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公开(公告)号：US10823416B2
公开(公告)日：2020-11-03
申请号：US15673882
申请日：2017-08-10
Applicant: General Electric Company
Inventor： Nayan Vinodbhai Patel , Daniel Kirtley , Duane Douglas Thomsen , Neeraj Kumar Mishra , Adam Robert Kahn
Abstract: The present disclosure is directed to a combustor assembly for a gas turbine engine comprising a bulkhead wall extended generally along a radial direction relative to a combustor centerline and a mixer disposed concentric to the nozzle centerline. The bulkhead wall defines one or more openings therethrough adjacent to a combustion chamber. Each of the openings defines a nozzle centerline extended along a lengthwise direction. The mixer comprises a retaining wall extended along a radial direction relative to the nozzle centerline and coupled to the upstream side of the bulkhead wall. The mixer further comprises an annular shroud extended at least partially through the one or more openings of the bulkhead wall. The mixer defines a cooling passage through the retaining wall and the annular shroud. The cooling passage defines an inlet opening through the retaining wall and an outlet opening through the annular shroud.
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公开(公告)号：US10591164B2
公开(公告)日：2020-03-17
申请号：US14645959
申请日：2015-03-12
Applicant: General Electric Company
Inventor： Nayan Vinodbhai Patel , Duane Douglas Thomsen
Abstract: A fuel nozzle apparatus for a gas turbine engine includes: an annular outer body extending parallel to a centerline axis, with an exterior surface having a plurality of openings; a main injection ring disposed inside the outer body and including: a circumferential main fuel gallery; and a plurality of main fuel orifices, each main fuel orifice communicating with the main fuel gallery and aligned with one of the openings; a venturi disposed inside the main injection ring; an annular splitter disposed inside the venturi, and including inner and outer walls spaced-apart from each other defining a splitter cavity, and a plurality of discharge holes communicating with the splitter cavity; an array of outer swirl vanes extending between the venturi and the splitter; a pilot fuel injector within the splitter; and an array of inner swirl vanes extending between the splitter and the pilot fuel injector.
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公开(公告)号：US20200025384A1
公开(公告)日：2020-01-23
申请号：US16037389
申请日：2018-07-17
Applicant: General Electric Company
Inventor： Nayan Vinodbhai Patel , Ying Huang , Duane Douglas Thomsen
Abstract: A fuel nozzle for a combustor assembly of a heat engine is generally provided. The fuel nozzle defines a fuel nozzle centerline therethrough and a radial direction extended from the nozzle centerline. The fuel nozzle includes a first wall extended along the radial direction. The first wall defines a first cooling passage and a second cooling passage each extended therethrough. The first cooling passage is defined at a first acute angle relative to the nozzle centerline. The second cooling passage is defined at a second acute angle 90 degrees or less relative to the first acute angle.
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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：US09939157B2
公开(公告)日：2018-04-10
申请号：US14643335
申请日：2015-03-10
Applicant: General Electric Company
Inventor： Nayan Vinodbhai Patel , Duane Douglas Thomsen
CPC classification number: F23R3/286 , F23D11/24 , F23D2900/00015 , F23D2900/11101 , F23R3/28 , F23R3/343
Abstract: A fuel nozzle apparatus for a gas turbine engine includes: a first pilot fuel injector disposed on a centerline axis of the fuel nozzle which defines a direction of air flow through the fuel nozzle, the first pilot fuel injector being of a pressure atomizing type; an annular second pilot fuel injector at least partially surrounding the first pilot fuel injector, the second pilot fuel injector being of an air blast type and having a fuel outlet disposed axially downstream and radially outboard of the first pilot fuel injector; an annular venturi surrounding the first and second pilot fuel injectors, the venturi including a throat of minimum diameter; an array of inner swirl vanes extending between the first pilot fuel injector and the second pilot fuel injector; and an array of outer swirl vanes extending between the second pilot fuel injector and the venturi.
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Patent Agency Ranking
公开(公告)号：US20160177834A1
公开(公告)日：2016-06-23
申请号：US14580301
申请日：2014-12-23
Applicant: General Electric Company
IPC: F02C7/22
CPC classification number: F02C7/22 , F05D2220/32 , F23R3/283 , F23R3/346
Abstract: A gas turbine engine fuel nozzle apparatus includes: an annular outer body, the outer body extending parallel to a centerline axis, and having a generally cylindrical exterior surface extending between forward and aft ends, and having a plurality of openings passing through the exterior surface; an annular main injection ring disposed inside the outer body, the main injection ring including an annular array of fuel posts extending radially outward therefrom; a main fuel gallery extending within the main injection ring in a circumferential direction; a plurality of main fuel orifices, each main fuel orifice communicating with the main fuel gallery and extending through one of the fuel posts; and a suspension structure connecting the main injection ring to the outer body, the suspension structure configured to substantially rigidly locate the position of the main ring in axial and lateral directions while permitting controlled deflection in a radial direction.
Abstract translation: 燃气涡轮发动机燃料喷嘴装置包括：环形外体，外体平行于中心线轴线延伸，并且具有在前端和后端之间延伸的大致圆柱形外表面，并且具有穿过外表面的多个开口; 设置在所述外主体内的环形主注射环，所述主注射环包括从其径向向外延伸的燃料柱的环形阵列; 在主注射环内沿圆周方向延伸的主燃料库; 多个主燃料喷口，每个主燃料孔与主燃料通道连通并延伸通过其中一个燃料柱; 以及将所述主注射环连接到所述外体的悬挂结构，所述悬架结构构造成基本上将所述主环的位置基本上刚性地定位在轴向和横向方向上，同时允许沿径向方向受到控制。
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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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公开(公告)号：US20210285642A1
公开(公告)日：2021-09-16
申请号：US17231750
申请日：2021-04-15
Applicant: General Electric Company
Inventor： Nayan Vinodbhai Patel , Duane Douglas Thomsen , Michael A. Benjamin
Abstract: A System for Aerodynamic Premixer for Reduced Emissions comprising a premixer is generally cylindrical in form and defined by the relationship in physical space between a first ring, a second ring, and a plurality of radial vanes. The first and second rings are found to be generally equidistant, one from the other, at all points along their facing surfaces. Radial vanes connect the first ring to the second ring and thereby form the premixer.
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公开(公告)号：US20210231307A1
公开(公告)日：2021-07-29
申请号：US17231771
申请日：2021-04-15
Applicant: General Electric Company
Inventor： Nayan Vinodbhai Patel , Duane Douglas Thomsen , MIchael A. Benjamin
Abstract: A System for Aerodynamic Premixer for Reduced Emissions comprising a premixer is generally cylindrical in form and defined by the relationship in physical space between a first ring, a second ring, and a plurality of radial vanes. The first and second rings are found to be generally equidistant, one from the other, at all points along their facing surfaces. Radial vanes connect the first ring to the second ring and thereby form the premixer.
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公开(公告)号：US10739006B2
公开(公告)日：2020-08-11
申请号：US15459309
申请日：2017-03-15
Applicant: General Electric Company
Inventor： Nayan Vinodbhai Patel , Alfred Albert Mancini , Duane Douglas Thomsen , Michael Anthony Benjamin
Abstract: A fuel nozzle for a gas turbine engine includes an outer body defining a plurality of openings in an exterior surface. The fuel nozzle also includes a main injection ring disposed at least partially inside the outer body. The main injection ring includes a plurality of fuel posts extending into or through the plurality of openings of the outer body. The plurality of fuel posts include an LP fuel post defining a main fuel orifice, a top surface, and a scarf, the scarf of the LP fuel post extending in the top surface in a first direction relative to the centerline axis away from the main fuel orifice. The plurality of fuel posts also include an HP fuel post defining a main fuel orifice, a top surface, and a scarf, the scarf of the HP fuel post extending in the top surface f in a second direction relative to the centerline axis away from the main fuel orifice, the second direction being at least ninety degrees different than the first direction.
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