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公开(公告)号：US20230211889A1
公开(公告)日：2023-07-06
申请号：US17568892
申请日：2022-01-05
Applicant: General Electric Company
Inventor： Honggang Wang , Kum Kang Huh , Michael Anthony Benjamin , Koji Asari
CPC classification number: B64D31/12 , B64D27/24 , B64D27/10 , B64D2027/026
Abstract: Systems and methods of aircraft thrust management are provided. For example, a propulsion system for an aircraft comprises a fuel cell assembly comprising a fuel cell, a turbomachine, and a controller comprising memory and one or more processors. The memory stores instructions that, when executed by the one or more processors, cause the propulsion system to perform operations including receiving data indicative of a propulsion system thrust discrepancy and modifying an output of the fuel cell in response to receiving data indicative of the propulsion system thrust discrepancy. Modifying the fuel cell output may include modifying output products, an electrical power output, or both of the fuel cell to balance the thrust provided by the propulsion system.
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公开(公告)号：US20230211888A1
公开(公告)日：2023-07-06
申请号：US17568088
申请日：2022-01-04
Applicant: General Electric Company
Inventor： Honggang Wang , Michael Anthony Benjamin , Richard L. Hart , Seung-Hyuck Hong , Koji Asari
IPC: B64D31/00 , H01M8/04746 , H01M8/04955 , H01M8/04664 , B64D27/10 , B64D27/24 , B64D37/32
CPC classification number: B64D31/00 , H01M8/04753 , H01M8/04955 , H01M8/04664 , B64D27/10 , B64D27/24 , B64D37/32 , H01M2250/20 , B64D2027/026
Abstract: A safety management system for an aircraft, or a propulsion system thereof including a fuel cell assembly and a combustion engine, may include various sensors and controllers configured to execute a safety action. At least one sensor is configured to detect at least one operating parameter of the propulsion system, and a controller is configured to determine that the at least one operating parameter has achieved a safety threshold and to execute a safety action when the at least one operating parameter has achieved the safety threshold. The safety action is configured to control operation of the fuel cell assembly and to control operation of the combustion engine.
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公开(公告)号：US20230138892A1
公开(公告)日：2023-05-04
申请号：US17518903
申请日：2021-11-04
Applicant: General Electric Company
Inventor： Honggang Wang , Richard L. Hart , Michael Anthony Benjamin , Seung-Hyuck Hong
IPC: B64D31/06 , H01M8/04664 , H01M8/04746 , H01M8/04701 , H01M8/0612 , H01M8/04828 , B64D27/24 , B64D27/10 , B60L50/70 , B60L58/34 , F02C7/262
Abstract: A propulsion system including: a fuel cell assembly having a fuel cell defining an outlet positioned to remove output products from the fuel cell and a fuel cell assembly operating condition; a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, the combustion section configured to receive a flow of aviation fuel from an aircraft fuel supply and further configured to receive the output products from the fuel cell; and a controller comprising memory and one or more processors, the memory storing instructions that when executed by the one or more processors cause the propulsion system to perform operations including receiving data indicative of a mid-flight flameout within the combustion section; modifying the fuel cell assembly operating condition in response to receiving data indicative of the mid-flight flameout within the combustion section; and initiating a relight of the combustion section.
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公开(公告)号：US20220282867A1
公开(公告)日：2022-09-08
申请号：US17751886
申请日：2022-05-24
Applicant: General Electric Company
IPC: F23R3/00
Abstract: A combustor for a gas turbine engine includes a forward liner segment and an aft liner segment positioned downstream from the forward liner segment relative to a direction of flow through the combustor. The forward and aft liner segments at least partially define a combustion chamber. Furthermore, the combustor includes a dilution slot frame positioned between the forward and aft liner segments along a longitudinal centerline of the gas turbine engine. Moreover, the dilution slot frame defines a plurality of dilution slots spaced apart from each other along a circumferential direction of the gas turbine engine such that the plurality of dilution slots provides an annular ring of dilution air to the combustion chamber.
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公开(公告)号：US11408356B2
公开(公告)日：2022-08-09
申请号：US15723303
申请日：2017-10-03
Applicant: General Electric Company
Inventor： Steven Clayton Vise , Duane Douglas Thomsen , Richard Wade Stickles , Clayton Stuart Cooper , Donald Lee Gardner , George ChiaChun Hsiao , Michael Anthony Benjamin , Shai Birmaher
Abstract: A system and method for operating a combustion system comprising a fuel nozzle defining at least one main fuel circuit and at least one pilot fuel circuit is generally provided. The method includes determining an overall flow of fuel, the overall flow of fuel defining a sum total fuel through the main fuel circuit and the pilot fuel circuit; determining a plurality of ranges of ratios of main fuel flow through the main fuel circuit versus pilot fuel flow through the pilot circuit from the overall flow of fuel, wherein each range of ratios is based on a combustion criterion different from one another; determining a resultant range of ratios of main fuel flow versus pilot fuel flow based on a hierarchy of combustion criteria, wherein the hierarchy of combustion criteria provides a priority ranking of the combustion criterion; and flowing the overall flow of fuel to the main fuel circuit and the pilot fuel circuit based on the resultant range of ratios of main fuel flow versus pilot fuel flow.
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Patent Agency Ranking
公开(公告)号：US11175045B2
公开(公告)日：2021-11-16
申请号：US15861791
申请日：2018-01-04
Applicant: General Electric Company
Inventor： Michael Anthony Benjamin , Girish Venkata Satya Sesha Goda , Habeeb Kunnummal Manat , Karthikeyan Sampath
Abstract: A method and structure for operating a combustion system of a gas turbine engine to mitigate low frequency combustion acoustics is generally provided. The method includes flowing an oxidizer through a fuel nozzle passage defining an inner wall and an outer wall, in which each of the inner wall and the outer wall are contoured from a first radius to a second radius smaller than the first radius; flowing the oxidizer at a higher axial velocity at the inner wall relative to the outer wall upstream of a fuel injection port; flowing a fuel through the fuel injection port to the fuel nozzle passage to mix with the flow of oxidizer to produce a fuel-oxidizer mixture; and igniting the fuel-oxidizer mixture downstream of the fuel injection port.
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公开(公告)号：US20210317990A1
公开(公告)日：2021-10-14
申请号：US17358377
申请日：2021-06-25
Applicant: General Electric Company
Inventor： Gregory Allen Boardman , Michael Anthony Benjamin , Clayton Stuart Cooper , Joseph Zelina , Eric John Stevens
Abstract: Various embodiments include a trapped vortex combustor and a method for operating trapped vortex combustor. In one embodiment, the trapped vortex combustor comprises a trapped vortex combustion zone and at least one secondary combustion zone disposed downstream of the trapped vortex combustion zone. The trapped vortex combustion zone is operable to receive and combust a first fuel and a first air and produce a first combustion product flowing toroidally therein. The at least one secondary combustion zone is operable to receive and combust the first combustion product and at least one second injection consisting of fuel and/or air and produce at least one second combustion product therein. The combustor may reduce the residence time of the highest temperature combustion products and achieve the lower NOx emission.
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公开(公告)号：US11073286B2
公开(公告)日：2021-07-27
申请号：US15709958
申请日：2017-09-20
Applicant: General Electric Company
Inventor： Gregory Allen Boardman , Michael Anthony Benjamin , Clayton Stuart Cooper , Joseph Zelina , Eric John Stevens
Abstract: Various embodiments include a trapped vortex combustor and a method for operating trapped vortex combustor. In one embodiment, the trapped vortex combustor comprises a trapped vortex combustion zone and at least one secondary combustion zone disposed downstream of the trapped vortex combustion zone. The trapped vortex combustion zone is operable to receive and combust a first fuel and a first air and produce a first combustion product flowing toroidally therein. The at least one secondary combustion zone is operable to receive and combust the first combustion product and at least one second injection consisting of fuel and/or air and produce at least one second combustion product therein. The combustor may reduce the residence time of the highest temperature combustion products and achieve the lower NOx emission.
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公开(公告)号：US10823418B2
公开(公告)日：2020-11-03
申请号：US15447847
申请日：2017-03-02
Applicant: General Electric Company
Inventor： Joseph Zelina , Sarah Marie Monahan , Michael Anthony Benjamin , Venkat Eswarlu Tangirala , Sibtosh Pal , William Thomas Ross
Abstract: A combustor for a turbine engine includes an inner combustion liner and an outer combustion liner together defining at least in part an interior. The interior includes a combustion chamber and a main portion. The combustor also includes an inlet combustion liner at least partially defining the combustion chamber of the interior and including an inlet assembly. The inlet assembly includes at least two cavity air tubes arranged along the axial direction, each cavity air tube extending between an inlet and an outlet, the outlet of each cavity air tube in airflow communication with the combustion chamber for providing the combustion chamber with a flow of air.
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公开(公告)号：US10816202B2
公开(公告)日：2020-10-27
申请号：US15823633
申请日：2017-11-28
Applicant: GENERAL ELECTRIC COMPANY
Abstract: A combustor liner, a gas turbine engine including a combustor having the combustor liner, and a method for regulating jet wakes in the combustor are disclosed. The combustor liner includes a panel, at least one first through-hole, and a plurality of second through-holes including first and second set of through-holes. The at least one first through-hole is disposed on a section of the panel in a first row. The plurality of second through-holes is disposed on the section along axial and circumferential directions and arranged adjacent to the at least one first through-hole. The first set and the second set of through-holes are arranged in a second row and a third row respectively. The first, second, and third rows extend along the circumferential direction. The at least one first through-hole and the plurality of second through-holes collectively cover circumferential plane of the section along the first, second, and third rows.
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