Patents by Inventor Leonid Guerchkovitch
Leonid Guerchkovitch 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: 11958622Abstract: A method includes controlling an electric motor of a hybrid-electric powerplant for an aircraft using an EPC (electric powertrain controller) and controlling a heat engine of the hybrid-electric powerplant using an ECU (engine control unit). The method includes performing at least one of the following to protect the hybrid-electric powerplant: using the ECU to power down the electric motor, and/or using the EPC to power down the heat engine.Type: GrantFiled: May 15, 2020Date of Patent: April 16, 2024Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Richard A. Poisson, Paul C. Imel, Leonid Guerchkovitch
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Publication number: 20240116645Abstract: A hybrid electric propulsion (HEP) system can include a heat engine torque sensor connected between a heat engine and a combining gear box to sense a heat motor input torque input to the combining gear box, an electric motor torque sensor connected between an electric motor and the combining gear box to sense an electric motor input torque input to the combining gear box, and a combining gear box torque sensor connected to an output of the combining gearbox. The system can include a HEP controller operatively connected to each of the heat engine torque sensor, the electric motor torque sensor, and the combining gear box torque sensor to receive one or more torque signals therefrom. The controller can be configured to output one or more output signals as a function of the signals from each of the heat engine torque sensor, the electric motor torque sensor, and the combining gear box torque sensor.Type: ApplicationFiled: December 18, 2023Publication date: April 11, 2024Inventors: Michael MARK, Paul C. IMEL, Leonid GUERCHKOVITCH
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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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Publication number: 20240051674Abstract: A method of controlling a multi-engine aircraft includes receiving input for commanded thrust and modifying the commanded thrust using a model of an incumbent powerplant to generate a modified commanded thrust for matching aircraft performance with a new powerplant to the aircraft performance with the incumbent powerplant. The method includes applying the modified commanded thrust to the new powerplant.Type: ApplicationFiled: October 23, 2023Publication date: February 15, 2024Inventors: Leonid GUERCHKOVITCH, Aaron J. KAUFMAN, Boris KARPMAN, Manuj DHINGRA
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Patent number: 11884412Abstract: A hybrid electric propulsion (HEP) system can include a heat engine torque sensor connected between a heat engine and a combining gear box to sense a heat motor input torque input to the combining gear box, an electric motor torque sensor connected between an electric motor and the combining gear box to sense an electric motor input torque input to the combining gear box, and a combining gear box torque sensor connected to an output of the combining gearbox. The system can include a HEP controller operatively connected to each of the heat engine torque sensor, the electric motor torque sensor, and the combining gear box torque sensor to receive one or more torque signals therefrom. The controller can be configured to output one or more output signals as a function of the signals from each of the heat engine torque sensor, the electric motor torque sensor, and the combining gear box torque sensor.Type: GrantFiled: August 24, 2020Date of Patent: January 30, 2024Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Michael Mark, Paul C. Imel, Leonid Guerchkovitch
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Publication number: 20240002065Abstract: A method of controlling a hybrid-electric aircraft powerplant includes running a first control loop for command of a thermal engine based on error between total response commanded for a hybrid-electric powerplant and total response from the hybrid-electric powerplant. A second control loop runs in parallel with the first control loop for commanding the thermal engine based on error between maximum thermal engine output and total response commanded. A third control loop runs in parallel with the first and second control loops for commanding engine/propeller speed, wherein the third control loop outputs a speed control enable or disable status. A fourth control loop runs in parallel with the first, second, and third control loops for commanding the electric motor with non-zero demand when the second control loop is above control to add response from the electric motor to response from the thermal engine to achieve the response commanded.Type: ApplicationFiled: September 19, 2023Publication date: January 4, 2024Inventors: Leonid GUERCHKOVITCH, Manuj DHINGRA, Boris KARPMAN, Aaron J. KAUFMAN
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Patent number: 11827372Abstract: A method of controlling a multi-engine aircraft includes receiving input for commanded thrust and modifying the commanded thrust using a model of an incumbent powerplant to generate a modified commanded thrust for matching aircraft performance with a new powerplant to the aircraft performance with the incumbent powerplant. The method includes applying the modified commanded thrust to the new powerplant.Type: GrantFiled: May 15, 2020Date of Patent: November 28, 2023Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Leonid Guerchkovitch, Aaron J. Kaufman, Boris Karpman, Manuj Dhingra
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Patent number: 11794916Abstract: A control system for a hybrid electric powerplant of an aircraft can include a throttle controller configured to receive one or more power settings and to output a heat engine setting and an electric motor setting, a heat engine controller operatively connected to the throttle controller. The heat engine controller can be configured to receive the heat engine setting and to control a heat engine system as a function of the heat engine setting to control torque output by a heat engine. The system can include a heat engine protection module that is part of or connected to the heat engine controller and configured to provide one or more protection commands to directly control one or more heat engine protection systems. The system can include an electric motor controller operatively connected to the throttle controller.Type: GrantFiled: May 15, 2020Date of Patent: October 24, 2023Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Michael Mark, Paul C. Imel, Leonid Guerchkovitch
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Patent number: 11794917Abstract: A method of controlling a hybrid-electric aircraft powerplant includes running a first control loop for command of a thermal engine based on error between total response commanded for a hybrid-electric powerplant and total response from the hybrid-electric powerplant. A second control loop runs in parallel with the first control loop for commanding the thermal engine based on error between maximum thermal engine output and total response commanded. A third control loop runs in parallel with the first and second control loops for commanding engine/propeller speed, wherein the third control loop outputs a speed control enable or disable status. A fourth control loop runs in parallel with the first, second, and third control loops for commanding the electric motor with non-zero demand when the second control loop is above control to add response from the electric motor to response from the thermal engine to achieve the response commanded.Type: GrantFiled: May 15, 2020Date of Patent: October 24, 2023Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Leonid Guerchkovitch, Manuj Dhingra, Boris Karpman, Aaron J. Kaufman
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Patent number: 11760495Abstract: A control system for a hybrid electric powerplant of an aircraft can include a heat engine controller configured to receive one or more power settings and to determine a heat engine setting and an electric motor setting. The heat engine controller can be configured to use the heat engine setting to control a heat engine system as a function of the heat engine setting to control torque output by a heat engine. The heat engine controller can be configured to output the electric motor setting. The system can include an electric motor controller can be operatively connected to the heat engine controller. The electric motor controller configured to receive the electric motor engine setting from the heat engine controller and to control an electric motor system as a function of the electric motor setting to control torque output by an electric motor.Type: GrantFiled: May 15, 2020Date of Patent: September 19, 2023Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Michael Mark, Paul C. Imel, Leonid Guerchkovitch
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Patent number: 11685540Abstract: Methods and systems for method for managing a hybrid-electric powerplant (HEP) comprising a thermal engine and an electric motor are described. The method comprises transmitting a thermal power command to the thermal engine to generate a thermal power output; transmitting an electric power command to the electric motor to generate an electric power output; comparing the thermal power output to the thermal power command and the electric power output to the electric power command; detecting a fault when the thermal power output deviates from the thermal power command or when the electric power output deviates from the electric power command; and accommodating the fault by modulating the thermal power command in response to a deviation in the electric power output and modulating the electric power command in response to a deviation in the thermal power output.Type: GrantFiled: January 22, 2021Date of Patent: June 27, 2023Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Michael R. Mark, Leonid Guerchkovitch
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Patent number: 11649038Abstract: A system includes a thermal engine operatively connected to drive a propeller. An electric motor is operatively connected to the thermal engine to drive the propeller together with the thermal engine. An external input system is configured to accept input and output a thrust command. A protection function module is configured to enforce limits on the thermal engine, electric motor, and propeller. A low select module is operatively connected to receive input from the external input system and form the protection function module and to output the lower of input from the protection function module and external input system to the thermal engine, the electric motor, and the propeller.Type: GrantFiled: July 10, 2020Date of Patent: May 16, 2023Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Michael Mark, Leonid Guerchkovitch
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Publication number: 20220297846Abstract: A hybrid electric system for a rotorcraft can include a first thermal engine, a second thermal engine, and an electrical machine. The first thermal engine can be sized to produce a maximum first thermal engine power that is below a one-or-more-engine-inoperative (OEI) requirement power and the second thermal engine can be sized to produce a maximum second thermal engine power that is below the OEI requirement power. The electrical machine can be sized to provide at least a remaining power needed to reach the OEI requirement power in an OEI state.Type: ApplicationFiled: March 19, 2021Publication date: September 22, 2022Applicant: Pratt & Whitney Canada Corp.Inventors: Michael R. Mark, Leonid Guerchkovitch
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Publication number: 20220234748Abstract: Methods and systems for method for managing a hybrid-electric powerplant (HEP) comprising a thermal engine and an electric motor are described. The method comprises transmitting a thermal power command to the thermal engine to generate a thermal power output; transmitting an electric power command to the electric motor to generate an electric power output; comparing the thermal power output to the thermal power command and the electric power output to the electric power command; detecting a fault when the thermal power output deviates from the thermal power command or when the electric power output deviates from the electric power command; and accommodating the fault by modulating the thermal power command in response to a deviation in the electric power output and modulating the electric power command in response to a deviation in the thermal power output.Type: ApplicationFiled: January 22, 2021Publication date: July 28, 2022Inventors: Michael R. MARK, Leonid GUERCHKOVITCH
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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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Publication number: 20220009615Abstract: A system includes a thermal engine operatively connected to drive a propeller. An electric motor is operatively connected to the thermal engine to drive the propeller together with the thermal engine. An external input system is configured to accept input and output a thrust command. A protection function module is configured to enforce limits on the thermal engine, electric motor, and propeller. A low select module is operatively connected to receive input from the external input system and form the protection function module and to output the lower of input from the protection function module and external input system to the thermal engine, the electric motor, and the propeller.Type: ApplicationFiled: July 10, 2020Publication date: January 13, 2022Applicant: Pratt & Whitney Canada Corp.Inventors: Michael Mark, Leonid Guerchkovitch
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Publication number: 20210354842Abstract: A method of controlling a multi-engine aircraft includes receiving input for commanded thrust and modifying the commanded thrust using a model of an incumbent powerplant to generate a modified commanded thrust for matching aircraft performance with a new powerplant to the aircraft performance with the incumbent powerplant. The method includes applying the modified commanded thrust to the new powerplant.Type: ApplicationFiled: May 15, 2020Publication date: November 18, 2021Applicant: Pratt & Whitney Canada Corp.Inventors: Leonid Guerchkovitch, Aaron J. Kaufman, Boris Karpman, Manuj Dhingra
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Publication number: 20210354837Abstract: A control system for a hybrid electric powerplant of an aircraft can include a heat engine controller configured to receive one or more power settings and to determine a heat engine setting and an electric motor setting. The heat engine controller can be configured to use the heat engine setting to control a heat engine system as a function of the heat engine setting to control torque output by a heat engine. The heat engine controller can be configured to output the electric motor setting. The system can include an electric motor controller can be operatively connected to the heat engine controller. The electric motor controller configured to receive the electric motor engine setting from the heat engine controller and to control an electric motor system as a function of the electric motor setting to control torque output by an electric motor.Type: ApplicationFiled: May 15, 2020Publication date: November 18, 2021Inventors: Michael Mark, Paul C. Imel, Leonid Guerchkovitch
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Publication number: 20210354843Abstract: A method of controlling a hybrid-electric aircraft powerplant includes running a first control loop for command of a thermal engine based on error between total response commanded for a hybrid-electric powerplant and total response from the hybrid-electric powerplant. A second control loop runs in parallel with the first control loop for commanding the thermal engine based on error between maximum thermal engine output and total response commanded. A third control loop runs in parallel with the first and second control loops for commanding engine/propeller speed, wherein the third control loop outputs a speed control enable or disable status. A fourth control loop runs in parallel with the first, second, and third control loops for commanding the electric motor with non-zero demand when the second control loop is above control to add response from the electric motor to response from the thermal engine to achieve the response commanded.Type: ApplicationFiled: May 15, 2020Publication date: November 18, 2021Applicant: Pratt & Whitney Canada Corp.Inventors: Leonid Guerchkovitch, Manuj Dhingra, Boris Karpman, Aaron J. Kaufman
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Publication number: 20210354841Abstract: A method includes controlling an electric motor of a hybrid-electric powerplant for an aircraft using an EPC (electric powertrain controller) and controlling a heat engine of the hybrid-electric powerplant using an ECU (engine control unit). The method includes performing at least one of the following to protect the hybrid-electric powerplant: using the ECU to power down the electric motor, and/or using the EPC to power down the heat engine.Type: ApplicationFiled: May 15, 2020Publication date: November 18, 2021Applicant: Pratt & Whitney Canada Corp.Inventors: Richard A. Poisson, Paul C. Imel, Leonid Guerchkovitch