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公开(公告)号：US20220333780A1
公开(公告)日：2022-10-20
申请号：US17232653
申请日：2021-04-16
Applicant: General Electric Company
Inventor： Allen M. Danis , Nicholas R. Overman , Steven Clayton Vise , Michael Anthony Benjamin , James Matthew Rogers
Abstract: A swirler apparatus for a combustor, including: primary and secondary swirlers disposed axially adjacent to each other along a swirler centerline; the primary swirler including a plurality of primary swirl vanes arrayed around the swirler centerline, each primary swirl vane including opposed sides bounded between opposed forward and aft edges and opposed leading and trailing edges; wherein the forward edge is oriented at a first vane angle with respect to a radial direction; wherein the aft edge is oriented at a second vane angle with respect to the radial direction; wherein the second vane angle is different from the first vane angle; and the secondary swirler including a plurality of secondary swirl vanes arrayed around the swirler centerline.
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公开(公告)号：US11415321B2
公开(公告)日：2022-08-16
申请号：US17029587
申请日：2020-09-23
Applicant: GENERAL ELECTRIC COMPANY
Abstract: A method for regulating jet wakes in a combustor including: directing compressed fluid into a passageway between a casing and a combustor liner; directing a combustion gas along a combustion zone; discharging a first portion of compressed fluid from the passageway into the combustion zone via a first through-hole which is disposed on a section of a combustor panel in a first circumferential row; and discharging a second portion of the compressed fluid from the passageway into the combustion zone via second through-holes, wherein the second through-holes are disposed on a section of the panel, spaced apart axially and circumferentially, and adjacent to the first through-hole, wherein the second through-holes include a first set of through-holes and a second set of through-holes, the first set of through-holes in a second row and the second set of through-holes in a third row, wherein the second and third rows extend circumferentially.
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公开(公告)号：US20220026068A1
公开(公告)日：2022-01-27
申请号：US17497152
申请日：2021-10-08
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：US10808934B2
公开(公告)日：2020-10-20
申请号：US15865809
申请日：2018-01-09
Applicant: General Electric Company
Inventor： Gregory Allen Boardman , Jeffrey Michael Martini , Michael Anthony Benjamin , Pradeep Naik
Abstract: A fuel injector for a gas turbine engine including an outer sleeve. An upstream end of the outer sleeve defines an inlet opening and a downstream end defines an exit opening, each of which defined within the outer sleeve. The outer sleeve defines a radial opening extended therethrough along the radial direction. At least a portion of the outer sleeve defines a plurality of grooves. The outer sleeve defines a fuel conduit through at least a portion of the outer sleeve outward of the plurality of grooves along the radial direction from the fuel injector centerline. The fuel conduit defines a fuel injection opening inward along the radial direction of the radial opening defined through the outer sleeve. A first member of an arm is coupled to the outer sleeve. A second member of the arm is contoured defining a fuel injection port generally concentric to the fuel injector centerline.
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公开(公告)号：US20200217510A1
公开(公告)日：2020-07-09
申请号：US16239004
申请日：2019-01-03
Applicant: General Electric Company
Inventor： Karthikeyan Sampath , Varun Swaminathan Lakshmanan , Michael Anthony Benjamin , Veeraraju Vanapalli
Abstract: A turbo machine including a heat exchanger flowpath is generally provided. The turbo machine includes an outer casing extended along an axial direction, a prediffuser defining an inlet passage into a combustion section of the turbo machine, an inner casing extended from the prediffuser, in which a diffuser cavity is defined between the outer casing and the inner casing, a first plenum wall extended outward along a radial direction from the prediffuser, and a second plenum wall extended outward along a radial direction from the prediffuser. The second plenum wall is separated along the axial direction from the first plenum wall. A plenum is defined between the first plenum wall and the second plenum wall. The turbo machine includes a heat exchanger including a first conduit in fluid communication with the diffuser cavity. The first conduit is in fluid communication with a passage, and a second conduit in fluid communication with the passage and the plenum. A flow of working fluid is admitted from the diffuser cavity through the heat exchanger to the plenum via the first conduit, the passage, and the second conduit.
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Patent Agency Ranking
公开(公告)号：US20190101062A1
公开(公告)日：2019-04-04
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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公开(公告)号：US09927126B2
公开(公告)日：2018-03-27
申请号：US14735694
申请日：2015-06-10
Applicant: General Electric Company
CPC classification number: F23R3/343 , F23D11/104 , F23D11/105 , F23D11/14 , F23D2900/11101 , F23R3/14 , F23R3/32
Abstract: A pilot fuel injector is provided for a fuel nozzle of a gas turbine engine. The pilot fuel injector can include an axially-elongated, inner pilot centerbody wall extending from an upstream end to a downstream end, with the axially-elongated, inner pilot centerbody wall having a diverging-converging orientation with respect to a centerline axis to define a hollow tube having an upstream diameter, a throat, and a downstream diameter such that the throat has an inner diameter that is less than both of the upstream diameter and the downstream diameter. The pilot fuel injector also includes a center air circuit positioned at the upstream end, and an annular fuel passage defining the downstream end and intersecting with the centerbody wall at a pilot fuel metering orifice. A pilot fuel film surface is downstream from the annular fuel passage.
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公开(公告)号：US12202616B2
公开(公告)日：2025-01-21
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 , B60L50/70 , B60L58/34 , B64D27/10 , B64D27/24 , F02C7/262 , H01M8/04664 , H01M8/04701 , H01M8/04746 , H01M8/04858 , H01M8/0612
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：US12152777B2
公开(公告)日：2024-11-26
申请号：US17340703
申请日：2021-06-07
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Hiranya Kumar Nath , Perumallu Vukanti , Daniel J. Kirtley , Karthikeyan Sampath , Shai Birmaher , Pradeep Naik , Rajendra Mahadeorao Wankhade , Michael Anthony Benjamin , Veeraraju Vanapalli , Deepak Ghiya
Abstract: A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a liner at least partially defining a combustion chamber, the liner including a dilution slot in fluid communication with the combustion chamber; and one or more guides configured to redirect cooling medium into the dilution slot.
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公开(公告)号：US12129789B2
公开(公告)日：2024-10-29
申请号：US17676465
申请日：2022-02-21
Applicant: General Electric Company
Inventor： Honggang Wang , Radislav A. Potyrailo , Michael Anthony Benjamin
Abstract: A propulsion system is provided including: a propulsor; a turbomachine operable to drive the propulsor to generate thrust during operation; a fuel cell assembly configured to add power to the propulsor, the turbomachine, or both; and a multi-gas sensor operable with the turbomachine, the fuel cell assembly, or both for sensing gas composition data of a fluid flow in or to the turbomachine, the fuel cell assembly, or both, the gas composition data comprising data indicative of at least two gases and their concentrations.
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