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公开(公告)号：US20140190170A1
公开(公告)日：2014-07-10
申请号：US13735340
申请日：2013-01-07
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Jun Cai , Gregory Allen Boardman , Hasan Karim , Lucas John Stoia
CPC classification number: F23R3/346 , F23C2900/07001 , F23R3/14 , F23R3/286
Abstract: A fuel injector for a combustor generally includes an annular outer body having an inlet and an outlet. The outer body at least partially defines an outer flow passage. An inner flow passage extends at least partially through the outer flow passage and a radial swirler is disposed at the inlet of the outer body. The radial swirler includes a first radial passage separated from a second radial passage. The first radial passage has a first plurality of swirler vanes and the second radial passage has a second plurality of swirler vanes. The first radial passage is in fluid communication with the outer flow passage and the second radial passage is in fluid communication with the inner flow passage.
Abstract translation: 用于燃烧器的燃料喷射器通常包括具有入口和出口的环形外部主体。 外体至少部分地限定外部流动通道。 内部流动通道至少部分地延伸穿过外部流动通道，并且径向旋流器设置在外部主体的入口处。 径向旋流器包括与第二径向通道分离的第一径向通道。 第一径向通道具有第一多个旋流器叶片，并且第二径向通道具有第二多个旋流器叶片。 第一径向通道与外流道流体连通，第二径向通道与内流道流体连通。
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公开(公告)号：US20140116054A1
公开(公告)日：2014-05-01
申请号：US13664705
申请日：2012-10-31
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Gregory Scott Means , Gregory Allen Boardman , Jonathan Dwight Berry
CPC classification number: F23D11/24 , F23D11/38 , F23D14/00 , F23D2900/00015 , F23R3/283 , F23R3/286 , F23R3/343 , F23R3/46 , F23R2900/00012 , F23R2900/03044
Abstract: A combustor for a gas turbine generally includes a radial flow fuel nozzle having a fuel distribution manifold, and a fuel injection manifold axially separated from the fuel distribution manifold. The fuel injection manifold generally includes an inner side portion, an outer side portion, and a plurality of circumferentially spaced fuel ports that extend through the outer side portion. A plurality of tubes provides axial separation between the fuel distribution manifold and the fuel injection manifold. Each tube defines a fluid communication path between the fuel distribution manifold and the fuel injection manifold.
Abstract translation: 用于燃气轮机的燃烧器通常包括具有燃料分配歧管的径流式燃料喷嘴和与燃料分配歧管轴向分离的燃料喷射歧管。 燃料喷射歧管通常包括延伸穿过外侧部分的内侧部分，外侧部分和多个周向间隔开的燃料端口。 多个管在燃料分配歧管和燃料喷射歧管之间提供轴向间隔。 每个管限定在燃料分配歧管和燃料喷射歧管之间的流体连通路径。
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公开(公告)号：US20140097276A1
公开(公告)日：2014-04-10
申请号：US13647636
申请日：2012-10-09
Applicant: GENERAL ELECTRIC COMPANY
CPC classification number: F23R3/14 , F23D11/103 , F23D11/105 , F23D17/002 , F23R3/286 , F23R3/36 , Y10T29/49826
Abstract: A fuel nozzle is provided. The fuel nozzle includes a nozzle body, a plurality of swirler vanes, and at least one outlet. The nozzle body includes a back plate, a front plate, and a mixing zone defined therebetween. The back plate includes at least one inlet defined therein and the front plate includes at least one discharge defined therein. The plurality of swirler vanes are positioned between the back plate and the front plate and spaced circumferentially about the mixing zone. Each of the plurality of swirler vanes direct air obliquely into the mixing zone. The at least one outlet is defined within at least one of the nozzle body and the plurality of swirler vanes, the at least one outlet configured to inject fuel into said mixing zone.
Abstract translation: 提供燃料喷嘴。 燃料喷嘴包括喷嘴体，多个旋流器叶片和至少一个出口。 喷嘴体包括背板，前板和限定在其间的混合区。 背板包括限定在其中的至少一个入口，并且前板包括限定在其中的至少一个排出口。 多个旋流器叶片位于后板和前板之间并且围绕混合区周向间隔开。 多个旋流器叶片中的每一个将空气倾斜地引导到混合区域中。 所述至少一个出口限定在所述喷嘴主体和所述多个旋流器叶片中的至少一个中，所述至少一个出口构造成将燃料喷射到所述混合区域中。
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公开(公告)号：US11022313B2
公开(公告)日：2021-06-01
申请号：US15189061
申请日：2016-06-22
Applicant: General Electric Company
Inventor： Gregory Allen Boardman , Pradeep Naik , Allen Michael Danis
Abstract: A rich-quench-lean combustor assembly for a gas turbine engine includes a liner extending between a forward end and an aft end. The liner includes a plurality of quench air jets positioned between the forward end and the aft end. The combustor assembly additionally includes a dome attached to or formed integrally with the liner, the dome and the liner together defining at least in part a combustion chamber. A fuel nozzle is attached to the dome, the fuel nozzle configured as a premix fuel nozzle for providing a substantially homogenous mixture of fuel and air to the combustion chamber, the mixture of fuel and air having an equivalence ratio of at least 1.5.
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公开(公告)号：US10816210B2
公开(公告)日：2020-10-27
申请号：US15718077
申请日：2017-09-28
Applicant: General Electric Company
Inventor： David Albin Lind , Gregory Allen Boardman
Abstract: A fuel injector assembly for a gas turbine engine includes a centerbody extended along a lengthwise direction, the centerbody defining a first fuel nozzle, and an annular shroud defining a second fuel nozzle directly surrounding the centerbody and extended along the lengthwise direction. A passage is defined through the annular shroud and extended generally along the lengthwise direction. The passage defines an exit opening disposed at a downstream end adjacent to the combustion chamber and in fluid communication therewith. The annular shroud defines a fuel inlet opening disposed at an upstream end of the passage. The annular shroud defines an air inlet opening in fluid communication with the passage. The air inlet opening is disposed between the fuel inlet opening and the exit opening.
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Patent Agency Ranking
公开(公告)号：US10598380B2
公开(公告)日：2020-03-24
申请号：US15711203
申请日：2017-09-21
Applicant: General Electric Company
Inventor： David Albin Lind , Rishikesh Karande , Pradeep Naik , Ajoy Patra , Gregory Allen Boardman
Abstract: The present disclosure is directed to a combustion section for a gas turbine engine including a combustor assembly, an outer casing, a fuel injector assembly, and an inner casing. An inner liner and an outer liner are each extended at least partially along a lengthwise direction and at an acute angle. A dome assembly is extended between the inner liner and the outer liner, and the inner liner, and the outer liner together define a combustion chamber therebetween. A bulkhead assembly defining a plurality of walls is coupled to the inner liner and generally surrounding the outer liner and dome assembly. The outer casing surrounds the combustor assembly. The inner casing, the outer casing, and the combustor assembly together define a primary flowpath. An oxidizer flows through the primary flowpath in serial flow through the plenum and the fuel injector assembly into the combustion chamber.
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公开(公告)号：US10458655B2
公开(公告)日：2019-10-29
申请号：US14788644
申请日：2015-06-30
Applicant: General Electric Company
Inventor： Gregory Allen Boardman , Gerardo Antonio Salazar Lois , Jeffrey Michael Martini , Rajesh Sharma , Rishikesh Prakash Karande
Abstract: A system includes a fuel nozzle including a first wall disposed about a central axis, a second wall disposed about the first wall, and a plurality of lobes disposed between the first and second walls, wherein the plurality of lobes is spaced about the central axis to define a plurality of flow passages, and the plurality of flow passages is configured to output a plurality of flows into a flame region.
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公开(公告)号：US20190271470A1
公开(公告)日：2019-09-05
申请号：US15909211
申请日：2018-03-01
Applicant: General Electric Company
Inventor： Gregory Allen Boardman , Pradeep Naik , Jacob Foster , Kediya Vishal Sanjay
Abstract: The present disclosure is directed to a fuel injector including a centerbody defining an air inlet opening defined substantially radially through the centerbody; an outer sleeve surrounding the centerbody, and an end wall coupled to the centerbody and the outer sleeve. The outer sleeve defines a radially oriented first air inlet port defined radially outward of the air inlet opening at the centerbody. A mixing passage is defined between the outer sleeve and the centerbody. A first fuel injection port is defined substantially axially through the end wall to the mixing passage. The first fuel injection port defines a first fuel injection opening at the mixing passage between the first air inlet port at the outer sleeve and the air inlet opening at the centerbody.
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公开(公告)号：US20190212009A1
公开(公告)日：2019-07-11
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：US10215414B2
公开(公告)日：2019-02-26
申请号：US14693838
申请日：2015-04-22
Applicant: General Electric Company
Inventor： Jeffrey Michael Martini , Gregory Allen Boardman , Bassam Sabry Mohammad Abd El-Nabi , Gerardo Antonio Salazar-Lois
Abstract: A gas turbine system include a first body including a central passage extending from a mixing region to a central outlet at a first downstream end portion of the first body, a fuel outlet in the mixing region, an oxidant outlet in the mixing region, and an outer passage including a first passage extending in a downstream direction toward the first downstream end portion and a second passage extending in an upstream direction from the first downstream end portion into the mixing region.
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