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公开(公告)号：US11097850B2
公开(公告)日：2021-08-24
申请号：US16503943
申请日：2019-07-05
Applicant: General Electric Company
Inventor： Daniel Alan Niergarth , Randy M. Vondrell , Brandon Wayne Miller , Patrick Michael Marrinan
Abstract: A propulsion system for an aircraft includes an electric propulsion engine configured to be mounted to the aircraft at an aft end of the aircraft. The electric propulsion engine includes a power gearbox mechanically coupled to an electric motor. The electric propulsion engine further includes a fan rotatable about a central axis of the electric propulsion engine by the electric motor through the power gearbox. Moreover, the electric propulsion engine includes an attachment assembly for mounting at least one of the electric motor or the power gearbox. The attachment assembly includes a torsional damper for accommodating a torsional vibration of the electric motor or the power gearbox.
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公开(公告)号：US20210246836A1
公开(公告)日：2021-08-12
申请号：US17240234
申请日：2021-04-26
Applicant: General Electric Company
Inventor： Justin Paul Smith , Brandon Wayne Miller , Daniel Alan Niergarth
Abstract: A thermal management system includes a first heat source assembly including a first heat source exchanger, a first thermal fluid inlet line extending to the first heat source exchanger, and a first thermal fluid outlet line extending from the first heat source exchanger; a second heat source assembly including a second heat source exchanger, a second thermal fluid inlet line extending to the second heat source exchanger, and second a thermal fluid outlet line extending from the second heat source exchanger; a shared assembly including a thermal fluid line and a heat sink exchanger, the shared assembly defining an upstream junction in fluid communication with the first thermal fluid outlet line and second thermal fluid outlet line and a downstream junction in fluid communication with the first thermal fluid inlet line and second thermal fluid inlet line; and a controller configured to selectively fluidly connect the first heat source assembly or the second heat source assembly to the shared assembly.
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公开(公告)号：US11053812B2
公开(公告)日：2021-07-06
申请号：US16108133
申请日：2018-08-22
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Ian Francis Prentice , Daniel Alan Niergarth
Abstract: A fan for a gas turbine engine is provided. The fan includes a plurality of fan blades, a disk, and a trunnion mechanism for attaching the fan blades to the disk. The disk can be formed of a plurality of individual disk segments, with the trunnion mechanism attaching one of the plurality of fan blades to a respective disk segment. A retention member is also provided. The retention member includes a means for catching a portion of the trunnion mechanism should a primary attachment system of the trunnion mechanism fail.
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公开(公告)号：US11022037B2
公开(公告)日：2021-06-01
申请号：US15861802
申请日：2018-01-04
Applicant: General Electric Company
Inventor： Daniel Alan Niergarth , Brandon Wayne Miller , Raymond Floyd Martell , Jeffrey Douglas Rambo , Ryan James Matthys , Joel Francis Kirk
IPC: F02C7/143 , F01D5/14 , F02C7/18 , F01D25/12 , F02C7/12 , F01D5/08 , F02C3/06 , F23R3/28 , F01D9/06
Abstract: A gas turbine engine includes a turbomachine including a compressor section, a combustion section, a turbine section, and an exhaust section arranged in serial flow order and together defining at least in part a core air flowpath. The gas turbine engine also includes a thermal management system including a flowpath heat exchanger coupled to, or integrated into, one or more components of the compressor section, the combustion section, the turbine section, or the exhaust section such that the flowpath heat exchanger is directly thermally coupled to an airflow through the core air flowpath.
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公开(公告)号：US11015534B2
公开(公告)日：2021-05-25
申请号：US16202747
申请日：2018-11-28
Applicant: General Electric Company
Inventor： Justin Paul Smith , Brandon Wayne Miller , Daniel Alan Niergarth
Abstract: A thermal management system includes a first heat source assembly including a first heat source exchanger, a first thermal fluid inlet line extending to the first heat source exchanger, and a first thermal fluid outlet line extending from the first heat source exchanger; a second heat source assembly including a second heat source exchanger, a second thermal fluid inlet line extending to the second heat source exchanger, and second a thermal fluid outlet line extending from the second heat source exchanger; a shared assembly including a thermal fluid line and a heat sink exchanger, the shared assembly defining an upstream junction in fluid communication with the first thermal fluid outlet line and second thermal fluid outlet line and a downstream junction in fluid communication with the first thermal fluid inlet line and second thermal fluid inlet line; and a controller configured to selectively fluidly connect the first heat source assembly or the second heat source assembly to the shared assembly.
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Patent Agency Ranking
公开(公告)号：US11008883B2
公开(公告)日：2021-05-18
申请号：US15709535
申请日：2017-09-20
Applicant: General Electric Company
Inventor： Darek Tomasz Zatorski , Gert Johannes van der Merwe , Brandon Wayne Miller , Daniel Alan Niergarth
IPC: F01D15/10 , F01D15/12 , F01D1/26 , F01D25/16 , H02K7/18 , H02K7/116 , B64D27/10 , F01D5/03 , F02K5/00 , F02C7/36
Abstract: A turbomachine includes a turbine section including a turbine. The turbine includes a first plurality of turbine rotor blades and a second plurality of turbine rotor blades, the first plurality of turbine rotor blades and second plurality of turbine rotor blades alternatingly spaced along the axial direction. The turbomachine also includes a gearbox. The first plurality of turbine rotor blades and the second plurality of turbine rotor blades are each coupled to one of a ring gear, a planet gear, or a sun gear of the gearbox such that the first plurality of turbine rotor blades is rotatable with the second plurality of turbine rotor blades through the gearbox. The turbomachine also includes an electric machine assembly including a rotor coupled to one of the ring gear, the planet gear, or the sun gear of the gearbox such that the rotor rotates relative to a stator during operation.
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公开(公告)号：US10787928B2
公开(公告)日：2020-09-29
申请号：US15364294
申请日：2016-11-30
Applicant: General Electric Company
Inventor： Andrew Michael Tompkins , Brandon Wayne Miller , Donald Albert Bradley , Michele Gravina , Daniel Alan Niergarth , Lorenzo Cipolla
Abstract: A casing for use in a turbofan engine is provided. The casing includes an inner hub, an intermediate casing positioned radially outward from the inner hub, an outer casing positioned radially outward from the intermediate casing, and a plurality of struts spaced circumferentially about the inner hub and extending between the inner hub and the outer casing. At least one strut of the plurality of struts includes a flow channel extending therethrough. The casing also includes a fluid scoop defined within the inner hub, and a collector that couples the fluid scoop in flow communication with the flow channel.
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公开(公告)号：US20200165982A1
公开(公告)日：2020-05-28
申请号：US16202747
申请日：2018-11-28
Applicant: General Electric Company
Inventor： Justin Paul Smith , Brandon Wayne Miller , Daniel Alan Niergarth
Abstract: A thermal management system includes a first heat source assembly including a first heat source exchanger, a first thermal fluid inlet line extending to the first heat source exchanger, and a first thermal fluid outlet line extending from the first heat source exchanger; a second heat source assembly including a second heat source exchanger, a second thermal fluid inlet line extending to the second heat source exchanger, and second a thermal fluid outlet line extending from the second heat source exchanger; a shared assembly including a thermal fluid line and a heat sink exchanger, the shared assembly defining an upstream junction in fluid communication with the first thermal fluid outlet line and second thermal fluid outlet line and a downstream junction in fluid communication with the first thermal fluid inlet line and second thermal fluid inlet line; and a controller configured to selectively fluidly connect the first heat source assembly or the second heat source assembly to the shared assembly.
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公开(公告)号：US20200044518A1
公开(公告)日：2020-02-06
申请号：US16051982
申请日：2018-08-01
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Daniel Alan Niergarth , Christopher James Kroger , Christian Xavier Stevenson
Abstract: In one an exemplary aspect of the present disclosure, an engine includes a drive shaft; an electric machine including a stator assembly and a rotor assembly, the rotor assembly rotatable relative to the stator assembly; and an electrical break, the drive shaft coupled to the rotor assembly through the electrical break.
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公开(公告)号：US10436151B2
公开(公告)日：2019-10-08
申请号：US14943058
申请日：2015-11-17
Applicant: General Electric Company
Abstract: A gas turbine engine includes a core and a tie shaft. The tie shaft is rotatable about an axial direction of the gas turbine engine by the core of the gas turbine engine. The gas turbine engine additionally includes a modular fan having a plurality of fan blades and a frame. The plurality fan blades are attached to the frame and the frame is slidably received on the tie shaft of the gas turbine engine. The modular fan additionally includes an attachment member removably attaching the frame to the tie shaft of the gas turbine engine to removably install the modular fan in the gas turbine engine.
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