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公开(公告)号：US09528704B2
公开(公告)日：2016-12-27
申请号：US14186157
申请日：2014-02-21
Applicant: General Electric Company
Inventor： Michael John Hughes , Gregory Allen Boardman , Johnie Franklin McConnaughhay , Carlo Antonio Arguinzoni
Abstract: A system includes a a combustor cap configured to be coupled to a plurality of mixing tubes of a multi-tube fuel nozzle, wherein each mixing tube of the plurality of mixing tubes is configured to mix air and fuel to form an air-fuel mixture. The combustor cap includes multiple nozzles integrated within the combustor cap. Each nozzle of the multiple nozzles is coupled to a respective mixing tube of the multiple mixing tubes. In addition, each nozzle of the multiple nozzles includes a first end and a second end. The first end is coupled to the respective mixing tube of the multiple mixing tubes. The second end defines a non-round outlet for the air-fuel mixture. Each nozzle of the multiple nozzles includes an inner surface having first and second portions, the first portion radially diverges along an axial direction from the first end to the second end, and the second portion radially converges along the axial direction from the first end to the second end.
Abstract translation: 一种系统包括：燃烧器盖，其构造成联接到多管燃料喷嘴的多个混合管，其中多个混合管的每个混合管被配置为混合空气和燃料以形成空气 - 燃料混合物。 燃烧器盖包括集成在燃烧器盖内的多个喷嘴。 多个喷嘴的每个喷嘴连接到多个混合管的相应混合管。 此外，多个喷嘴的每个喷嘴包括第一端和第二端。 第一端连接到多个混合管的各个混合管。 第二端限定了空气 - 燃料混合物的非圆形出口。 多个喷嘴的每个喷嘴包括具有第一和第二部分的内表面，第一部分沿着从第一端到第二端的轴向方向径向地分叉，并且第二部分沿着轴向方向从第一端径向地会聚到 第二端
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公开(公告)号：US20150241065A1
公开(公告)日：2015-08-27
申请号：US14186157
申请日：2014-02-21
Applicant: General Electric Company
Inventor： Michael John Hughes , Gregory Allen Boardman , Johnie Franklin McConnaughhay , Carlo Antonio Arguinzoni
IPC: F23R3/28
Abstract: A system includes a a combustor cap configured to be coupled to a plurality of mixing tubes of a multi-tube fuel nozzle, wherein each mixing tube of the plurality of mixing tubes is configured to mix air and fuel to form an air-fuel mixture. The combustor cap includes multiple nozzles integrated within the combustor cap. Each nozzle of the multiple nozzles is coupled to a respective mixing tube of the multiple mixing tubes. In addition, each nozzle of the multiple nozzles includes a first end and a second end. The first end is coupled to the respective mixing tube of the multiple mixing tubes. The second end defines a non-round outlet for the air-fuel mixture. Each nozzle of the multiple nozzles includes an inner surface having first and second portions, the first portion radially diverges along an axial direction from the first end to the second end, and the second portion radially converges along the axial direction from the first end to the second end.
Abstract translation: 一种系统包括：燃烧器盖，其构造成联接到多管燃料喷嘴的多个混合管，其中多个混合管的每个混合管被配置为混合空气和燃料以形成空气 - 燃料混合物。 燃烧器盖包括集成在燃烧器盖内的多个喷嘴。 多个喷嘴的每个喷嘴连接到多个混合管的相应混合管。 此外，多个喷嘴的每个喷嘴包括第一端和第二端。 第一端连接到多个混合管的各个混合管。 第二端限定了空气 - 燃料混合物的非圆形出口。 多个喷嘴的每个喷嘴包括具有第一和第二部分的内表面，第一部分沿着从第一端到第二端的轴向方向径向地分叉，并且第二部分沿轴向方向从第一端径向地会聚到 第二端
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公开(公告)号：US20150241064A1
公开(公告)日：2015-08-27
申请号：US14186016
申请日：2014-02-21
Applicant: General Electric Company
IPC: F23R3/28
CPC classification number: F23R3/283 , F23R3/10 , F23R3/286 , Y02T50/675
Abstract: A system includes a combustor cap assembly for a multi-tube fuel nozzle. The combustor cap assembly includes a support structure defining an interior volume configured to receive an air flow. The combustor cap assembly also includes multiple mixing tubes disposed within the interior volume, wherein each mixing tube is configured to mix air and fuel to form an air-fuel mixture. The combustor cap assembly further includes a combustor cap removably coupled to the support structure. The combustor cap includes multiple nozzles integrated within the combustor cap. Each nozzle of the multiple nozzles is coupled to a respective mixing tube of the multiple mixing tubes. The combustor cap is configured to internally cool itself via one or more cooling features integrated within the combustor cap.
Abstract translation: 一种系统包括用于多管燃料喷嘴的燃烧器盖组件。 燃烧器盖组件包括限定被构造成接收空气流的内部容积的支撑结构。 燃烧器盖组件还包括设置在内部容积内的多个混合管，其中每个混合管构造成混合空气和燃料以形成空气 - 燃料混合物。 燃烧器盖组件还包括可移除地联接到支撑结构的燃烧器盖。 燃烧器盖包括集成在燃烧器盖内的多个喷嘴。 多个喷嘴的每个喷嘴连接到多个混合管的相应混合管。 燃烧器盖构造成通过集成在燃烧器盖内的一个或多个冷却特征来内部冷却自身。
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公开(公告)号：US20240384873A1
公开(公告)日：2024-11-21
申请号：US18789124
申请日：2024-07-30
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：US11371708B2
公开(公告)日：2022-06-28
申请号：US17043004
申请日：2018-04-06
Applicant: General Electric Company
Inventor： Mathew Paul Thariyan , Manampathy Gangadharan Giridharan , Kapil Kumar Singh , Sravan Kumar Dheeraj Kapilavai , Keith Robert McManus , Gregory Allen Boardman , Mark David Durbin
Abstract: A premixer for a gas turbine combustor includes a centerbody, a swirler assembly, and a mixing duct. The swirler assembly includes an inner swirler with vanes that rotate air in a first direction and an outer swirler with vanes that rotate air in an opposite direction. The inner swirler vanes and the outer swirler vanes are separated by an annular splitter. The outer swirler vanes define an outlet plane, and the inner swirler vanes each have a trailing edge that is disposed at an acute angle relative to the outlet plane. In one aspect, the inner swirler is axially offset from the outer swirler. The mixing duct may also define fuel passages that deliver fuel to fuel outlets on the downstream end of the mixing duct. The premixer is designed for operation on gaseous fuel or liquid fuel.
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Patent Agency Ranking
公开(公告)号：US10976053B2
公开(公告)日：2021-04-13
申请号：US15793129
申请日：2017-10-25
Applicant: General Electric Company
Inventor： Gregory Allen Boardman , Pradeep Naik , Joseph Zelina , Clayton Stuart Cooper
Abstract: A combustor assembly includes a volute wall extended annularly around a combustor centerline, extended at least partially as a spiral curve from a circumferential reference line around the combustor centerline, and defining a combustion chamber therewithin, an annular inner wall extended at least partially along a lengthwise direction from the volute wall, an annular outer wall extended at least partially along the lengthwise direction from the volute wall, the annular inner wall and the annular outer wall being separated along a radial direction from the combustor centerline, and a primary flow passage being defined between the annular inner wall and the annular outer wall in fluid communication with the combustion chamber, and a flow passage wall extending between a portion of the volute wall and a portion of the annular outer wall.
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公开(公告)号：US10976052B2
公开(公告)日：2021-04-13
申请号：US15793104
申请日：2017-10-25
Applicant: General Electric Company
Inventor： Gregory Allen Boardman , Pradeep Naik , Joseph Zelina , Clayton Stuart Cooper
Abstract: A combustor assembly is generally provided. The combustor assembly includes a volute wall extended annularly around a combustor centerline. The volute wall is extended at least partially as a spiral curve from a circumferential reference line around the combustor centerline. The volute wall defines a combustion chamber therewithin. An annular inner wall is extended at least partially along a lengthwise direction from the volute wall. An annular outer wall is extended at least partially along the lengthwise direction from the volute wall. The inner wall and the outer wall are each separated along a radial direction from the combustor centerline. A primary flow passage is defined between the inner wall and the outer wall in fluid communication from the combustion chamber.
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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：US20200025385A1
公开(公告)日：2020-01-23
申请号：US16375958
申请日：2019-04-05
Applicant: General Electric Company
Inventor： Gregory Allen Boardman , Pradeep Naik , Manampathy Gangadharan Giridharan , David Albin Lind , Jeffrey Michael Martini
Abstract: The present disclosure is directed to a method for operating a turbine engine, the method including arranging a fluid conduit through a fuel nozzle in a first direction toward a downstream end and in a second direction toward an upstream end, the fluid conduit in fluid communication with a premix passage via a fluid injection port; flowing an oxidizer into the premix passage via a radially oriented first inlet port and a radially oriented second inlet port; flowing a first fuel to the premix passage through the fluid conduit and the fluid injection port, wherein the first fuel is provided to the premix passage axially downstream of the first inlet port; and generating a premixed flame from a mixture of the oxidizer and the first fuel.
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公开(公告)号：US10465909B2
公开(公告)日：2019-11-05
申请号：US15343814
申请日：2016-11-04
Applicant: General Electric Company
Abstract: The present disclosure is directed to a fuel nozzle for a gas turbine engine. The fuel nozzle includes a sleeve defining a plurality of radially oriented air inlet ports. The sleeve defines a sleeve outlet at the downstream end of the fuel nozzle and a longitudinally extended annular inner wall inward of the sleeve in the radial direction. The inner wall defines a fluid passage and an inner wall outlet, in which the inner wall outlet is disposed toward the downstream end of the inner wall. At least a portion of the plurality of radially oriented air inlet ports is outward of the inner wall along the radial direction. The fuel nozzle further includes a plurality of fuel injectors surrounding the sleeve, in which the sleeve and each of the fuel injectors are connected to an aft body at the downstream end and a forward body at the upstream end.
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