynamic fuel pump hydraulically connected to the fuel system to pump a fluid from an inlet of the rotodynamic pump and out of an outlet of the rotodynamic pump for delivery to the fuel system. The method further includes varying an angular relationship between the inlet and the outlet of the pump to control the delivery pressure. An aircraft engine fuel system and a rotodynamic pump are also described.Type: GrantFiled: April 5, 2019Date of Patent: March 22, 2022Assignee: PRATT & WHITNEY CANADA CORP.Inventors: David Waddleton, Benjamin Renaud, Sebastien Bergeron, Etienne Plamondon, Jean-Gabriel Gauvreau
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Patent number: 11230979Abstract: A liquid fuel system for an aircraft engine includes a first fuel supply conduit hydraulically connected to a fuel source, a second fuel supply conduit hydraulically connected to the engine, a fuel return conduit hydraulically connected to the second fuel supply conduit, and a fuel pump. The fuel pump has a main inlet hydraulically connected to the first fuel supply conduit, an outlet hydraulically connected to the second fuel supply conduit, and an intermediate inlet hydraulically connected to the fuel return conduit. The intermediate inlet is located between the main inlet and the outlet and in use has a pressure between the main inlet pressure and the outlet pressure. A method of supplying a liquid fuel to an aircraft engine is also described.Type: GrantFiled: March 8, 2019Date of Patent: January 25, 2022Assignee: PRATT & WHITNEY CANADA CORP.Inventors: David Waddleton, Benjamin Renaud, Sebastien Bergeron, Etienne Plamondon, Jean-Gabriel Gauvreau
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Publication number: 20210355898Abstract: A rotary internal combustion engine (ICE) has: a housing defining a rotor cavity; a rotor received within the rotor cavity to define working chambers of variable volume around the rotor, the rotor having circumferentially spaced peripheral apex seals biased radially outwardly in sliding engagement against a peripheral wall of the housing to separate the working chambers from one another, the housing having a fluid passage defined therethrough and opening into an inner surface of the peripheral wall; and an injector having a lubricant inlet hydraulically connected to a lubricant source, an actuation inlet hydraulically connected to a source of an actuation fluid, and a lubricant outlet, the injector having an open state in which the lubricant outlet is in fluid flow communication with the fluid passage upon the actuation fluid received within the injector and a closed state in which the lubricant outlet is disconnected from the fluid passage.Type: ApplicationFiled: May 12, 2020Publication date: November 18, 2021Inventors: Etienne PLAMONDON, Sebastien BERGERON, Jean THOMASSIN
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Patent number: 11174732Abstract: A rotary internal combustion engine (ICE) has: a housing defining a rotor cavity; a rotor received within the rotor cavity to define working chambers of variable volume around the rotor, the rotor having circumferentially spaced peripheral apex seals biased radially outwardly in sliding engagement against a peripheral wall of the housing to separate the working chambers from one another, the housing having a fluid passage defined therethrough and opening into an inner surface of the peripheral wall; and an injector having a lubricant inlet hydraulically connected to a lubricant source, an actuation inlet hydraulically connected to a source of an actuation fluid, and a lubricant outlet, the injector having an open state in which the lubricant outlet is in fluid flow communication with the fluid passage upon the actuation fluid received within the injector and a closed state in which the lubricant outlet is disconnected from the fluid passage.Type: GrantFiled: May 12, 2020Date of Patent: November 16, 2021Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Etienne Plamondon, Sebastien Bergeron, Jean Thomassin
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Patent number: 11125185Abstract: There is disclosed an engine assembly for an aircraft, including: a combustion engine including a coolant circuit in heat exchange relationship with a heat sink, the heat sink including a heat exchanger and at least one component, the at least one component having a main function that differs from thermal exchange. A method of operating the system is also disclosed.Type: GrantFiled: January 31, 2019Date of Patent: September 21, 2021Assignee: PRATT & WHIINEY CANADA CORP.Inventors: Sebastien Bergeron, Etienne Plamondon, Andre Julien
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Patent number: 11111848Abstract: A fuel injection system for an aircraft engine has: a first fuel injector having a first actuation inlet, a first fuel inlet connected to a fuel source, and a first fuel outlet connected to the at least one combustion chamber, the first fuel injector defining a first pressure ratio; a second fuel injector having a second actuation inlet, a second fuel inlet connected to the fuel source, and a second fuel outlet connected to the at least one combustion chamber, the second fuel injector defining a second pressure ratio; and an actuation fluid system having a circuit connected to the first actuation inlet and to the second actuation inlet, the first outlet pressure different than the second outlet pressure by having one or both of the first pressure ratio different than the second pressure ratio and a first actuation pressure different than a second actuation pressure.Type: GrantFiled: June 2, 2020Date of Patent: September 7, 2021Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Sebastien Bergeron, Etienne Plamondon, Jean Thomassin
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Patent number: 11092126Abstract: A method of operating an aircraft engine of an aircraft, the aircraft engine having a common-rail fuel injection system for injecting fuel into a combustion chamber of the aircraft engine, including: pressurizing fuel for circulation through the common-rail injection system; circulating a portion of the pressurized fuel through a motive flow inlet of an ejector pump; and entraining a flow through the ejector pump with the portion of the pressurized fuel circulating through the motive flow inlet.Type: GrantFiled: September 3, 2019Date of Patent: August 17, 2021Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Sebastien Bergeron, Etienne Plamondon, Jean-Gabriel Gauvreau, Benjamin Renaud
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Publication number: 20210231033Abstract: A rotary internal combustion engine with a housing having a fluid passage defined therethrough opening into a portion of its inner surface engaging each peripheral or apex seal of the rotor. An injector has an inlet for fluid communication with a pressurized lubricant source and a selectively openable and closable outlet in fluid communication with the fluid passage for delivering the pressurized lubricant to each seal through the fluid passage. A housing for a Wankel engine and a method of lubricating peripheral seals of a rotor in an internal combustion engine are also discussed.Type: ApplicationFiled: April 14, 2021Publication date: July 29, 2021Inventors: Edwin SCHULZ, Etienne PLAMONDON, Jean THOMASSIN
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Patent number: 11008909Abstract: A rotary internal combustion engine with a housing having a fluid passage defined therethrough opening into a portion of its inner surface engaging each peripheral or apex seal of the rotor. An injector has an inlet for fluid communication with a pressurized lubricant source and a selectively openable and closable outlet in fluid communication with the fluid passage for delivering the pressurized lubricant to each seal through the fluid passage. A housing for a Wankel engine and a method of lubricating peripheral seals of a rotor in an internal combustion engine are also discussed.Type: GrantFiled: January 23, 2020Date of Patent: May 18, 2021Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Edwin Schulz, Etienne Plamondon, Jean Thomassin
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Publication number: 20210062772Abstract: A method of operating an aircraft engine of an aircraft, the aircraft engine having a common-rail fuel injection system for injecting fuel into a combustion chamber of the aircraft engine, including: pressurizing fuel for circulation through the common-rail injection system; circulating a portion of the pressurized fuel through a motive flow inlet of an ejector pump; and entraining a flow through the ejector pump with the portion of the pressurized fuel circulating through the motive flow inlet.Type: ApplicationFiled: September 3, 2019Publication date: March 4, 2021Inventors: Sebastien BERGERON, Etienne PLAMONDON, Jean-Gabriel GAUVREAU, Benjamin RENAUD
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Patent number: 10865728Abstract: There is disclosed a method of operating an engine assembly including a combustion engine and a common-rail injector. The method includes: injecting fuel into a combustion chamber of the combustion engine via the common-rail injector thereby generating a backflow of fuel; and powering an actuator using at least a portion of the backflow of fuel. An engine assembly including the combustion engine is disclosed; the engine assembly having a fuel circuit fluidly connecting a fuel source, the common-rail injector, and the second injector outlet together. The fuel circuit has an actuator sub-circuit operatively connected to an outlet of the common-rail injector and an actuator fluidly connected to the actuator sub-circuit.Type: GrantFiled: March 13, 2019Date of Patent: December 15, 2020Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Etienne Plamondon, Sebastien Bergeron, Benjamin Renaud, Jean-Gabriel Gauvreau
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Publication number: 20200318644Abstract: A method of controlling a delivery pressure of an aircraft engine fuel system includes operating a rotodynamic fuel pump hydraulically connected to the fuel system to pump a fluid from an inlet of the rotodynamic pump and out of an outlet of the rotodynamic pump for delivery to the fuel system. The method further includes varying an angular relationship between the inlet and the outlet of the pump to control the delivery pressure. An aircraft engine fuel system and a rotodynamic pump are also described.Type: ApplicationFiled: April 5, 2019Publication date: October 8, 2020Inventors: David WADDLETON, Benjamin RENAUD, Sebastien BERGERON, Etienne PLAMONDON, Jean-Gabriel GAUVREAU
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Publication number: 20200300179Abstract: A rotodynamic pump for pumping a fluid includes an impeller, a housing surrounding the impeller, and a pressure regulating mechanism. The pressure regulating mechanism is configured to adjust the clearance between the impeller and the impeller housing to regulate pressure of the fluid downstream of the impeller. A method of regulating the delivery pressure is also disclosed.Type: ApplicationFiled: March 22, 2019Publication date: September 24, 2020Inventors: David WADDLETON, Benjamin RENAUD, Sebastien BERGERON, Etienne PLAMONDON, Jean-Gabriel GAUVREAU