Patents by Inventor Richard Freer
Richard Freer 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: 11936007Abstract: A battery system includes a plurality of battery cells abutting one another to form a battery cell stack. An optical communication link is connected to each of the plurality of battery cells. A battery management system (BMS) connected to the optical communication link configured and adapted to receive information from the optical communication link. A method of controlling heat transfer in a battery system includes monitoring at least one characteristic of at least one battery cell of a plurality of battery cells with at least one sensor, and sending information from the at least one sensor to a battery management system (BMS) with an optical communication link. The optical communication link is connected to each of the plurality of battery cells. The method includes selectively varying a fluid circulation rate in the battery system with the BMS depending on the at least one characteristic.Type: GrantFiled: September 24, 2021Date of Patent: March 19, 2024Assignee: Hamilton Sundstrand CorporationInventors: Richard Freer, Chase Whitman
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Patent number: 11909283Abstract: An electric machine system disclosed herein comprises first and second electric machines configured to drive a load. The first electric machine has a plurality of first rotors. The second electric machine has a plurality of second rotors. At least one of the second rotors is indexed relative to a respective one of the first rotors to, in use, provide a torque phase offset between the first and second electric machines. A shaft is coupled to the load and connects the respective one of the first rotors with the at least one of the second rotors. The respective one of the first rotors is coaxial with and axially spaced apart from the at least one of the second rotors.Type: GrantFiled: April 15, 2021Date of Patent: February 20, 2024Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Eric Latulipe, Richard Freer
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Patent number: 11894742Abstract: An electric machine system described herein comprises a first and second electric machines configured to drive a load. The first electric machine has a plurality of first rotors driven using electric power having a first phase. The second electric machine has a plurality of second rotors driven using electric power having a second phase. The second phase differs from the first phase. Each of one or more shafts connects a first rotor with a second rotor. The first rotor is coaxial with and axially spaced apart from the second rotor.Type: GrantFiled: April 8, 2021Date of Patent: February 6, 2024Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Eric Latulipe, Richard Freer
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Publication number: 20240017842Abstract: An aircraft system is provided that includes a first propulsor rotor, a first transmission, a second propulsor rotor, a second transmission and an intermittent combustion engine. The first propulsor rotor is rotatable about a first propulsor axis. The first transmission is coupled to the first propulsor rotor. The second propulsor rotor is rotatable about a second propulsor axis. The second transmission is coupled to the second propulsor rotor. The intermittent combustion engine is configured to drive rotation of the first propulsor rotor through the first transmission. The intermittent combustion engine is configured to drive rotation of the second propulsor rotor through the second transmission.Type: ApplicationFiled: July 15, 2022Publication date: January 18, 2024Inventor: Richard Freer
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Publication number: 20240017841Abstract: An aircraft system is provided that includes an aircraft fuselage, a first propulsor, a first drivetrain, a second propulsor, a second drivetrain and an intermittent combustion engine. The first propulsor is outside of the aircraft fuselage. The first propulsor includes a first propulsor rotor and a first vane array. The first drivetrain is coupled to the first propulsor rotor. The second propulsor is outside of the aircraft fuselage. The second propulsor includes a second propulsor rotor and a second vane array. The second drivetrain is coupled to the second propulsor rotor. The intermittent combustion engine is within the aircraft fuselage. The intermittent combustion engine is configured to drive rotation of the first propulsor rotor, independent of the second propulsor rotor, through the first drivetrain. The intermittent combustion engine is configured to drive rotation of the second propulsor rotor, independent of the first propulsor rotor, through the second drivetrain.Type: ApplicationFiled: July 15, 2022Publication date: January 18, 2024Inventor: Richard Freer
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Publication number: 20240017847Abstract: An aircraft system is provided that includes a first propulsor, a second propulsor, a drivetrain and an intermittent combustion engine. The first propulsor includes a first propulsor rotor and a first vane array. The second propulsor includes a second propulsor rotor and a second vane array. The drivetrain includes a drive structure and a transmission. An output of the transmission is coupled to the first propulsor rotor and the second propulsor rotor through the drive structure. The intermittent combustion engine is configured to drive rotation of the first propulsor rotor and the second propulsor rotor through the drivetrain.Type: ApplicationFiled: July 15, 2022Publication date: January 18, 2024Inventor: Richard Freer
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Patent number: 11863032Abstract: An electric machine system described herein comprises a first electric machine rotor, a first gear and a second gear. The first gear is connected to the first electric machine rotor and to a first input/output shaft. The second gear is connected to the first electric machine rotor and to a second input/output shaft. The first electric machine rotor is disposed between the first gear and the second gear.Type: GrantFiled: October 29, 2021Date of Patent: January 2, 2024Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Eric Latulipe, Richard Freer
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Publication number: 20230415905Abstract: An aircraft propulsion system for an aircraft having a nacelle that includes a pylon structure is provided. The system includes compressor and turbine sections, an IC engine, a fan, and an IC engine cooling system. The compressor section is powered by a first electric motor. The turbine section is configured to power a first electric generator configured to produce electrical power. The first fan is rotationally driven by a second electric motor. The fan has a hub and a plurality of fan blades extending radially outward from the hub. The hub is disposed in the pylon interior region and the fan blades are configured to extend outside of the pylon structure. The fan is positioned downstream of the compressor section. The IC engine cooling system has a heat exchanger and a pump configured to provide coolant communication between the IC engine and the heat exchanger.Type: ApplicationFiled: September 13, 2023Publication date: December 28, 2023Inventor: Richard Freer
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Publication number: 20230406519Abstract: A propulsion system for an aircraft having a nacelle and a fuselage is provided. The nacelle has a gas flow path and a nacelle interior region. The system includes a compressor section, an intermittent IC engine, a turbine section, a fan, and an IC cooling system. A first electric motor powers the compressor section. The compressor section produces a flow of elevated pressure compressor air. The intermittent IC engine selectively intakes the compressor air flow and produces an exhaust gas flow. The turbine section powered by exhaust gas in turn powers a first electric generator. The fan is driven by a second electric motor. The IC engine cooling system has a heat exchanger disposed within the gas flow path, coolant, coolant piping, and a pump. The heat exchanger is disposed in the nacelle.Type: ApplicationFiled: June 21, 2022Publication date: December 21, 2023Inventor: Richard Freer
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Patent number: 11827370Abstract: A propulsion system for an aircraft having a nacelle and a fuselage is provided. The nacelle has a gas flow path and a nacelle interior region. The system includes a compressor section, an intermittent IC engine, a turbine section, a fan, and an IC cooling system. A first electric motor powers the compressor section. The compressor section produces a flow of elevated pressure compressor air. The intermittent IC engine selectively intakes the compressor air flow and produces an exhaust gas flow. The turbine section powered by exhaust gas in turn powers a first electric generator. The fan is driven by a second electric motor. The IC engine cooling system has a heat exchanger disposed within the gas flow path, coolant, coolant piping, and a pump. The heat exchanger is disposed in the nacelle.Type: GrantFiled: June 21, 2022Date of Patent: November 28, 2023Assignee: Pratt & Whitney Canada Corp.Inventor: Richard Freer
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Patent number: 11757386Abstract: A hybrid electric aircraft propulsion system and method of operation are described. The system comprises a thermal engine, a generator coupled to the thermal engine, a first electric propulsor operatively connected to the generator to receive alternating current (AC) electric power therefrom, a second electric propulsor, a generator inverter operatively connected to the generator to convert AC electric power to direct current (DC) electric power, and a first motor inverter operatively connected to the generator inverter and selectively connected to one of the first electric propulsor and the second electric propulsor and configured to receive the DC electric power and provide the first electric propulsor and the second electric propulsor with AC electric power, respectively.Type: GrantFiled: February 17, 2022Date of Patent: September 12, 2023Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Eric Latulipe, Richard Freer
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Patent number: 11739693Abstract: There are described methods and systems for operating a glow plug. The method comprises monitoring a glow plug current; applying a nominal voltage VN to the glow plug when the glow plug current is between an upper threshold I1 and a lower threshold I2<I1; applying a voltage VH>VN to the glow plug when the glow plug current exceeds the upper threshold I1; and applying substantially no voltage to the glow plug when the glow plug current falls below the lower threshold I2.Type: GrantFiled: November 18, 2020Date of Patent: August 29, 2023Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Mehmet Celal Tanju, Richard Freer
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Publication number: 20230257128Abstract: A method of operating a hybrid-electric propulsion system for an aircraft and a hybrid-electric propulsion system is provided. The method includes: a) providing at least one thermal engine sized to provide sufficient thrust to the aircraft for at least one flight mission independent of a second non-thermal engine source of thrust for the at least one flight mission; b) providing at least one electric motor powered by a non-hydrocarbon fuel burning electrical energy source, the at least one electric motor configured to provide thrust to the aircraft for the at least one flight mission; and c) selectively providing thrust during one or more segments of the at least one flight mission using the electric motor.Type: ApplicationFiled: February 11, 2022Publication date: August 17, 2023Inventors: Richard Freer, Dominik Quillet, David Rancourt
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Patent number: 11719166Abstract: An aircraft system is provided that includes a first propulsor rotor, a second propulsor rotor, a drivetrain and an intermittent combustion engine. The first propulsor rotor is rotatable about a first propulsor axis. The second propulsor rotor is rotatable about a second propulsor axis. The drivetrain includes a drive structure and a transmission. The drive structure is rotatable about a drive axis that is angularly offset from the first propulsor axis and the second propulsor axis. An output of the transmission is coupled to the first propulsor rotor and the second propulsor rotor through the drive structure. The intermittent combustion engine is configured to drive rotation of the first propulsor rotor and the second propulsor rotor through the drivetrain.Type: GrantFiled: July 15, 2022Date of Patent: August 8, 2023Assignee: Pratt & Whitney Canada Corp.Inventor: Richard Freer
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Patent number: 11692489Abstract: A method of servicing a gas turbine engine having an igniter socket, the method comprising: inserting a glow plug into the igniter socket of the gas turbine engine until a rod end of a glow plug heater rod of the glow plug is exposed to a combustion chamber of the gas turbine engine; and blocking a gap between the glow plug heater rod and an aperture defined in a combustor liner of the gas turbine engine to block fluid communication between the combustion chamber and an environment outside the combustion chamber via the aperture.Type: GrantFiled: January 26, 2022Date of Patent: July 4, 2023Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Richard Freer, Kian McCaldon, Tin-Cheung John Hu, Michel Bousquet, André Fortin
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Publication number: 20230155209Abstract: A battery module includes at least one cell having a positive terminal, a negative terminal, and a voltage and a current rating. A first electrically conductive heat pipe is thermally and electrically connected to the positive terminal. A second electrically conductive heat pipe is thermally and electrically connected to the negative terminal. The first and second heat pipes have the voltage and the current rating.Type: ApplicationFiled: November 18, 2021Publication date: May 18, 2023Inventor: Richard FREER
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Patent number: 11649065Abstract: In accordance with at least one aspect of this disclosure, there is provided a system for aircraft power. The system includes a DC/DC converter having a DC input and a DC output and a switching circuit connecting the DC input to the DC output operable to vary voltage at the DC output. A control module is operatively connected to the switching circuit for variable control of the DC output. The control module includes machine readable instructions to cause the control module to receive input indicative of altitude and control the switching circuit to vary voltage of the DC output as a function of environmental conditions such as altitude and humidity. In embodiments the altitude sensor is operatively connected to the controller.Type: GrantFiled: August 13, 2021Date of Patent: May 16, 2023Assignee: PRATT & WHITNEY CANADA CORP.Inventor: Richard Freer
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Patent number: 11614034Abstract: A gas turbine engine has: a casing; a combustor liner delimiting a combustion chamber; a fuel nozzle in fluid communication with the combustion chamber; and an igniter having a base, a glow plug heater rod extending from the base along an axis and terminating in a rod end, and a sleeve extending around the glow plug heater rod, the sleeve radially spaced apart from the glow plug heater rod by an annular gap, the sleeve defines fins circumferentially distributed around the axis, each two circumferentially adjacent fins of the fins spaced apart from one another by a spacing communicating with the annular gap, the fins extending in a direction having an axial component from roots to tips, the roots axially closer to the base than the tips, the rod end extending axially beyond the tips of the fins such that the rod end is located outside the annular gap.Type: GrantFiled: August 5, 2022Date of Patent: March 28, 2023Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Richard Freer, Kian McCaldon, Tin-Cheung John Hu, Michel Bousquet, André Fortin
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Publication number: 20230058484Abstract: In accordance with at least one aspect of the present disclosure, there is provided a method for controlling power in an aircraft. The method includes, monitoring an electric energy storage module electrically connected to an electrical bus for an exceedance of a first current limit and monitoring a generator module connected to the electrical bus for an exceedance of a second current limit. If the current limit of either of the electric energy storage module or the generator module is exceeded by a predetermined exceedance amount, the method includes reducing a power consumption for an electric machine by a predetermined bias until the exceedance of the electrical energy storage and the exceedance of the generator module are both less than or equal to zero.Type: ApplicationFiled: August 17, 2021Publication date: February 23, 2023Applicant: Pratt & Whitney Canada Corp.Inventor: Richard Freer
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Publication number: 20230047326Abstract: In accordance with at least one aspect of this disclosure, there is provided a method of accelerating a gas turbine engine. The method includes adding torque to a core of the gas turbine engine to accelerate rotation of the core by controlling fuel flow to a plurality of fuel injectors of the gas turbine engine. The method also includes adding torque to the core by powering an electric machine that is operatively connected to the core. In embodiments, controlling fuel flow to the plurality of fuel injectors is based on feedback from the electric machine.Type: ApplicationFiled: August 13, 2021Publication date: February 16, 2023Applicant: Pratt & Whitney Canada Corp.Inventor: Richard Freer