Patents by Inventor James JARVO
James JARVO 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: 20240150010Abstract: A propeller control unit for an aircraft propulsion system including a propeller is provided. The propeller control unit includes an actuator, a pump, a flow regulator, a pressure sensor, and a controller. The actuator is configured to control a pitch of each of the propeller blades. The pump is configured to direct hydraulic fluid to the actuator. The flow regulator is in fluid communication with the pump and configured to control a hydraulic fluid pressure of the hydraulic fluid downstream of the pump. The pressure sensor is disposed downstream of the pump and upstream of the actuator. The pressure sensor is configured to measure the hydraulic fluid pressure and generate a hydraulic fluid pressure signal. The controller includes a processor in communication with a non-transitory memory storing instructions, which instructions when executed by the processor, cause the processor to monitor the hydraulic fluid pressure signal.Type: ApplicationFiled: November 8, 2022Publication date: May 9, 2024Inventors: Jagoda Krzywon, Benoit Lachance, James Jarvo
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Patent number: 11835543Abstract: There is provided a blade angle feedback system for an aircraft-bladed rotor rotatable about a longitudinal axis and having an adjustable blade pitch angle. A feedback device is coupled to rotate with the rotor and to move along the axis with adjustment of the blade pitch angle. The feedback device comprises a body having position marker(s) embedded therein, the body made of a first material having a first magnetic permeability and the position marker(s) comprising a second material having a second magnetic permeability greater than the first. Sensor(s) are positioned adjacent the feedback device and configured for producing, as the feedback device rotates about the axis, sensor signal(s) in response to detecting passage of the position marker(s). A control unit is communicatively coupled to the sensor(s) and configured to generate a feedback signal indicative of the blade pitch angle in response to the sensor signal(s) received from the sensor(s).Type: GrantFiled: May 19, 2022Date of Patent: December 5, 2023Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Dana Tomescu, James Jarvo
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Publication number: 20230304449Abstract: Systems and methods for configuring operation of an engine are described herein. A computer-readable label associate with the engine is read by a mobile device to obtain label information having at least one trim value for the engine encoded therein. The at least one trim value is extracted from the label information on the mobile device. The at least one trim value is wirelessly transmitted from the mobile device to a data transmission unit of the engine. The data transmission unit is configured for instructing an electronic engine controller to trim the engine with the at least one trim value during operation of the engine.Type: ApplicationFiled: May 15, 2023Publication date: September 28, 2023Inventors: Bjorn STICKLING, Jonathan MILLER, James JARVO
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Patent number: 11713723Abstract: Systems and methods for operating an engine are described herein. The engine is operated at low power by supplying fuel to a combustor through a first set of fuel nozzles of at least one first manifold and without supplying fuel to the combustor through a second set of fuel nozzles of at least one second manifold. An amount of fuel to at least in part fill the at least one second manifold to impede fuel coking of the second set of fuel nozzles is determined. The amount of fuel is periodically supplied to the at least one second manifold.Type: GrantFiled: May 29, 2019Date of Patent: August 1, 2023Assignee: PRATT & WHITNEY CANADA CORP.Inventors: James Jarvo, Patrick Manoukian, Philippe Beauchesne-Martel
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Patent number: 11686257Abstract: Systems and methods for configuring operation of an engine are described herein. A computer-readable label associate with the engine is read by a mobile device to obtain label information having at least one trim value for the engine encoded therein. The at least one trim value is extracted from the label information on the mobile device. The at least one trim value is wirelessly transmitted from the mobile device to a data transmission unit of the engine. The data transmission unit is configured for instructing an electronic engine controller to trim the engine with the at least one trim value during operation of the engine.Type: GrantFiled: October 2, 2019Date of Patent: June 27, 2023Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Bjorn Stickling, Jonathan Miller, James Jarvo
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Patent number: 11505307Abstract: A phonic wheel having a body and a tooth is disclosed. An embodiment of the phonic wheel includes a body that is configured to rotate about a rotation axis. The tooth is attached to the body. The tooth has a first axial end relative to the rotation axis, a second axial end opposite the first axial end, and a mid portion extending between the first and second axial ends. The mid portion has a substantially axially uniform height from the body. The first axial end has a greater height from the body than the height of the mid portion.Type: GrantFiled: October 21, 2019Date of Patent: November 22, 2022Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Ella Yakobov, James Jarvo
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Publication number: 20220276279Abstract: There is provided a blade angle feedback system for an aircraft-bladed rotor rotatable about a longitudinal axis and having an adjustable blade pitch angle. A feedback device is coupled to rotate with the rotor and to move along the axis with adjustment of the blade pitch angle. The feedback device comprises a body having position marker(s) embedded therein, the body made of a first material having a first magnetic permeability and the position marker(s) comprising a second material having a second magnetic permeability greater than the first. Sensor(s) are positioned adjacent the feedback device and configured for producing, as the feedback device rotates about the axis, sensor signal(s) in response to detecting passage of the position marker(s). A control unit is communicatively coupled to the sensor(s) and configured to generate a feedback signal indicative of the blade pitch angle in response to the sensor signal(s) received from the sensor(s).Type: ApplicationFiled: May 19, 2022Publication date: September 1, 2022Inventors: Dana TOMESCU, James JARVO
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Patent number: 11420772Abstract: A sensor signal comprising a first signal pulse having a first voltage amplitude and a second signal pulse having a second voltage amplitude greater than or substantially equal to the first voltage amplitude is obtained from a sensor positioned adjacent a feedback device coupled to rotate with an aircraft-bladed rotor about a longitudinal axis and to move along the axis with adjustment of the rotor's blade pitch angle. The feedback device comprises a reference feature configured to generate the second signal pulse and varying detectable feature(s) configured to generate the first signal pulse and to cause a change in the first voltage amplitude as a function of an axial position of the feedback device along the axis. A voltage ratio is determined based on the first voltage amplitude and the second voltage amplitude, and the axial position of the feedback device is determined from the voltage ratio.Type: GrantFiled: December 17, 2019Date of Patent: August 23, 2022Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Dana Tomescu, James Jarvo, Ella Yakobov
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Patent number: 11391218Abstract: Methods and systems for setting a target power of an aircraft engine are described herein. A power lever position is obtained. At least one flight condition indicative of a phase of flight of the aircraft is obtained. A maximum rated power of the engine is determined for one or more engine rating based on the phase of flight. The target power of the engine is set based on the power lever position and the maximum rated power of the one or more engine ratings.Type: GrantFiled: March 22, 2019Date of Patent: July 19, 2022Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Jean-Philippe Royer, Eric Martel, Daniel D'Anjou, James Jarvo
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Patent number: 11365691Abstract: There is provided a blade angle feedback system for an aircraft-bladed rotor rotatable about a longitudinal axis and having an adjustable blade pitch angle. A feedback device is coupled to rotate with the rotor and to move along the axis with adjustment of the blade pitch angle. The feedback device comprises a body having position marker(s) embedded therein, the body made of a first material having a first magnetic permeability and the position marker(s) comprising a second material having a second magnetic permeability greater than the first. Sensor(s) are positioned adjacent the feedback device and configured for producing, as the feedback device rotates about the axis, sensor signal(s) in response to detecting passage of the position marker(s). A control unit is communicatively coupled to the sensor(s) and configured to generate a feedback signal indicative of the blade pitch angle in response to the sensor signal(s) received from the sensor(s).Type: GrantFiled: October 11, 2019Date of Patent: June 21, 2022Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Dana Tomescu, James Jarvo
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Publication number: 20210179295Abstract: A sensor signal comprising a first signal pulse having a first voltage amplitude and a second signal pulse having a second voltage amplitude greater than or substantially equal to the first voltage amplitude is obtained from a sensor positioned adjacent a feedback device coupled to rotate with an aircraft-bladed rotor about a longitudinal axis and to move along the axis with adjustment of the rotor's blade pitch angle. The feedback device comprises a reference feature configured to generate the second signal pulse and varying detectable feature(s) configured to generate the first signal pulse and to cause a change in the first voltage amplitude as a function of an axial position of the feedback device along the axis. A voltage ratio is determined based on the first voltage amplitude and the second voltage amplitude, and the axial position of the feedback device is determined from the voltage ratio.Type: ApplicationFiled: December 17, 2019Publication date: June 17, 2021Inventors: Dana TOMESCU, James Jarvo, Ella Yakobov
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Patent number: 11012146Abstract: A communication system and a method for transmitting data from an aircraft, the aircraft comprising at least one engine. A data collection and transmission unit is configured to collect and transmit data received from one or more locations in the aircraft, the data collection and transmission unit comprising at least one radio transmitter. At least one engine controller for the at least one engine is communicatively coupled to the data collection and transmission unit and configured to transmit, while the aircraft is airborne, engine data to the data collection and transmission unit, and, responsive to determining that the aircraft is on ground, cause the at least one radio transmitter to activate for transmitting the engine data from the data collection and transmission unit to at least one ground equipment.Type: GrantFiled: February 6, 2020Date of Patent: May 18, 2021Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Frederic Fortin, James Jarvo, Jonathan Miller
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Publication number: 20210114716Abstract: A phonic wheel having a body and a tooth is disclosed. An embodiment of the phonic wheel includes a body that is configured to rotate about a rotation axis. The tooth is attached to the body. The tooth has a first axial end relative to the rotation axis, a second axial end opposite the first axial end, and a mid portion extending between the first and second axial ends. The mid portion has a substantially axially uniform height from the body. The first axial end has a greater height from the body than the height of the mid portion.Type: ApplicationFiled: October 21, 2019Publication date: April 22, 2021Inventors: Ella YAKOBOV, James JARVO
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Publication number: 20210104104Abstract: A system and method for transmitting data from an aircraft, the aircraft comprising at least one engine. Aircraft input indicative of a request to enable a maintenance mode of operation of at least one engine controller for the at least one engine is received at the at least one engine controller.Type: ApplicationFiled: December 3, 2019Publication date: April 8, 2021Inventors: Frederic FORTIN, James JARVO, Jonathan MILLER
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Publication number: 20210102502Abstract: Systems and methods for configuring operation of an engine are described herein. A computer-readable label associate with the engine is read by a mobile device to obtain label information having at least one trim value for the engine encoded therein. The at least one trim value is extracted from the label information on the mobile device. The at least one trim value is wirelessly transmitted from the mobile device to a data transmission unit of the engine. The data transmission unit is configured for instructing an electronic engine controller to trim the engine with the at least one trim value during operation of the engine.Type: ApplicationFiled: October 2, 2019Publication date: April 8, 2021Inventors: Bjorn STICKLING, Jonathan MILLER, James JARVO
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Publication number: 20210070424Abstract: There is provided a blade angle feedback system for an aircraft-bladed rotor rotatable about a longitudinal axis and having an adjustable blade pitch angle. A feedback device is coupled to rotate with the rotor and to move along the axis with adjustment of the blade pitch angle. The feedback device comprises a body having position marker(s) embedded therein, the body made of a first material having a first magnetic permeability and the position marker(s) comprising a second material having a second magnetic permeability greater than the first. Sensor(s) are positioned adjacent the feedback device and configured for producing, as the feedback device rotates about the axis, sensor signal(s) in response to detecting passage of the position marker(s). A control unit is communicatively coupled to the sensor(s) and configured to generate a feedback signal indicative of the blade pitch angle in response to the sensor signal(s) received from the sensor(s).Type: ApplicationFiled: October 11, 2019Publication date: March 11, 2021Inventors: Dana TOMESCU, James JARVO
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Publication number: 20200362769Abstract: Systems and methods for operating an engine are described herein. The engine is operated at low power by supplying fuel to a combustor through a first set of fuel nozzles of at least one first manifold and without supplying fuel to the combustor through a second set of fuel nozzles of at least one second manifold. An amount of fuel to at least in part fill the at least one second manifold to impede fuel coking of the second set of fuel nozzles is determined. The amount of fuel is periodically supplied to the at least one second manifold.Type: ApplicationFiled: May 29, 2019Publication date: November 19, 2020Inventors: James JARVO, Patrick MANOUKIAN, Philippe BEAUCHESNE-MARTEL
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Publication number: 20200300176Abstract: Methods and systems for setting a target power of an aircraft engine are described herein. A power lever position is obtained. At least one flight condition indicative of a phase of flight of the aircraft is obtained. A maximum rated power of the engine is determined for one or more engine rating based on the phase of flight. The target power of the engine is set based on the power lever position and the maximum rated power of the one or more engine ratings.Type: ApplicationFiled: March 22, 2019Publication date: September 24, 2020Inventors: Jean-Philippe ROYER, Eric MARTEL, Daniel D'ANJOU, James JARVO
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Publication number: 20200259557Abstract: A communication system and a method for transmitting data from an aircraft, the aircraft comprising at least one engine. A data collection and transmission unit is configured to collect and transmit data received from one or more locations in the aircraft, the data collection and transmission unit comprising at least one radio transmitter. At least one engine controller for the at least one engine is communicatively coupled to the data collection and transmission unit and configured to transmit, while the aircraft is airborne, engine data to the data collection and transmission unit, and, responsive to determining that the aircraft is on ground, cause the at least one radio transmitter to activate for transmitting the engine data from the data collection and transmission unit to at least one ground equipment.Type: ApplicationFiled: February 6, 2020Publication date: August 13, 2020Inventors: Frederic FORTIN, James JARVO, Jonathan MILLER
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Patent number: 10392099Abstract: A system and method for controlling an aircraft propeller are provided. In anticipation of a condition in which a parameter related to an angle of a plurality of blades of the propeller reaches a value beyond a predetermined threshold, a first control signal is output comprising instructions to actuate a feather valve operatively coupled to an actuator configured to adjust the angle in response to hydraulic pressure, thereby causing the feather valve to provide the hydraulic pressure to the actuator and the angle to be adjusted for bringing the parameter towards the threshold. When the parameter reaches the predetermined threshold, a second control signal is output comprising instructions to hold the feather valve at a position in which the hydraulic pressure is withheld from the actuator, thereby causing the angle to remain unchanged.Type: GrantFiled: May 18, 2017Date of Patent: August 27, 2019Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Reza Pedrami, James Jarvo