Patents by Inventor Thomas Dewey
Thomas Dewey 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: 20210403168Abstract: A hybrid propulsion system for a tiltrotor aircraft comprises one or more engines that provide thrust whenever the tiltrotor aircraft is in a first forward flight mode, one or more electrical or hydraulic power sources, and two or more pylon assemblies. Each pylon assembly houses one or more electric or hydraulic motors connected to the one or more electrical or hydraulic power sources and a proprotor. All or part of each pylon assembly is rotatable. The proprotors provide lift whenever the tiltrotor aircraft is in a vertical takeoff and landing mode and a hover mode, and provide thrust whenever the tiltrotor aircraft is in a second forward flight mode.Type: ApplicationFiled: June 29, 2020Publication date: December 30, 2021Inventors: Thomas Dewey Parsons, James E. Sobel, Alan Hisashi Steinert, David Henderson Loe
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Patent number: 11174018Abstract: The present invention includes an a plurality of first variable speed motors mounted on a tail boom of the helicopter; one or more fixed pitch blades attached to each of the plurality of first variable speed motors; and wherein a speed of one or more of the plurality of first variable speed motors is varied to provide an anti-torque thrust.Type: GrantFiled: May 28, 2020Date of Patent: November 16, 2021Assignee: TEXTRON INNOVATIONS INC.Inventors: Carlos Fenny, Thomas Dewey Parsons, Erik John Oltheten
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Patent number: 11077957Abstract: An air intake system (AIS) has a plenum and an inlet barrier filter associated with the plenum, through which air can selectively enter the plenum. The AIS also has an inlet duct associated with the plenum, through which air can selectively enter the plenum. The AIS also has a bypass door associated with the inlet duct, the bypass door being configured to selectively change an amount of air allowed to pass through the inlet duct. The AIS also has a filter airflow change device configured to change an amount of airflow allowed through the inlet barrier filter.Type: GrantFiled: January 23, 2018Date of Patent: August 3, 2021Assignee: Textron Innovations Inc.Inventors: Thomas Dewey Parsons, David Haynes, David L. Miller, Bradley Robert Henson
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Publication number: 20210070462Abstract: The present invention achieves technical advantages as a rotorcraft engine inlet configuration to optimize performance in both hover and high-speed flight. A rotorcraft fuselage with a ram air intake and a side air intake allows airflow into the engine inlet plenum. A door can be operably coupled to the fuselage, wherein the door is in an open position when the airspeed is below a first threshold and is in a closed position when the airspeed exceeds a second threshold. Additionally, control logic, compares the rotorcraft airspeed with a stored airspeed to operate an actuator to open and close the door to modulate the airflow into the engine inlet plenum. The present invention realizes the advantages of eliminating the inlet spillage drag due to inlet ram airflow in forward flight and increasing the available engine power by mitigating the loss of inlet air pressure recovery.Type: ApplicationFiled: November 18, 2020Publication date: March 11, 2021Applicant: Textron Innovations Inc.Inventor: Thomas Dewey Parsons
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Patent number: 10906663Abstract: A boundary layer utilization apparatus for intake of air to a high speed aircraft, comprises a first air inlet adjacent an exterior surface of a fuselage of the aircraft and offset from the fuselage enough to integrate a second air inlet in the offset space to ingest and divert the boundary layer air flowing next to the fuselage into the aircraft for a useful purpose such as cooling the engine compartment. The second air inlet is disposed aft of the first air inlet to minimize hot gas re-ingestion.Type: GrantFiled: July 23, 2018Date of Patent: February 2, 2021Assignee: Textron Innovations Inc.Inventors: Thomas Dewey Parsons, Angel David Rosado, Robert Paul Reynolds, David Frank Haynes, William Mathisen Gons
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Patent number: 10889384Abstract: The present invention achieves technical advantages as a rotorcraft engine inlet configuration to optimize performance in both hover and high-speed flight. A rotorcraft fuselage with a ram air intake and a side air intake allows airflow into the engine inlet plenum. A door can be operably coupled to the fuselage, wherein the door is in an open position when the airspeed is below a first threshold and is in a closed position when the airspeed exceeds a second threshold. Additionally, control logic, compares the rotorcraft airspeed with a stored airspeed to operate an actuator to open and close the door to modulate the airflow into the engine inlet plenum. The present invention realizes the advantages of eliminating the inlet spillage drag due to inlet ram airflow in forward flight and increasing the available engine power by mitigating the loss of inlet air pressure recovery.Type: GrantFiled: September 20, 2017Date of Patent: January 12, 2021Assignee: Textron Innovations Inc.Inventor: Thomas Dewey Parsons
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Publication number: 20200392897Abstract: Embodiments are directed to systems and methods for determining an optimal engine inlet area to minimize spillage drag. An algorithm may utilize aircraft parameters, aircraft performance charts, and engine models to determine the engine inlet area as a function of engine air mass flow, airspeed, and air density at current ambient conditions.Type: ApplicationFiled: June 13, 2019Publication date: December 17, 2020Applicant: Bell Helicopter Textron Inc.Inventor: Thomas Dewey Parsons
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Patent number: 10829239Abstract: Embodiments are directed to systems and methods for managing electrical load in an aircraft comprising a generator coupled to an aircraft engine, and a power distribution controller configured to monitor current engine operating parameters and to reduce an electrical load on the generator when the engine operating parameters reach a limit during specified aircraft operating conditions. The system may further comprise a non-essential electrical bus coupled to the generator, wherein the electrical load on the generator is reduced by disconnecting the non-essential bus from the generator. The generator may be coupled to the aircraft engine via an accessory gearbox or a transmission gearbox. The monitored current engine operating parameters comprise one or more of an engine torque, a gas generator RPM, and a temperature. The aircraft operating conditions may comprise one or more of a takeoff, a landing, or an engine failure.Type: GrantFiled: August 9, 2018Date of Patent: November 10, 2020Assignee: Bell Helicopter Textron Inc.Inventor: Thomas Dewey Parsons
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Publication number: 20200317331Abstract: The present invention includes an a plurality of first variable speed motors mounted on a tail boom of the helicopter; one or more fixed pitch blades attached to each of the plurality of first variable speed motors; and wherein a speed of one or more of the plurality of first variable speed motors is varied to provide an anti-torque thrust.Type: ApplicationFiled: May 28, 2020Publication date: October 8, 2020Inventors: Carlos Fenny, Thomas Dewey Parsons, JR., Erik John Oltheten
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Patent number: 10787253Abstract: The present invention includes an anti-torque assembly for a helicopter comprising a plurality of fixed blade pitch motors mounted on one or more pivots on the tail boom of the helicopter, wherein the plurality of fixed blade pitch motors on the one or more pivots are adapted to be oriented substantially in-plane with a tail boom of a helicopter during a first mode of operation that comprises a hover mode and wherein the fixed blade pitch motors are adapted to be oriented substantially off-plane from the tail boom of the helicopter during a second mode of helicopter operation that is different from the first mode.Type: GrantFiled: November 7, 2018Date of Patent: September 29, 2020Assignee: BELL HELICOPTER TEXTRON INC.Inventors: Thomas Dewey Parsons, Carlos Alexander Fenny, Erik John Oltheten
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Publication number: 20200284192Abstract: An aircraft includes a fuselage and an engine housed in the fuselage. A ram-air engine inlet is formed on an exterior of the fuselage. The ram-air engine inlet is defined, at least in part, by a cowling door. The cowling door is moveable between a closed position and an open position. An intake duct fluidly couples the ram-air engine inlet to the engine. A filter is disposed across the intake duct. A bypass duct is formed in the ram-air engine inlet aft of the intake duct. The bypass duct is operable to be selectively opened and closed.Type: ApplicationFiled: March 6, 2019Publication date: September 10, 2020Applicant: Bell Helicopter Textron Inc.Inventors: David HAYNES, Thomas Dewey PARSONS, Shahryar FOTOVATI
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Patent number: 10731553Abstract: The present invention achieves technical advantages as an engine compartment drainage system that allows fluid on an engine deck to exit an engine compartment, while shielding fluid from airflow. A fluid drainage apparatus utilizes a funnel member to direct fluid to an external drain line. A drain shield circumscribes the top end of the funnel member and upwardly extending therefrom and directs airflow away from the funnel member. A plurality of deck holes are disposed in the drain shield, such that fluid on the deck can enter the funnel member and exit the engine compartment. A fluid drainage system, disposes the fluid drainage apparatus in an engine deck to allow fluid on the deck to enter a funnel member of the apparatus and direct it toward the external drain line.Type: GrantFiled: August 10, 2017Date of Patent: August 4, 2020Assignee: Bell Helicopter Textron Inc.Inventors: Thomas Dewey Parsons, Chris James Ludtke, Andrew Jordan Birkenheuer, Eric Christopher Terry
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Publication number: 20200231293Abstract: An exemplary convertible engine includes an engine housing forming a fan duct extending from a fan inlet to an exhaust; a fan positioned in the fan duct proximate the fan inlet; an engine core located in the fan duct aft of the fan, the engine core coupled to the fan by a fan shaft; a drive shaft mechanically coupled to the engine core and extending exterior of the engine housing; and a dedicated core inflow duct coupled to the core and having a core inlet to capture and direct air into the engine core. An inlet barrier filter may be located in the dedicated core inflow duct. The core inlet may be located inside of the fan duct or exterior to the fan duct. A gearbox may be operationally connected to the fan shaft and may be located inside of the fan duct.Type: ApplicationFiled: January 18, 2019Publication date: July 23, 2020Applicant: Bell Helicopter Textron Inc.Inventors: Thomas Dewey PARSONS, Alan Hisashi STEINERT
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Patent number: 10703471Abstract: The present invention includes an a plurality of first variable speed motors arranged in a first matrix pattern and mounted on a tail boom of the helicopter; one or more fixed pitch blades attached to each of the plurality of first variable speed motors; and wherein a speed of one or more of the plurality of first variable speed motors is varied to provide an anti-torque thrust.Type: GrantFiled: March 14, 2017Date of Patent: July 7, 2020Assignee: BELL HELICOPTER TEXTRON INC.Inventors: Carlos Fenny, Thomas Dewey Parsons, Erik John Oltheten
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Patent number: 10644417Abstract: A coaxial cable connector for attachment to an end of a coaxial cable is disclosed. The coaxial cable connector includes a rotatable body segment having a body wall with an outer surface and an inner surface defining a width of the body wall. The body wall has a radial dimension which varies along a perimeter of the rotatable body segment. The inner surface defines a longitudinal opening extending between a forward end of the rotatable body segment and a rearward end of the rotatable body segment. A post positions proximal the forward end of the rotatable body segment. The post has a first end and a second end with a bore extending therebetween. The post is rotationally stationary with respect to the rotatable body segment. A coupling member positions proximal to the first end of the post. The rotatable body segment is rotated to close the coaxial cable connector.Type: GrantFiled: November 14, 2017Date of Patent: May 5, 2020Assignee: Corning Optical Communications RF LLCInventors: Anders Balcer, Michael Ole Matzen, Michael Meister, Thomas Dewey Miller, Jens Petersen, Nikolaj Slobodziuk
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Publication number: 20200047911Abstract: Embodiments are directed to systems and methods for managing electrical load in an aircraft comprising a generator coupled to an aircraft engine, and a power distribution controller configured to monitor current engine operating parameters and to reduce an electrical load on the generator when the engine operating parameters reach a limit during specified aircraft operating conditions. The system may further comprise a non-essential electrical bus coupled to the generator, wherein the electrical load on the generator is reduced by disconnecting the non-essential bus from the generator. The generator may be coupled to the aircraft engine via an accessory gearbox or a transmission gearbox. The monitored current engine operating parameters comprise one or more of an engine torque, a gas generator RPM, and a temperature. The aircraft operating conditions may comprise one or more of a takeoff, a landing, or an engine failure.Type: ApplicationFiled: August 9, 2018Publication date: February 13, 2020Applicant: Bell Helicopter Textron Inc.Inventor: Thomas Dewey Parsons
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Publication number: 20200023988Abstract: A boundary layer utilization apparatus for intake of air to a high speed aircraft, comprises a first air inlet adjacent an exterior surface of a fuselage of the aircraft and offset from the fuselage enough to integrate a second air inlet in the offset space to ingest and divert the boundary layer air flowing next to the fuselage into the aircraft for a useful purpose such as cooling the engine compartment. The second air inlet is disposed aft of the first air inlet to minimize hot gas re-ingestion.Type: ApplicationFiled: July 23, 2018Publication date: January 23, 2020Applicant: Bell Helicopter Textron Inc.Inventors: Thomas Dewey Parsons, Angel David Rosado, Robert Paul Reynolds, David Frank Haynes, William Mathisen Gons
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Publication number: 20200017229Abstract: Systems and methods include providing an aircraft with a fuselage and a convertible engine disposed within the fuselage. The convertible engine is operable as a turbofan engine in a thrust mode and a turboshaft engine in a shaft power mode. The convertible engine includes a housing, an engine core having a low pressure turbine shaft, and a bypass fan system. The bypass fan system includes a bypass fan having a fan clutch. The fan clutch selectively couples at least a portion of the bypass fan to the low pressure turbine shaft when the convertible engine is operated in the thrust mode and decouples at least a portion of the bypass fan from the low pressure turbine shaft when the convertible engine is operated in the shaft power mode.Type: ApplicationFiled: July 13, 2018Publication date: January 16, 2020Applicant: Bell Helicopter Textron Inc.Inventors: Alan Hisashi Steinert, Thomas Dewey Parsons, Troy Cyril Schank
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Publication number: 20200003295Abstract: A drive system for a tiltrotor aircraft operable to transition between rotary and non rotary flight modes. The drive system includes an engine to provide rotational energy and a proprotor assembly to receive rotational energy from the engine when the tiltrotor aircraft is in the rotary flight mode. The proprotor assembly is disengaged from the engine in the non rotary flight mode. The drive system includes a proprotor gearbox including one or more gears mechanically interposed between the engine and the proprotor assembly. The proprotor gearbox transfers rotational energy from the engine to the proprotor assembly when the tiltrotor aircraft is in the rotary flight mode. The drive system includes a lubricant operable to reduce friction between the gears and a lubrication management system to affect a temperature of the lubricant to enhance lubrication between the gears in the proprotor gearbox in the rotary flight mode.Type: ApplicationFiled: July 2, 2018Publication date: January 2, 2020Applicant: Bell Helicopter Textron Inc.Inventors: Thomas Dewey Parsons, Troy Cyril Schank
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Publication number: 20190390564Abstract: A differential pressure transducer provides measurements for determining the restriction, updated in real time, of an inlet barrier filter for a turboshaft engine of an aircraft. The percentage of restriction of the air inlet barrier filter, which corresponds to the condition of the air inlet barrier filter, is determined as a function of mass air flow into the engine during operation. The restriction percentage is indicated on the instrument panel of the rotorcraft.Type: ApplicationFiled: June 22, 2018Publication date: December 26, 2019Applicant: Bell Helicopter Textron Inc.Inventor: Thomas Dewey Parsons