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公开(公告)号：US20240253014A1
公开(公告)日：2024-08-01
申请号：US18323604
申请日：2023-05-25
Applicant: General Electric Company
Inventor： Karthick Gourishankar , Arundhati Sengupta , Narayanan Janakiraman , Sanjay Kumar Sondhi , Vasanth Srinivasa Kothnur , Hejie Li
IPC: B01J20/28
CPC classification number: B01J20/28016 , C10G25/00 , F02C7/22
Abstract: A hydrocarbon fluid system including a hydrocarbon fluid conduit and an oxygen gettering assembly. The hydrocarbon fluid conduit has a fluid passage through which hydrocarbon fluid flows. The hydrocarbon fluid includes oxygen and has an oxygen content. The oxygen gettering assembly is disposed relative to the hydrocarbon fluid conduit such that an oxygen getter comes into contact with the hydrocarbon fluid as the hydrocarbon fluid flows through the fluid passage to reduce the oxygen content of the hydrocarbon fluid. The oxygen gettering assembly may be a part of a deoxygenation system that also includes a sparging system. The hydrocarbon fluid may be a fuel used in a gas turbine engine.
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公开(公告)号：US11821366B2
公开(公告)日：2023-11-21
申请号：US17351023
申请日：2021-06-17
Applicant: General Electric Company
Inventor： Brandon W. Miller , Robert Jon McQuiston , Stefan Joseph Cafaro , Eric Richard Westervelt , Michael A. Benjamin , Joel M. Haynes , Hejie Li
CPC classification number: F02C7/22 , F02C7/224 , F02C9/28 , F23R3/28 , F05D2220/32 , F05D2240/35 , F23R2900/00
Abstract: A gas turbine engine fuel supply system can include a fuel delivery system, a thermal management system, a fuel manifold, and one or more sensors that identify one or more fuel parameters. A fuel control system adjusts parameters of the fuel based on data received from the sensors.
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公开(公告)号：US20230272749A1
公开(公告)日：2023-08-31
申请号：US17652790
申请日：2022-02-28
Applicant: General Electric Company
Inventor： Hejie Li , Mathew Paul Thariyan , Diana Julieta Méndez Maya , Jorge Omar Mañón Cantú , Brandon W. Miller , Michael A. Benjamin , Brian Devendorf
Abstract: A fuel system including a fuel metering unit, a heat exchanger, a plurality of fuel nozzles, and a coke filtration system. The fuel metering unit is configured to meter a flow of a hydrocarbon fuel. The heat exchanger is fluidly connected to the fuel metering unit. The heat exchanger is configured to heat the hydrocarbon fuel to improve engine performance or efficiency. The plurality of fuel nozzles is fluidly connected to the heat exchanger downstream of the heat exchanger to receive the hydrocarbon fuel heated by the heat exchanger. The coke filtration system includes at least one filter to remove coke particles in the heated fuel. The coke filtration system is located upstream of the plurality of fuel nozzles and directly downstream of the heat exchanger.
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公开(公告)号：US20220235707A1
公开(公告)日：2022-07-28
申请号：US17379261
申请日：2021-07-19
Applicant: General Electric Company
Inventor： Michael Robert Millhaem , Christopher R. Bosco , Gerardo Perez , Hejie Li , Francisco Ernesto de la Pena , Alejandro Federico Medrano Perez , Andrew Campbell
Abstract: A gas turbine engine includes a core cowl and a core contained within the core cowl. The core includes a compressor in fluid communication with a downstream combustor and a downstream turbine, the compressor including a compressor bleed port, wherein an undercowl space is defined between the core cowl and the core. The gas turbine engine further includes a cooling duct disposed at least partially in the undercowl space and having an inlet and an outlet, wherein the cooling duct is in fluid communication with a source of cooling air and is further in fluid communication with the compressor bleed port; a valve assembly including at least one valve disposed in the cooling duct; and a cooling blower disposed within the engine and operable to move an air flow from the inlet of the cooling duct towards the outlet of the cooling duct and through the compressor bleed port.
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公开(公告)号：US20190056108A1
公开(公告)日：2019-02-21
申请号：US15681851
申请日：2017-08-21
Applicant: General Electric Company
Inventor： Hejie Li , David Louis Burrus , Arvind Kumar Rao , Sreejith Keloth
IPC: F23R3/06
Abstract: The present disclosure is directed to a combustor assembly for a gas turbine engine comprising a fuel nozzle and an annular shroud. The fuel nozzle comprises a centerbody extended along a lengthwise direction. The fuel nozzle defines a nozzle centerline extended through the centerbody of the fuel nozzle along the lengthwise direction. The fuel nozzle defines a plurality of exit openings in circumferential arrangement on the centerbody relative to the nozzle centerline. The annular shroud surrounds the centerbody of the fuel nozzle. At least a portion of the shroud defines a contoured structure defining a waveform.
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Patent Agency Ranking
公开(公告)号：US12298006B1
公开(公告)日：2025-05-13
申请号：US18659511
申请日：2024-05-09
Applicant: General Electric Company
Inventor： Gerardo Antonio Salazar Lois , Hejie Li
Abstract: A combustor of a turbine engine combusts fuel and air. The combustor includes a dome and a heat shield fastened to the dome. The heat shield is unconstrained relative to dome, to permit relative thermal expansion and contraction in a radial direction. A heat shield inner portion is generally annular in shape, is arranged about a dome eyelet longitudinal centerline axis, is smaller in diameter than a dome inner portion, and is assembled inside of the dome inner portion. A plurality of pinned assemblies fastens the heat shield to dome. Each pinned assembly includes a fastener with a pin end, the pin end assembled in a clearance fit into a hole in the heat shield inner portion. The fastener is fixed to the dome inner portion, the pin end sliding in the hole in the heat shield during relative thermal expansion and contraction between the dome and the heat shield.
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公开(公告)号：US20250093032A1
公开(公告)日：2025-03-20
申请号：US18469187
申请日：2023-09-18
Applicant: GENERAL ELECTRIC COMPANY , GE Marmara Technology Center Muhendislik Hizmetleri Ltd , GE Aerospace Poland sp. z o.o.
Inventor： Emrah Deniz , Fatih Yasar , Katarzyna Anna Mikolajczyk , Michael T. Bucaro , Ahmet Kacar , Anquan Wang , Hejie Li , Craig Alan Gonyou , Aaron C. Brady
Abstract: A gas turbine engine comprises a compressor section, a combustion section, and a turbine section in a serial flow arrangement and enshrouded by a casing, the combustion section comprising: an annular combustion chamber defined by at least a dome wall and an annular liner; a plurality of combustor cups circumferentially arranged on the dome wall; a fuel supply connected to the casing; and a fuel nozzle passing through the casing and having a nozzle tube and a distribution manifold fluidly coupling the nozzle tube to at least two combustor cups of the plurality of combustor cups; wherein the fuel nozzle is fixed to the at least two combustor cups.
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公开(公告)号：US12116935B2
公开(公告)日：2024-10-15
申请号：US18310386
申请日：2023-05-01
Applicant: General Electric Company
Inventor： Brandon W. Miller , Robert Jon McQuiston , Stefan Joseph Cafaro , Eric Richard Westervelt , Michael A. Benjamin , Joel M. Haynes , Hejie Li
CPC classification number: F02C7/22 , F02C7/224 , F02C9/28 , F05D2220/32 , F05D2240/35 , F05D2260/20
Abstract: A gas turbine engine fuel supply system can include a fuel delivery system, a thermal management system, a fuel manifold, and one or more sensors that identify one or more fuel parameters. A fuel control system adjusts parameters of the fuel based on data received from the sensors.
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公开(公告)号：US12031484B2
公开(公告)日：2024-07-09
申请号：US17160742
申请日：2021-01-28
Applicant: General Electric Company
Inventor： Michael Robert Millhaem , Christopher R. Bosco , Gerardo Perez , Hejie Li , Francisco Ernesto de la Pena , Alejandro Federico Medrano Perez , Andrew Campbell
CPC classification number: F02C7/18 , F01D25/12 , F01D21/12 , F02C9/18 , F05D2220/323 , F05D2220/50 , F05D2240/35 , F05D2260/20 , F05D2270/303 , F05D2270/3032 , F05D2270/304
Abstract: A method is provided for operating a gas turbine engine. The method includes: determining data indicative of an operation of a cooling system of the gas turbine engine during a shutdown of the gas turbine engine, following the shutdown of the gas turbine engine, or both; and modifying a startup schedule of the gas turbine engine in response to the determined data indicative of the operation of the cooling system of the gas turbine engine.
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公开(公告)号：US20190056109A1
公开(公告)日：2019-02-21
申请号：US15681918
申请日：2017-08-21
Applicant: General Electric Company
Inventor： Hejie Li , Duane Douglas Thomsen
IPC: F23R3/06
Abstract: The present disclosure is directed to a combustor assembly for a gas turbine engine. The combustor assembly includes a fuel nozzle comprising a centerbody extended along a lengthwise direction, wherein the fuel nozzle defines a nozzle centerline extended through the centerbody along the lengthwise direction. The centerbody defines a plurality of exit openings in circumferential arrangement relative to the nozzle centerline. The plurality of exit openings defines two or more locations different from one another on the centerbody along the lengthwise direction.
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