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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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公开(公告)号：US20200032702A1
公开(公告)日：2020-01-30
申请号：US16431271
申请日：2019-06-04
Applicant: United Technologies Corporation
Inventor： Daniel Bernard Kupratis , Neil Terwilliger , Christopher J. Hanlon
Abstract: An aircraft gas turbine engine system comprises first and second gas turbine engines. The first gas turbine engine has first and second spools. A first power linkage connects the second gas turbine engine to the first spool of the gas turbine engine, and a second power linkage connects the second gas turbine engine to the second spool of the first gas turbine engine.
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Patent Agency Ranking
公开(公告)号：US11629646B2
公开(公告)日：2023-04-18
申请号：US16145431
申请日：2018-09-28
Applicant: United Technologies Corporation
Inventor： Daniel Bernard Kupratis , Neil Terwilliger , Michael M. Romero
Abstract: A disclosed drive assembly for an auxiliary power unit includes a first drive shaft driven by an auxiliary power unit, a second drive shaft driven by a first electric motor, a differential gear system including a ring gear driven by the second drive shaft, a and planet gears supported within a carrier attached to the ring gear. The first drive shaft and an output shaft are coupled to the planet gears and a generator is driven by the output shaft. The electric motor and the auxiliary power unit combine to drive the output shaft.
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公开(公告)号：US11565821B2
公开(公告)日：2023-01-31
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：US11415044B2
公开(公告)日：2022-08-16
申请号：US16431271
申请日：2019-06-04
Applicant: United Technologies Corporation
Inventor： Daniel Bernard Kupratis , Neil Terwilliger , Christopher J. Hanlon
Abstract: An aircraft gas turbine engine system comprises first and second gas turbine engines. The first gas turbine engine has first and second spools. A first power linkage connects the second gas turbine engine to the first spool of the gas turbine engine, and a second power linkage connects the second gas turbine engine to the second spool of the first gas turbine engine.
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公开(公告)号：US11167858B2
公开(公告)日：2021-11-09
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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公开(公告)号：US10995674B2
公开(公告)日：2021-05-04
申请号：US16104579
申请日：2018-08-17
Applicant: United Technologies Corporation
Inventor： Neil Terwilliger , John P. Virtue
Abstract: An embodiment of an engine assembly includes a plurality of offtakes powered by a combustion turbine engine having a high spool and at least one lower spool, and a controller configured to operate the combustion turbine engine through a range between a first low-idle mode, a second high idle mode, and a maximum takeoff power rating mode. The controller operates the engine in the low-idle mode by directing at least a first portion of power from the at least one lower spool to the plurality of offtakes, and wherein the controller operates the engine in the high idle mode by increasing a speed of the high spool relative to a speed of the high spool in the low-idle mode, thereby increasing a compressor outlet (T3) temperature in the high idle mode relative to a T3 temperature in the low-idle mode.
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