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公开(公告)号：US11352960B2
公开(公告)日：2022-06-07
申请号：US16864646
申请日：2020-05-01
Applicant: General Electric Company
Inventor： Alfred Albert Mancini , Daniel Alan Niergarth , Ethan Patrick O'Connor , Brandon Wayne Miller
Abstract: In one exemplary embodiment of the present disclosure, a method of operating a fuel system for an aeronautical gas turbine engine is provided. The method includes: providing a flow of fuel to a fuel nozzle of the aeronautical gas turbine engine during a wind down condition; operating a fuel oxygen reduction unit to reduce an oxygen content of the flow of fuel provided to the fuel nozzle of the aeronautical gas turbine engine during the wind down condition; and ceasing providing the flow of fuel to the fuel nozzle of the aeronautical gas turbine engine, the fuel nozzle comprising a volume of fuel after ceasing providing the flow of fuel to the fuel nozzle; wherein operating the fuel oxygen reduction unit comprises operating the fuel oxygen reduction unit to reduce an oxygen content of the volume of fuel in the fuel nozzle to less than 20 parts per million.
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公开(公告)号：US20220128317A1
公开(公告)日：2022-04-28
申请号：US17569619
申请日：2022-01-06
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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43.发明申请公开(公告)号：US20220112902A1
公开(公告)日：2022-04-14
申请号：US17560544
申请日：2021-12-23
Applicant: General Electric Company
Abstract: The variable pitch propeller assembly includes a hub. The variable pitch propeller assembly also includes a plurality of propeller blade assemblies spaced circumferentially about the hub. Each of the plurality of propeller blade assemblies configured to rotate a respective propeller blade. The variable pitch propeller assembly also includes a hydraulic fluid port assembly integrally formed and including at least three hydraulic fluid ports configured to receive respective flows of hydraulic fluid from a stationary hydraulic fluid transfer sleeve. The variable pitch propeller assembly also includes a pitch actuator assembly coupled in flow communication with at least three hydraulic fluid ports through respective hydraulic fluid transfer tubes. The pitch actuator coupled to the plurality of propeller blade assemblies to selectively control a pitch of the propeller blades. The pitch actuator assembly includes a travel stop configured to limit a rotation of at least one of the pitch actuator assemblies.
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公开(公告)号：US20210340916A1
公开(公告)日：2021-11-04
申请号：US16864646
申请日：2020-05-01
Applicant: General Electric Company
Inventor： Alfred Albert Mancini , Daniel Alan Niergarth , Ethan Patrick O'Connor , Brandon Wayne Miller
Abstract: In one exemplary embodiment of the present disclosure, a method of operating a fuel system for an aeronautical gas turbine engine is provided. The method includes: providing a flow of fuel to a fuel nozzle of the aeronautical gas turbine engine during a wind down condition; operating a fuel oxygen reduction unit to reduce an oxygen content of the flow of fuel provided to the fuel nozzle of the aeronautical gas turbine engine during the wind down condition; and ceasing providing the flow of fuel to the fuel nozzle of the aeronautical gas turbine engine, the fuel nozzle comprising a volume of fuel after ceasing providing the flow of fuel to the fuel nozzle; wherein operating the fuel oxygen reduction unit comprises operating the fuel oxygen reduction unit to reduce an oxygen content of the volume of fuel in the fuel nozzle to less than 20 parts per million.
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公开(公告)号：US11131256B2
公开(公告)日：2021-09-28
申请号：US16178898
申请日：2018-11-02
Applicant: General Electric Company
Inventor： Ethan Patrick O'Connor , Daniel Alan Niergarth , Brandon Wayne Miller , Richard Alan Wesling
IPC: B01D47/00 , F02D21/08 , F02D21/04 , F02B47/10 , B01D19/00 , B01D45/12 , F02C7/224 , B01D3/38 , B04B5/12 , F01M13/04 , F02C3/20 , F02C3/24
Abstract: A fuel oxygen conversion unit includes a contactor defining a liquid fuel inlet, a stripping gas inlet and a fuel/gas mixture outlet. The fuel oxygen conversion unit also includes a fuel/gas separator defining a fuel/gas mixture inlet in flow communication with the fuel/gas mixture outlet of the contactor, an axial direction, and a radial direction. The fuel/gas separator includes a separator assembly including a core including a gas-permeable section extending along the axial direction and defining a maximum diameter, the maximum diameter of the gas-permeable section being substantially constant along the axial direction; and a stationary casing, the fuel/gas separator defining a fuel/gas chamber in fluid communication with the fuel/gas mixture inlet at a location inward of the stationary casing and outward of the gas-permeable section of the separator assembly along the radial direction.
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Patent Agency Ranking
公开(公告)号：US11097849B2
公开(公告)日：2021-08-24
申请号：US16126269
申请日：2018-09-10
Applicant: General Electric Company
Inventor： Nikolai N. Pastouchenko , Randy M. Vondrell , Kurt David Murrow , Jixian Yao , Brandon Wayne Miller , Patrick Michael Marrinan , Daniel Alan Niergarth , Narendra Digamber Joshi
Abstract: A method for operating an electric fan of an aircraft propulsion system includes driving a plurality of fan blades of the electric fan with an electric machine to generate thrust for the aircraft; and driving the electric machine with the plurality of fan blades of the electric fan to generate electrical power subsequent to driving the plurality of fan blades of the electric fan with the electric machine to generate thrust for the aircraft.
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公开(公告)号：US10951095B2
公开(公告)日：2021-03-16
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
IPC: F01D15/10 , F02C6/00 , H02K11/26 , B64D41/00 , F16C32/06 , F16C41/00 , H02K5/167 , H02K7/08 , H02K7/18
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：US10941706B2
公开(公告)日：2021-03-09
申请号：US15895336
申请日：2018-02-13
Applicant: General Electric Company
Inventor： Arnab Sen , Brandon Wayne Miller , Bhaskar Nanda Mondal , Kishanjit Pal , Daniel Alan Niergarth
Abstract: An aeronautical gas turbine engine includes a turbomachine including a compressor section, a combustion section, a turbine section, and an exhaust section in serial flow order. The aeronautical gas turbine engine additionally includes a closed cycle heat engine including a compressor configured to compress a working fluid; a primary heat exchanger in thermal communication with the turbomachine and the working fluid, the primary heat exchanger configured to transfer heat from the turbomachine to the working fluid; an expander coupled to the compressor for expanding the working fluid; and an output shaft driven by the expander.
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公开(公告)号：US10826343B2
公开(公告)日：2020-11-03
申请号：US15354370
申请日：2016-11-17
Applicant: General Electric Company
Abstract: An electric machine is provided which includes a rotor disk extending along a radial direction and having a rotor flange attached to or formed integrally with the rotor disk and extending substantially along the axial direction. A plurality of rotor magnets are mounted on the rotor disk and supported by the rotor flange such that the rotor flange absorbs centrifugal loads exerted on the magnets and enables high speeds of operation.
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公开(公告)号：US20200269991A1
公开(公告)日：2020-08-27
申请号：US16864441
申请日：2020-05-01
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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