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公开(公告)号：US11781478B2
公开(公告)日：2023-10-10
申请号：US17571720
申请日：2022-01-10
Applicant: Raytheon Technologies Corporation
Inventor： Marc J. Muldoon , Joseph B. Staubach , Jesse M. Chandler , Neil Terwilliger , Gabriel L. Suciu
Abstract: An aircraft propulsion system includes a fan section that includes a fan shaft that is rotatable about a fan axis. The fan shaft includes a fan gear. The aircraft propulsion system also includes a boost turbine engine that includes a first output shaft that includes a first gear that is coupled to the fan gear. The boost turbine engine has a first maximum power capacity. The aircraft propulsion system further includes a cruise gas turbine engine that includes a second output shaft that includes a second gear that is coupled to the fan gear. The cruise turbine engine has a second maximum power capacity that is less than the first maximum power capacity of the boost turbine engine. The fan section produces a thrust that corresponds to power input through the fan gear from the boost turbine engine and the cruise turbine engine.
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公开(公告)号：US11428161B2
公开(公告)日：2022-08-30
申请号：US17142726
申请日：2021-01-06
Applicant: Raytheon Technologies Corporation
Inventor： Steven M. O'Flarity , Neil Terwilliger
Abstract: A gas turbine engine includes a compressor. A turbine is mechanically connected to the compressor by a shaft. An air-driven auxiliary turbine is in fluid communication with the compressor and is configured to receive pressurized air from the compressor. An auxiliary generator is operably connected to the auxiliary turbine. The auxiliary generator is configured to generate electrical energy in response to an operation of the auxiliary turbine. An energy storage device is in electrical communication with the auxiliary generator.
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3.发明授权公开(公告)号：US11421545B2
公开(公告)日：2022-08-23
申请号：US16938579
申请日：2020-07-24
Applicant: Raytheon Technologies Corporation
Inventor： Neil Terwilliger , Christopher J Hanlon , Sorin Bengea , Zubair Ahmed Baig
IPC: F01D11/24
Abstract: A clearance control system for a gas turbine engine may include a rotor blade, an outer structure disposed radially outward from the rotor blade, a heating element, a hybrid electric power source, and a controller. The heating element is configured to cause the outer structure to be heated in response to electric current being supplied to the heating element. A gap between the rotor blade and the outer structure is at least one of increased, decreased, and maintained in response to the outer structure being heated. The hybrid electric power source is configured to supply the electric current to the heating element. The controller is configured to regulate the electric current being supplied to the heating element.
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公开(公告)号：US11549464B2
公开(公告)日：2023-01-10
申请号：US16936602
申请日：2020-07-23
Applicant: Raytheon Technologies Corporation
Inventor： Neil Terwilliger , Gary Collopy
Abstract: A system includes a gas turbine engine having a low speed spool, a high speed spool, and a combustor. The system also includes a low spool motor configured to augment rotational power of the low speed spool. The system further includes a controller configured to cause fuel flow. The controller is operable to control the low spool motor to drive rotation of the low speed spool responsive to a thrust command while the controller does not command fuel flow to the combustor.
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公开(公告)号：US20220397062A1
公开(公告)日：2022-12-15
申请号：US17345205
申请日：2021-06-11
Applicant: Raytheon Technologies Corporation
Inventor： Neil Terwilliger , Lance L. Smith , Neal R. Herring , Christopher J. Hanlon
Abstract: A gas turbine engine includes a turbine section located at an engine central longitudinal axis, a combustor configured to drive rotation of the turbine with combustion products, and a compressor section coupled to the turbine section at the engine central longitudinal axis and driven by the turbine section. An auxiliary compressor is located fluidly between the compressor section and the combustor such that an airflow exiting the compressor section is directed toward the auxiliary compressor. The auxiliary compressor is driven independently from the compressor section and is configured to output the airflow toward the combustor.
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Patent Agency Ranking
公开(公告)号：US20220396363A1
公开(公告)日：2022-12-15
申请号：US17345619
申请日：2021-06-11
Applicant: Raytheon Technologies Corporation
Inventor： Arnab Roy , Marc J. Muldoon , Neil Terwilliger , Nancy Poisson
Abstract: Examples described herein provide a computer-implemented method for managing battery usage for a hybrid electric engine of an aircraft. The method includes receiving a flight plan comprising flight plan data for a flight of an aircraft. The method further includes receiving battery data about a battery system of the aircraft. The method further includes determining waypoints for when to apply electric power from the battery system based at least in part on the flight plan data and the battery data. The method further includes controlling, based at least in part on the waypoints, an electric motor while the flight plan is executed. The method further includes updating, while the flight plan is executed, the waypoints based at least in part on data received during the flight.
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公开(公告)号：US20220055763A1
公开(公告)日：2022-02-24
申请号：US17517936
申请日：2021-11-03
Applicant: Raytheon Technologies Corporation
Inventor： Neil Terwilliger , Sorin Bengea
Abstract: An aspect includes a method of variable cycle compensation in a gas turbine engine. An electric component can be adjusted to compensate for a power change induced by an actuation system by operating the electric component as an electric motor to compensate for an increase in power absorption or a decrease in power production of a turbomachinery of the gas turbine engine. The actuation system is configured to adjust a variable cycle of the turbomachinery by adjusting power absorption or power production, and the electric component can be configured to add or subtract torque to a shaft of the gas turbine engine. The electric component can be operated as an electric generator to compensate for an increase in power production or a decrease in power absorption of the turbomachinery.
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公开(公告)号：US20220034262A1
公开(公告)日：2022-02-03
申请号：US17501051
申请日：2021-10-14
Applicant: Raytheon Technologies Corporation
Inventor： Neil Terwilliger , John P. Virtue
IPC: F02C7/268 , B64D27/10 , B64D27/24 , B64D31/06 , B64D33/00 , F02C9/26 , F02C9/54 , F02K5/00 , F02C6/14
Abstract: An aspect includes a hybrid gas turbine engine system of a hybrid electric aircraft. The hybrid gas turbine engine system includes a gas turbine engine having a low speed spool and a high speed spool, a generator operably coupled to the low speed spool, a high spool electric motor operably coupled to the high speed spool, and a controller. The controller is configured to control the hybrid gas turbine engine system in a powered warm-up state to add heat to one or more components of the gas turbine engine by operating the gas turbine engine with a higher engine power setting above idle to drive rotation of the generator, transfer power from the generator to the high spool electric motor, and produce thrust. The gas turbine engine transitions from the powered warm-up state after reaching a target temperature of the one or more components in the powered warm-up state.
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公开(公告)号：US20210231051A1
公开(公告)日：2021-07-29
申请号：US17142726
申请日：2021-01-06
Applicant: Raytheon Technologies Corporation
Inventor： Steven M. O'Flarity , Neil Terwilliger
Abstract: A gas turbine engine includes a compressor. A turbine is mechanically connected to the compressor by a shaft. An air-driven auxiliary turbine is in fluid communication with the compressor and is configured to receive pressurized air from the compressor. An auxiliary generator is operably connected to the auxiliary turbine. The auxiliary generator is configured to generate electrical energy in response to an operation of the auxiliary turbine. An energy storage device is in electrical communication with the auxiliary generator.
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10.发明授权公开(公告)号：US12180846B2
公开(公告)日：2024-12-31
申请号：US17866841
申请日：2022-07-18
Applicant: Raytheon Technologies Corporation
Inventor： Neil Terwilliger , Christopher J Hanlon , Sorin Bengea , Zubair Ahmed Baig
IPC: F01D11/24
Abstract: A method for active bi-directional control of an outer structure of a gas turbine engine comprises sending, by a controller, a first control signal to a power electronics for varying an electric current supplied to a heating element to cause the outer structure to move in a first radial direction, and sending, by the controller, a second control signal to a valve assembly for varying a cooling air flow supplied to the outer structure to cause the outer structure to move in a second radial direction. The first radial direction is opposite the second radial direction.
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