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公开(公告)号：US11255263B2
公开(公告)日：2022-02-22
申请号：US16733504
申请日：2020-01-03
Applicant: United 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：US11124291B2
公开(公告)日：2021-09-21
申请号：US16219423
申请日：2018-12-13
Applicant: United Technologies Corporation
Inventor： Neil Terwilliger , Stuart S. Ochs
Abstract: An aircraft is provided and includes fuselage having a nose, a main section aft of the nose and a tail aft of the main section, an engine nacelle partially embedded in the tail and including a boundary layer ingestion (BLI) propulsor with an inlet directly adjacent to the fuselage and a nozzle element disposed upstream from the inlet and configured to accelerate boundary flows flowing toward the interior side of the engine nacelle.
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公开(公告)号：US10773812B2
公开(公告)日：2020-09-15
申请号：US16104288
申请日：2018-08-17
Applicant: United Technologies Corporation
Inventor： Neil Terwilliger , David A. Golfin
Abstract: An aspect includes a battery charging system for a hybrid electric aircraft. The battery charging system includes a generator, a battery system, and a controller. The controller is operable to charge the battery system up to a first charge level based on receiving a first charging current at a power input. An operational status of a gas turbine engine of the hybrid electric aircraft is monitored. The battery system is charged at a second charging current received from the generator driven by the gas turbine engine responsive to determining that the gas turbine engine is in a taxi state, where the second charging current is less than the first charging current. Charging of the battery system is halted based on detecting a transition of the gas turbine engine from the taxi state to an off-idle throttle state.
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4.发明授权公开(公告)号：US10760444B2
公开(公告)日：2020-09-01
申请号：US15979112
申请日：2018-05-14
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Neil Terwilliger , Christopher J Hanlon , Sorin Bengea , Zubair Ahmed Baig
IPC: F01D11/24
Abstract: A hybrid energy storage and control system for a clearance control system for a gas turbine engine may comprise a hybrid electric power source, a first converter, a second converter configured to receive electric power from the hybrid electric power source via the first converter and configured to send the electric power to a heating element for controlling a blade tip clearance between a rotor blade and an outer structure of the gas turbine engine, and a controller in electronic communication with the second converter. The hybrid electric power source may comprise a battery, a supercapacitor, and/or an ultracapacitor.
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公开(公告)号：US20200182113A1
公开(公告)日：2020-06-11
申请号：US16586348
申请日：2019-09-27
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Daniel B. Kupratis , Neil Terwilliger , Gary Roberge
IPC: F01N3/04
Abstract: A fluid injection system for a gas turbine engine may comprise a fluid injector configured to inject a fluid into an exhaust flow exiting a turbine section of the gas turbine engine. The fluid injector may be coupled to a turbine exit guide vane located at a forward end of an exhaust system of the gas turbine engine. The fluid may decrease a temperature of the exhaust flow exiting the turbine section and/or increase a thrust of the gas turbine engine.
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Patent Agency Ranking
公开(公告)号：US20200031480A1
公开(公告)日：2020-01-30
申请号：US16524752
申请日：2019-07-29
Applicant: United Technologies Corporation
Inventor： Zubair Ahmed Baig , Neil Terwilliger , Sorin Bengea
Abstract: A power system of an aircraft includes a hybrid energy storage system with at least two energy storage subsystems each having a different power-energy density. The power system also includes one or more electric motors operably coupled to the hybrid energy storage system and to an aircraft engine. The power system further includes a means for controlling one or more electric power flows of the hybrid energy storage system to/from the one or more electric motors based on a modeled electric power demand associated with an engine load of one or more spools of the aircraft engine.
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公开(公告)号：US11111809B2
公开(公告)日：2021-09-07
申请号：US15979085
申请日：2018-05-14
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Neil Terwilliger , Christopher J. Hanlon , Patrick D Couture , Coy Bruce Wood
Abstract: A clearance control system for a gas turbine engine may comprise a rotor blade, an outer structure disposed radially outward from the rotor blade, and a heating element configured to cause the outer structure to be heated in response to electric current being supplied to the heating element, wherein 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.
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公开(公告)号：US11024894B2
公开(公告)日：2021-06-01
申请号：US15971295
申请日：2018-05-04
Applicant: United Technologies Corporation
Inventor： Neil Terwilliger
IPC: H01M10/44 , H01M10/613 , H01M10/625 , H01M10/656
Abstract: A method of recharging an energy storage system for a vehicle, the energy storage system operable in a charging mode and a discharging mode includes balancing a discharging mode waste power and a discharging mode removal power to independently maintain the energy storage system near a discharging design temperature during the discharging mode; receiving an off-board cooling flow into an on-board cooling architecture of the energy storage system during charging mode, wherein the on-board cooling architecture comprises a network of on-board passages proximate to at least portions of the energy storage system; and distributing the off-board cooling flow to maintain the energy storage system near a peak charging design temperature through a balance of a charging mode waste power and a charging mode removal power.
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公开(公告)号：US11015523B2
公开(公告)日：2021-05-25
申请号：US16431259
申请日：2019-06-04
Applicant: United Technologies Corporation
Inventor： Neil Terwilliger , Daniel Bernard Kupratis , Christopher J. Hanlon
Abstract: An aircraft gas turbine engine system comprises first and second gas turbine engines connected by an inter-engine gas path. The first gas turbine engine has a first spool with a first compressor section, and a second spool with a second compressor section downstream of and rotationally independent from the first compressor section. The second gas turbine engine is configured to provide power to at least one of the first and second spools of the first gas turbine engine. The inter-engine gas path is disposed to receive gas flow bled from a bleed location in the first gas turbine engine downstream of the first compressor section, and to supply this gas flow to an inlet of the second gas turbine engine.
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公开(公告)号：US20200079517A1
公开(公告)日：2020-03-12
申请号：US16126200
申请日：2018-09-10
Applicant: United Technologies Corporation
Inventor： Neil Terwilliger , Sorin Bengea
Abstract: An aspect includes a variable cycle system of a gas turbine engine. The variable cycle system includes an actuation system, an electric component, and a controller. The actuation system is configured to adjust a variable cycle of turbomachinery of the gas turbine engine. The electric component is operable to provide a shaft power supply or a load corresponding respectively to an adjustment of the turbomachinery. The controller is operable to adjust an output of either or both of the actuation system and the electric component for separate control of thrust and cycle responses.
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