Patents by Inventor Thomas Trevor
Thomas Trevor 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: 20250243819Abstract: A method of and system for operating a hybrid electric propulsion system for an aircraft in a start sequence is provided. The hybrid electric propulsion system includes a thermal engine, an electric motor, a gearbox, an electric power storage unit, and a propulsion unit having a propeller having propeller blades. The method includes: driving the propeller from a static state to a target rotational speed within a predetermined range of speeds using the electric motor; transitioning the propeller blades from a feathered mode to an unfeathered mode while the propeller is being driven at the target rotational speed solely by the electric motor; starting the thermal engine; and transitioning the driving of the propeller using the electric motor to driving the propeller using the thermal engine.Type: ApplicationFiled: March 3, 2025Publication date: July 31, 2025Inventors: Yusuf Syed, Thomas Trevor Ricci, James Jarvo
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Publication number: 20250244203Abstract: Methods and systems for detecting a torque transmission failure in an aircraft power plant are provided. The system comprises a hydrostatic transmission for transmitting torque between a first shaft and a second shaft using hydraulic fluid, an a failure detector including a sensor configured to detect a pressure change in the hydraulic fluid. The failure detector is configured to generate an output indicative of the torque transmission failure in response to the pressure change having crossed a threshold.Type: ApplicationFiled: January 26, 2024Publication date: July 31, 2025Inventors: Xuening LU, Ezzat MESHKINFAM, Etienne PLAMONDON, Thomas Trevor RICCI
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Publication number: 20250206459Abstract: An indication system for a hybrid aircraft power plant including an electric motor and a heat engine for driving an air mover configured to propel an aircraft is provided. The indication system includes a display providing a display area and a computer operatively connected to the display. The computer is configured to cause a first visual indication to be generated in the display area of the display. The first visual indication indicates a current amount of energy stored in a battery powering the electric motor of the hybrid aircraft power plant along a scale. The computer is configured to cause a second visual indication to be generated in the same display area of the display. The second visual indication indicates a remaining run time for the electric motor based on the current amount of energy stored in the battery.Type: ApplicationFiled: December 20, 2023Publication date: June 26, 2025Inventors: Yusuf SYED, Raphael GARIEPY, Thomas Trevor RICCI, Todd YOUNG, Piotr TWARECKI
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Patent number: 12318988Abstract: An extrudate cooling tank having cooling water chambers adapted for running passage of extrudate serially therethrough at a preselected regulated variable pressures with water in the chambers being at different temperatures, and a wheel-servo motor combination hingedly connected to the chamber and being movable with respect thereto between a first position with the wheel engaging running extrudate and a second position with the wheel remote from engagement with the extrudate.Type: GrantFiled: September 26, 2023Date of Patent: June 3, 2025Assignee: Reel Power Licensing Corp.Inventors: Richard Vester, Steven Gillmeister, Thomas Trevor Bludis, Robert H. Bessemer
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Patent number: 12297738Abstract: A rotary engine, comprising: housings defining a rotor cavity and respective coolant passages fluidly connected in parallel to a source of coolant; a rotor within the rotor cavity; and a cooling system including: a flow regulating device in fluid communication with the respective coolant passages; a heat exchanger facilitating heat exchange between the coolant and a heat-transfer medium; and a controller operatively connected to the flow regulating device to: determine, based on an engine parameter and an environment parameter of the rotary engine, a flow rate of the coolant to be injected towards the respective coolant passages to maintain the housings within a temperature range, the engine parameter indicative of a quantity of heat generated by the rotary engine, the environment parameter indicative of a quantity of heat the heat exchanger is able to transfer to the heat-transfer medium; and cause the coolant to flow towards at the flow rate.Type: GrantFiled: January 8, 2024Date of Patent: May 13, 2025Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Etienne Plamondon, Thomas Trevor Ricci, Jeremie Barberger, Michel Bousquet
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Patent number: 12300991Abstract: A hybrid-electric powerplant (HEP) of an aircraft comprises a thermal engine providing a first torque input to the HEP and an electric motor providing a second torque input to the HEP. A power management system connected to one or both of the thermal engine and the electric motor comprises an engine control unit (ECU) connected to the thermal engine. The ECU controls fuel supplied to the thermal engine. An electric propulsion control (EPC) is connected to the electric motor and controls power supplied to the electric motor. The EPC includes an EPC protection module in communication with a power source for the electric motor. The EPC protection module disables power supplied to the electric motor upon receipt of a signal indicative of one or more of an over-speed condition and an over-torque condition detected in the HEP.Type: GrantFiled: October 4, 2022Date of Patent: May 13, 2025Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Yusuf Syed, Thomas Trevor Ricci, James Robert Jarvo
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Publication number: 20250099109Abstract: Methods and systems for pressure application are provided. A pressure application system comprises a base assembly having an upper profile and a lower profile, a chassis coupled to the base assembly, a ratchet, a handle coupled with the ratchet, and at least on strap retention mechanism coupled to the chassis. The ratchet extends through the chassis and least partially in the base assembly. The handle is coupled with the ratchet such that a movement of the handle moves the ratchet. The at least one strap retention mechanism is configured to receive a strap retention mechanism.Type: ApplicationFiled: August 30, 2024Publication date: March 27, 2025Inventors: Chibueze Joseph Ihenacho, Thomas Trevor Bludis, Andrew James Stephens
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Patent number: 12241425Abstract: A method of and system for operating a hybrid electric propulsion system for an aircraft in a start sequence is provided. The hybrid electric propulsion system includes a thermal engine, an electric motor, a gearbox, an electric power storage unit, and a propulsion unit having a propeller having propeller blades. The method includes: driving the propeller from a static state to a target rotational speed within a predetermined range of speeds using the electric motor; transitioning the propeller blades from a feathered mode to an unfeathered mode while the propeller is being driven at the target rotational speed solely by the electric motor; starting the thermal engine; and transitioning the driving of the propeller using the electric motor to driving the propeller using the thermal engine.Type: GrantFiled: February 8, 2024Date of Patent: March 4, 2025Assignee: Pratt & Whitney Canada Corp.Inventors: Yusuf Syed, Thomas Trevor Ricci, James Jarvo
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Patent number: 12129043Abstract: A system is provided for an aircraft. This aircraft system includes a heat exchanger, a lubricant flow circuit and a bypass valve. The lubricant flow circuit includes an inlet passage, an outlet passage, a heat exchanger passage and a bypass passage. The heat exchanger passage extends through the heat exchanger. The bypass passage bypasses the heat exchanger. The heat exchanger passage and the bypass passage are fluidly coupled in parallel between the inlet passage and the outlet passage. The bypass valve is fluidly coupled inline along the lubricant flow circuit. The bypass valve is operable to regulate lubricant flow through the bypass passage. The bypass valve includes a rotary electric motor.Type: GrantFiled: August 28, 2023Date of Patent: October 29, 2024Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Xuening Lu, Ezzat Meshkinfam, Thomas Trevor Ricci
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Publication number: 20240271547Abstract: A hybrid electric propulsion system for an aircraft is provided that includes a thermal engine, an electric motor, a gearbox, an electric power storage unit, a propulsion unit, and a controller. The thermal engine has a main oil pump configured to be driven by the thermal engine. The gearbox is in communication with the thermal and electric motors. The propulsion unit includes a propeller having propeller blades, and a pitch change mechanism. The controller is in communication with the thermal and electric motors, the propulsion unit, and a memory storing instructions. The instructions when executed cause the controller to control the electric motor to operate using electrical power from the electric power storage unit to cause the main oil pump to actuate and produce a flow of engine oil to the pitch change mechanism for a period of time sufficient to feather the propeller blades.Type: ApplicationFiled: February 8, 2024Publication date: August 15, 2024Inventors: Yusuf Syed, Thomas Trevor Ricci, James Jarvo
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Publication number: 20240271577Abstract: A method of and system for operating a hybrid electric propulsion system for an aircraft in a start sequence is provided. The hybrid electric propulsion system includes a thermal engine, an electric motor, a gearbox, an electric power storage unit, and a propulsion unit having a propeller having propeller blades. The method includes: driving the propeller from a static state to a target rotational speed within a predetermined range of speeds using the electric motor; transitioning the propeller blades from a feathered mode to an unfeathered mode while the propeller is being driven at the target rotational speed solely by the electric motor; starting the thermal engine; and transitioning the driving of the propeller using the electric motor to driving the propeller using the thermal engine.Type: ApplicationFiled: February 8, 2024Publication date: August 15, 2024Inventors: Yusuf Syed, Thomas Trevor Ricci, James Jarvo
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Patent number: 12043402Abstract: An assembly for an aircraft propulsion system includes an intercooler assembly and a controller. The intercooler assembly includes an intercooler and a flow control assembly. The intercooler includes a primary air inlet, a primary air outlet, a secondary air inlet, and a secondary air outlet. The flow control assembly is disposed at the secondary air outlet. The flow control assembly includes an actuator and at least one flap. The actuator is configured to position the at least one flap in an open position, a closed position, and intermediate positions. The controller is configured to control the actuator to position the at least one flap in the open position, determine a hot-side heat transfer effectiveness of the intercooler and a hot-side mass flow rate for the intercooler, determine a cold-side mass flow rate of the intercooler, identify a position of the actuator, and identify a successful or an unsuccessful actuator range check for the actuator.Type: GrantFiled: September 26, 2023Date of Patent: July 23, 2024Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Xuening Lu, Ezzat Meshkinfam, Thomas Trevor Ricci
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Patent number: 12006883Abstract: The method can include, while the airplane is on the ground: entering a disking mode including positioning the blades at a disking pitch including rotating each blade around the length, the disking pitch oriented parallel to the plane of rotation; maintaining the blades at the disking pitch; and exiting the disking mode when a disking mode exit condition is met, including rotating each blade around the length, away from the disking pitch.Type: GrantFiled: February 4, 2022Date of Patent: June 11, 2024Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Nicolas Des Roches-Dionne, Thomas Trevor Ricci, Charles Bolon-Bruhn, Jeremie Hebert
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Publication number: 20240113513Abstract: A hybrid-electric powerplant (HEP) of an aircraft comprises a thermal engine providing a first torque input to the HEP and an electric motor providing a second torque input to the HEP. A power management system connected to one or both of the thermal engine and the electric motor comprises an engine control unit (ECU) connected to the thermal engine. The ECU controls fuel supplied to the thermal engine. An electric propulsion control (EPC) is connected to the electric motor and controls power supplied to the electric motor. The EPC includes an EPC protection module in communication with a power source for the electric motor. The EPC protection module disables power supplied to the electric motor upon receipt of a signal indicative of one or more of an over-speed condition and an over-torque condition detected in the HEP.Type: ApplicationFiled: October 4, 2022Publication date: April 4, 2024Inventors: Yusuf SYED, Thomas Trevor RICCI, James Robert JARVO
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Publication number: 20240017464Abstract: An extrudate cooling tank having cooling water chambers adapted for running passage of extrudate serially therethrough at a preselected regulated variable pressures with water in the chambers being at different temperatures, and a wheel-servo motor combination hingedly connected to the chamber and being movable with respect thereto between a first position with the wheel engaging running extrudate and a second position with the wheel remote from engagement with the extrudate.Type: ApplicationFiled: September 26, 2023Publication date: January 18, 2024Applicant: Novatec, Inc.Inventors: Richard VESTER, Steven GILLMEISTER, Thomas Trevor BLUDIS, Robert H. BESSEMER
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Publication number: 20230250766Abstract: The method can include, while the airplane is on the ground: entering a disking mode including positioning the blades at a disking pitch including rotating each blade around the length, the disking pitch oriented parallel to the plane of rotation; maintaining the blades at the disking pitch; and exiting the disking mode when a disking mode exit condition is met, including rotating each blade around the length, away from the disking pitch.Type: ApplicationFiled: February 4, 2022Publication date: August 10, 2023Inventors: Nicolas DES ROCHES-DIONNE, Thomas Trevor RICCI, Charles BOLON-BRUHN, Jeremie HEBERT
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Patent number: 11459955Abstract: A method of deactivating a liquid distribution system of a gas turbine engine in the event of a fire condition includes introducing a quantity of air into the liquid distribution system at a location upstream of a liquid pump of the liquid distribution system. The quantity of air is greater than a liquid discharge capacity of the liquid pump, thereby starving the liquid pump.Type: GrantFiled: November 15, 2019Date of Patent: October 4, 2022Assignee: PRATT & WHITNEY CANADA CORP.Inventor: Thomas Trevor Ricci
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Patent number: 11203133Abstract: Method and apparatus for drying granular resin material by heating compressed air to a temperature prescribed for gas separation membrane operation, presenting the heated compressed air to a membrane separating out oxygen-size and smaller molecules to provide a stream of gas molecules of at least nitrogen-size at a pressure substantially that of the compressed air, heating the stream of gas molecules of at least nitrogen-size to a temperature at which dew point of the stream is no higher than ?40 degrees F., and introducing the heated stream of gas molecules into a chamber for upward flow to atmosphere through granular resin material in the chamber.Type: GrantFiled: January 2, 2020Date of Patent: December 21, 2021Assignee: Novatec, Inc.Inventors: Conrad Bessemer, Mark Haynie, Gregory Michael Washburn, Thomas Trevor Bludis
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Publication number: 20210213667Abstract: An extrudate cooling tank having cooling water chambers adapted for running passage of extrudate serially therethrough at a preselected regulated variable pressures with water in the chambers being at different temperatures, and a wheel-servo motor combination hingedly connected to the chamber and being movable with respect thereto between a first position with the wheel engaging running extrudate and a second position with the wheel remote from engagement with the extrudate.Type: ApplicationFiled: January 15, 2021Publication date: July 15, 2021Applicant: Novatec, Inc.Inventors: Richard VESTER, Steven GILLMEISTER, Thomas Trevor BLUDIS, Robert H. BESSEMER
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Patent number: 10705038Abstract: There is described herein methods and systems for detecting of metallic chips in a fluid system of an aircraft engine. A resistance value is measured across a magnetic chip detector mounted to a fluid system of the aircraft engine. The resistance value is transmitted to an engine computer of the aircraft engine. In the engine computer, The resistance value is compared to a first threshold and a first warning indicative of a chip in the fluid is issued when the resistance value exceeds the first threshold.Type: GrantFiled: April 30, 2019Date of Patent: July 7, 2020Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Thomas Trevor Ricci, Simon Sai-Ming Lam, James Robert Jarvo