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公开(公告)号：US20230091733A1
公开(公告)日：2023-03-23
申请号：US17483251
申请日：2021-09-23
Applicant: General Electric Company
Inventor： Scott Alan Schimmels , Daniel Alan Niergarth , Arthur William Sibbach , Brandon Wayne Miller
Abstract: A method of regulating pressure in a thermal transport bus of a gas turbine engine, the method including: operating the gas turbine engine with the thermal transport bus having an intermediary heat exchange fluid flowing therethrough, the thermal transport bus including one or more heat source heat exchangers and one or more heat sink heat exchangers in thermal communication through the intermediary heat exchanger fluid; and adjusting a flow volume of the thermal transport bus using a variable volume device in fluid communication with the thermal transport bus in response to a pressure change associated with the thermal transport bus.
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公开(公告)号：US20230060238A1
公开(公告)日：2023-03-02
申请号：US18047452
申请日：2022-10-18
Applicant: General Electric Company
Inventor： Donald Scott Yeager , Brandon Wayne Miller
Abstract: A structure for damping at a fluid manifold assembly for an engine is generally provided. The fluid manifold assembly includes a first walled conduit defining a first fluid passage therewithin. A flow of fluid defining a first frequency is permitted through the first fluid passage. A second walled conduit includes a pair of first portions each coupled to the first walled conduit. A second portion is coupled to the pair of first portions. A second fluid passage is defined through the first portion and the second portion in fluid communication with the first fluid passage. The flow of fluid is permitted through the second fluid passage at a second frequency approximately 180 degrees out of phase from the first frequency.
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公开(公告)号：US11591965B2
公开(公告)日：2023-02-28
申请号：US17215130
申请日：2021-03-29
Applicant: General Electric Company
Inventor： Christopher Edward Wolfe , Hendrik Pieter Jacobus de Bock , William Dwight Gerstler , Brian Gene Brzek , Brandon Wayne Miller , Daniel Alan Niergarth , Kevin Robert Feldmann , Kevin Edward Hinderliter
Abstract: A thermal management system for transferring heat between fluids includes a thermal transport bus through which a heat exchange fluid flows. Additionally, the system includes a heat source heat exchanger arranged along the bus such that heat is added to the fluid flowing through the heat source heat exchanger. Moreover, the system includes a plurality of heat sink heat exchangers arranged along the bus such that heat is removed from the fluid flowing through the plurality of heat sink heat exchangers. Furthermore, the system includes a bypass conduit fluidly coupled to the bus such that the bypass conduit allows the fluid to bypass one of the heat source heat exchanger or one of the heat sink heat exchangers. In addition, the system includes a valve configured to control a flow of the fluid through the bypass conduit based on a pressure of the fluid within the bus.
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公开(公告)号：US20230060010A1
公开(公告)日：2023-02-23
申请号：US17408786
申请日：2021-08-23
Applicant: General Electric Company
Inventor： Arthur William Sibbach , Brandon Wayne Miller
Abstract: A turbofan engine is provided. The turbofan engine includes a fan comprising a plurality of fan blades; a turbomachine operably coupled to the fan for driving the fan, the turbomachine comprising a compressor section, a combustion section, and a turbine section in serial flow order and together defining a core air flowpath; a nacelle surrounding and at least partially enclosing the fan; an inlet pre-swirl feature located upstream of the plurality of fan blades, the inlet pre-swirl feature attached to or integrated into the nacelle; and a means for directing incoming objects towards an outer portion of the turbofan engine in communication with the inlet pre-swirl feature.
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公开(公告)号：US11585354B2
公开(公告)日：2023-02-21
申请号：US17840685
申请日：2022-06-15
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Thomas Lee Becker, Jr.
IPC: F04D29/56 , F01D17/16 , F01D9/02 , F02C7/20 , F02C9/54 , F02K3/06 , F04D29/32 , F04D29/52 , F04D29/54
Abstract: An un-ducted turbofan engine defining a radial direction and an axial direction that includes a core engine, a fan, a plurality of variable outlet guide vanes, and a pitch change mechanism. Each of the plurality of variable outlet guide vanes are attached in a rotatable manner to the core engine of the un-ducted turbofan engine. The pitch change mechanism is positioned radially between the engine air flowpath and the plurality of variable outlet guide vanes and coupled to at least one variable outlet guide vane of the plurality of variable outlet guide vanes for changing a pitch of the at least one variable outlet guide vane.
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Patent Agency Ranking
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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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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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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