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公开(公告)号：US20220402625A1
公开(公告)日：2022-12-22
申请号：US17891262
申请日：2022-08-19
Applicant: General Electric Company
Inventor： Daniel Alan Niergarth , Brandon Wayne Miller
Abstract: A fuel system is provided for an aircraft having a fuel source. The fuel system includes a fuel oxygen reduction unit defining a liquid fuel supply path, a stripping gas supply path, a liquid fuel outlet path, and a stripping gas return path, wherein the stripping gas return path is in airflow communication with the fuel source.
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公开(公告)号：US20220289394A1
公开(公告)日：2022-09-15
申请号：US17571752
申请日：2022-01-10
Applicant: General Electric Company
Inventor： Thomas Kupiszewski , Brandon Wayne Miller , Daniel Alan Niergarth , Randy M. Vondrell
IPC: B64D27/24 , F01D15/10 , F01D25/18 , F02K5/00 , F04D25/06 , F02C7/32 , B64D27/12 , F02C7/24 , F02K3/06 , F04D19/02 , H02K1/27 , H02K7/18
Abstract: A gas turbine engine includes a compressor section and a turbine section together defining a core air flowpath. Additionally, a rotary component is rotatable with at least a portion of the compressor section and at least a portion of the turbine section. An electric machine is mounted coaxially with the rotary component and positioned at least partially inward of the core air flowpath along a radial direction of the gas turbine engine. A cavity wall defines at least in part a buffer cavity surrounding at least a portion of the electric machine to thermally insulate the electric machine, e.g., from the relatively high temperatures within the core air flowpath.
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公开(公告)号：US11300365B2
公开(公告)日：2022-04-12
申请号：US16011748
申请日：2018-06-19
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Nicholas Taylor Moore , Daniel Alan Niergarth , Jeffrey Douglas Rambo , Hendrik Pieter Jacobus de Bock , William Dwight Gerstler
Abstract: A system for heat exchange and leak detection is generally provided, the system including a heat exchanger including a first wall defining a first passage containing a first fluid. A leak detection enclosure containing a leak detection medium is defined between the first wall and a second wall surrounding the first wall.
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公开(公告)号：US11225975B2
公开(公告)日：2022-01-18
申请号：US16503929
申请日：2019-07-05
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Daniel Alan Niergarth , Darek Tomasz Zatorski
Abstract: A gas turbine engine includes a core turbine engine and a fan mechanically coupled to the core turbine engine. The fan includes a plurality of fan blades, each fan blade defining a base and an inner end along a radial direction of the gas turbine engine. The fan also includes a hub covering the base of each of the plurality of fan blades. Further, the fan includes one or more bearings for supporting rotation of the plurality of fan blades. The one or more bearings define a fan bearing radius along a radial direction of the gas turbine engine. Similarly, the hub defines a hub radius along the radial direction of the gas turbine engine. The ratio of the hub radius to the fan bearing radius is less than about three, providing for desired packaging of the various components within the fan of the gas turbine engine.
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公开(公告)号：US20210340914A1
公开(公告)日：2021-11-04
申请号：US17375489
申请日：2021-07-14
Applicant: General Electric Company
Inventor： Daniel Alan Niergarth , Adon Delgado, JR. , Brandon Wayne Miller , Hendrik Pieter Jacobus de Bock
Abstract: A gas turbine engine includes a turbomachine and a thermal management system. The thermal management system includes a heat source heat exchanger configured to collect heat from the turbomachine during operation; a heat sink heat exchanger; and a thermal transport bus having a heat exchange fluid configured to flow therethrough at a pressure within an operational pressure range. The thermal management system defines an operational temperature range for the heat exchange fluid, the operational temperature range having a lower temperature limit less than about zero degrees Fahrenheit at a pressure within the operational pressure range and an upper temperature limit of at least about 1000 degrees Fahrenheit at a pressure within the operational pressure range.
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Patent Agency Ranking
公开(公告)号：US11143104B2
公开(公告)日：2021-10-12
申请号：US15899831
申请日：2018-02-20
Applicant: General Electric Company
Inventor： Kishanjit Pal , Arnab Sen , Pranav R. Kamat , Brandon Wayne Miller , Daniel Alan Niergarth
Abstract: A method of operating a thermal management system for a gas turbine engine includes determining the gas turbine engine is in a first operating mode; transferring heat from a first heat source exchanger to a heat sink system in response to determining the gas turbine engine is in the first operation mode, the first heat source exchanger thermally coupled to a first system/component of the gas turbine engine; determining the gas turbine engine is in a second operating mode, the second operating mode being different than the first operating mode; and transferring heat from a second heat source exchanger to the heat sink system in response to determining the gas turbine engine is in the second operation mode, the second heat source exchanger thermally coupled to a second system/component of the gas turbine engine, the second system/component being different than the first system/component.
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公开(公告)号：US11085310B2
公开(公告)日：2021-08-10
申请号：US16188373
申请日：2018-11-13
Applicant: General Electric Company
Inventor： Daniel Alan Niergarth , Darek Tomasz Zatorski , Brandon Wayne Miller
IPC: F01D7/00 , B64C11/32 , F02C7/32 , F01D17/12 , F01D7/02 , F02C9/58 , F02C3/10 , F02C7/04 , F02K3/06
Abstract: A gas turbine engine including a core having in serial flow order a compressor, a combustor, and a turbine—the compressor, combustor, and turbine together defining a core air flowpath. The gas turbine engine additionally includes a fan section mechanically coupled to the core, the fan section including a plurality of fan blades, and each of the plurality fan blades defining a pitch axis. An actuation device is operable with the plurality fan blades for rotating the plurality fan blades about their respective pitch axes, the actuation device including an actuator located outward of the core air flowpath to, e.g., simplify the gas turbine engine.
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公开(公告)号：US11025104B2
公开(公告)日：2021-06-01
申请号：US15892962
申请日：2018-02-09
Applicant: General Electric Company
Inventor： Nicholas Taylor Moore , Daniel Alan Niergarth , Paul Robert Gemin , Arthur Vorwerk Radun , Hao Huang
Abstract: An electric machine includes a stator assembly including a first stator segment and a second stator segment, the first and second stator segments each including a plurality of laminations extending generally along a circumferential direction, each pair of adjacent laminations of the first and second stator segments defining a gap therebetween. The first and second stator segments are assembled together such that the laminations of the first stator segment are arranged at least partially in the gaps between the laminations of the second stator segment.
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公开(公告)号：US10826344B2
公开(公告)日：2020-11-03
申请号：US15354422
申请日：2016-11-17
Applicant: General Electric Company
Inventor： Nicholas Taylor Moore , Daniel Alan Niergarth , Paul Robert Gemin
Abstract: An electric machine is provided which includes a rotor disk extending along a radial direction and a having a rotor magnet embedded within the rotor disk. The electric machine further includes a stator assembly in axial or radial magnetic flux communication with the rotor magnets to generate a torque.
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公开(公告)号：US10443412B2
公开(公告)日：2019-10-15
申请号：US14838405
申请日：2015-08-28
Applicant: General Electric Company
Inventor： Daniel Alan Niergarth , Brandon Wayne Miller
Abstract: A variable pitch fan for gas turbine engine is provided. The variable pitch fan includes a plurality of fan blades rotatably coupled to a disk and an actuation assembly for changing a pitch of each of the plurality of fan blades. The actuation assembly generally includes an actuation member operably connected to at least one of the plurality of fan blades and a pin. The pin is movable between a first position in which the pin is positioned at least partially in a channel defined in the actuation member, and a second position. The pin blocks movement of the actuation member relative to the pin past a range defined by the channel when in the first position. The actuation assembly further includes a retraction system for selectively engaging the pin in moving the pin from the first position to the second position.
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