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公开(公告)号：US09945294B2
公开(公告)日：2018-04-17
申请号：US14978006
申请日：2015-12-22
Applicant: General Electric Company
Inventor： Michael John Hughes , Jonathan Dwight Berry
CPC classification number: F02C7/222 , F02C3/04 , F05D2220/32 , F23R3/002 , F23R3/06 , F23R3/346 , F23R2900/03044
Abstract: A gas turbine that includes a working fluid flowpath extending aftward from a forward injector in a combustor. The combustor may include an inner radial wall, an outer radial wall, and, therebetween, a flow annulus. A staged injector may intersect the flow annulus so to attain an injection point within the working fluid flowpath by which aftward and forward annulus sections are defined. Air directing structure may include an aftward intake section that corresponds to the aftward annulus section and a forward intake section that corresponds to the forward annulus section. The air directing structure may be configured to: direct air entering through the aftward intake section through the aftward annulus section in a forward direction to the staged injector; and direct air entering through the forward intake section through the forward annulus section in a forward direction to the forward injector.
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公开(公告)号：US20170299186A1
公开(公告)日：2017-10-19
申请号：US15442292
申请日：2017-02-24
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Michael John Hughes
IPC: F23R3/28
CPC classification number: F02C7/18 , F02C3/04 , F02C7/22 , F02C7/222 , F05D2220/32 , F05D2240/35 , F05D2260/201 , F05D2260/202 , F23R3/002 , F23R3/005 , F23R3/06 , F23R3/10 , F23R3/283 , F23R3/286 , F23R3/34 , F23R3/346
Abstract: The present disclosure is directed to a segmented annular combustion system including a first panel fuel injector including a premix air plenum, a fuel plenum, and a plurality of first side premixing channels, where each first side premixing channel is in fluid communication with the premix air plenum, the fuel plenum, and a respective first side injection aperture of a plurality of first side injection apertures. A second panel fuel injector is circumferentially spaced from the first panel fuel injector and includes a premix air plenum, a fuel plenum, and a plurality of second side premixing channels where each second side premixing channel is in fluid communication with the premix air plenum, the fuel plenum, and a respective second side injection aperture of a plurality of second side injection apertures. A fuel nozzle is disposed circumferentially between the first panel fuel injection and the second panel fuel injector.
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公开(公告)号：US20170175637A1
公开(公告)日：2017-06-22
申请号：US14978038
申请日：2015-12-22
Applicant: General Electric Company
Inventor： Michael John Hughes , Jonathan Dwight Berry
CPC classification number: F02C7/222 , F01D5/185 , F01D9/023 , F01D9/065 , F02C7/12 , F05D2220/32 , F05D2260/201 , F23R3/002 , F23R3/16 , F23R3/346 , F23R2900/03044
Abstract: A gas turbine that includes: a combustor coupled to a turbine that together define a working fluid flowpath; a compressor discharge cavity; a staged injector; stator blade airfoils extending between inboard and outboard sidewalls; and a first and second coolant flowpath. The first coolant flowpath includes: an intake section connected to the compressor discharge cavity and a downstream port formed through the inboard sidewall; an outtake section including a downstream port connected to the staged injector and an upstream port formed through the outboard sidewall; and a cooling circuit through the airfoil. The second coolant flowpath includes: an intake section connected to the compressor discharge cavity and a downstream port formed through the outboard sidewall; an outtake section that comprises a downstream port connected to the staged injector and an upstream port formed through the inboard sidewall; and a cooling circuit through the airfoil.
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公开(公告)号：US09528701B2
公开(公告)日：2016-12-27
申请号：US13833878
申请日：2013-03-15
Applicant: General Electric Company
Inventor： Michael John Hughes
CPC classification number: F23R3/002 , F23R3/005 , F23R3/46 , F23R2900/03043 , F23R2900/03044
Abstract: A system for tuning a combustor of a gas turbine includes a flow sleeve having an annular main body. The main body includes an upstream end, a downstream end, an inner surface and an outer surface. A cooling channel extends along the inner surface of the main body. The cooling channel extends at least partially between the downstream end and the upstream end of the main body.
Abstract translation: 用于调节燃气涡轮机的燃烧器的系统包括具有环形主体的流动套管。 主体包括上游端，下游端，内表面和外表面。 冷却通道沿着主体的内表面延伸。 冷却通道至少部分地延伸在主体的下游端和上游端之间。
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公开(公告)号：US20150253011A1
公开(公告)日：2015-09-10
申请号：US14719356
申请日：2015-05-22
Applicant: General Electric Company
Inventor： Jong Ho Uhm , Derrick Walter Simons , Gregory Allen Boardman , Bryan Wesley Romig , Kara Edwards , Michael John Hughes
CPC classification number: F23R3/286 , F23C7/004 , F23C2900/07001 , F23D14/08 , F23R3/14 , F23R3/343 , F23R2900/03343
Abstract: A combustor for a gas turbine engine has a head end portion that carries at least one fuel/air nozzle. Each fuel/air nozzle includes a premixed pilot nozzle having premix conduits where each premix conduit has an upstream end defining an opening and having a central axis and downstream end defining an outlet and having a central axis where the central axis of the downstream end is non-parallel with a central axis of a center body of the fuel/air nozzle. The premixed pilot nozzle can include an annular channel disposed radially outwardly from the premix conduits and may include air jets that direct air radially outwardly from the premix conduits.
Abstract translation: 用于燃气涡轮发动机的燃烧器具有承载至少一个燃料/空气喷嘴的头端部分。 每个燃料/空气喷嘴包括具有预混合管道的预混合先导喷嘴，其中每个预混管道具有限定开口的上游端，并且具有中心轴线和下游端限定出口，并且具有中心轴线，其中下游端的中心轴线不是 与燃料/空气喷嘴的中心体的中心轴平行。 预混合引导喷嘴可以包括从预混合管道径向向外设置的环形通道，并且可以包括从预混管道径向向外引导空气的空气射流。
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Patent Agency Ranking
公开(公告)号：US11828467B2
公开(公告)日：2023-11-28
申请号：US16731283
申请日：2019-12-31
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Wei Zhao , Michael John Hughes
IPC: F23R3/28 , B01F25/312
CPC classification number: F23R3/286 , B01F25/31233
Abstract: A fluid mixing apparatus includes mixing conduits that extend through a fluid plenum and that define injection holes therethrough. The fluid plenum, which surrounds a first wall defining a main passage fluidly coupled to a low-pressure fluid source, is surrounded itself by a second wall defining a high-pressure plenum fluidly coupled to a high-pressure fluid source. The mixing conduits fluidly couple the high-pressure plenum to the main passage, and the fluid from the fluid plenum is delivered with the high-pressure fluid to the main passage, where the fluids mix before being discharged from an outlet of the main passage. The fluid mixing apparatus may be used to mix one or more fuels with high- and low-pressure air in a gas turbine combustor. Alternately, the fluid mixing apparatus may mix a fluid with high- and low-pressure water streams.
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公开(公告)号：US11566790B1
公开(公告)日：2023-01-31
申请号：US17513066
申请日：2021-10-28
Applicant: General Electric Company
Inventor： Michael John Hughes , Willy Steve Ziminsky
Abstract: A method of operating a combustor of a turbomachine on a total fuel input that contains a concentration of hydrogen that is greater than about 80% is provided. The method includes injecting a first mixture of air and a first fuel containing a first amount of hydrogen into the primary combustion zone of the combustor to generate a first flow of combustion gases having a first temperature. The method further includes injecting, with one or more premix injectors disposed downstream of the fuel nozzles, a second mixture of air and a second fuel containing a second amount of hydrogen into the secondary combustion zone of the combustor to generate a second flow of combustion gases having a second temperature. The method further includes separately injecting a third fuel into secondary combustion zone to generate a third flow of combustion gases having a third temperature.
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公开(公告)号：US11460191B2
公开(公告)日：2022-10-04
申请号：US17007076
申请日：2020-08-31
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Michael John Hughes
Abstract: Integrated combustor nozzles and turbomachines are provided. An integrated combustor nozzle includes a cooling insert having a flange. The cooling insert further includes a first wall and a second wall that each define respective passages therein. The first wall and the second wall each extend from an open end defined within the flange to a closed end. The first wall and the second wall each include an impingement side spaced apart from a solid side. Each impingement side defines a plurality of impingement apertures configured to direct coolant from the respective passage towards a side wall of the combustion liner. The cooling inserts further includes a collection passageway that is defined between the solid sides of the first wall and the second wall.
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公开(公告)号：US20220065453A1
公开(公告)日：2022-03-03
申请号：US17007068
申请日：2020-08-31
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Michael John Hughes
Abstract: An integrated combustor nozzle includes a combustion liner that extends radially between an inner liner segment and an outer liner segment. The combustion liner includes a forward end portion, an aft end portion, a first side wall, and a second side wall. The aft end portion of the combustion liner defines a turbine nozzle. The integrated combustor nozzle further includes an impingement panel having an impingement plate disposed along an exterior surface of one of the inner liner segment or the outer liner segment. The impingement plate defines a plurality of impingement holes that direct coolant in discrete jets towards the exterior surface of the inner liner segment or the outer liner segment. The impingement panel is radially spaced from the exterior surface to form a cooling flow gap therebetween. The impingement panel includes a collection duct that extends from the impingement panel and defines a collection passage.
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公开(公告)号：US11187091B1
公开(公告)日：2021-11-30
申请号：US17136125
申请日：2020-12-29
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Michael John Hughes
Abstract: Sealing arrangements and turbomachines are provided. A sealing arrangement includes a transition duct having an upstream end and a downstream end. The transition duct includes an aft frame that circumferentially surrounds the downstream end of the transition duct. A stage one nozzle is spaced apart from the aft frame and defines a gap therebetween. A sealing assembly extends across the gap and is magnetically coupled to both the aft frame and the stage one nozzle. The sealing assembly includes a first magnet coupled to the aft frame and a second magnet coupled to the stage one nozzle. The sealing assembly further includes a shell that is coupled to and at least partially surrounds the first magnet and the second magnet.
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