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公开(公告)号：US20180128488A1
公开(公告)日：2018-05-10
申请号：US15343746
申请日：2016-11-04
Applicant: General Electric Company
Inventor： Gregory Allen Boardman , Marco Venturato , Douglas Downey Turner , Valeria Proano Cadena , William Thomas Bennett
Abstract: The present disclosure is directed to a fuel nozzle for a gas turbine engine, the fuel nozzle defining a radial direction, a longitudinal direction, a circumferential direction, an upstream end, and a downstream end. The fuel nozzle includes an aft body coupled to at least one fuel injector. The aft body defines a forward wall and an aft wall each extended in the radial direction, and a plurality of sidewalls extended in the longitudinal direction. The plurality of sidewalls couples the forward wall and the aft wall. At least one sidewall defines an impingement fluid outlet, and the aft body defines an impingement fluid cavity in fluid communication with the impingement fluid outlet.
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公开(公告)号：US20170370585A1
公开(公告)日：2017-12-28
申请号：US15189085
申请日：2016-06-22
Applicant: General Electric Company
Inventor： Gregory Allen Boardman , Pradeep Naik , Allen Michael Danis
CPC classification number: F23R3/06 , F02C7/18 , F05D2220/32 , F05D2270/082 , F23R3/002 , F23R3/007 , F23R3/045 , F23R3/14 , F23R3/286 , F23R2900/03043 , F23R2900/03044 , Y02T50/675 , Y02T50/677
Abstract: A rich-quench-lean combustor assembly for a gas turbine engine includes a fuel nozzle and a dome, the fuel nozzle attached to the dome. The combustor assembly additionally includes a liner attached to or formed integrally with the dome, the liner and the dome together defining at least in part a combustion chamber. Additionally, the liner extends between a forward end and an aft end. The liner includes a plurality of quench air jets positioned between the forward end and aft end and defines a forward section extending from the quench air jets to the dome. The dome and the forward section of the liner are configured to be cooled substantially by one or both of impingement cooling or convective cooling.
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23.发明申请MICROMIXER SYSTEM FOR A TURBINE SYSTEM AND AN ASSOCIATED METHOD THEREOF 审中-公开用于涡轮机系统的MICROMIXER系统及其相关方法公开(公告)号：US20160290650A1
公开(公告)日：2016-10-06
申请号：US14675827
申请日：2015-04-01
Applicant: General Electric Company
IPC: F23R3/28
Abstract: A micromixer system includes a casing having a first side wall and a second side wall. Further, the micromixer system includes a plurality of pipes spaced apart from each other and disposed within the casing. Each pipe includes an inlet and an outlet formed in the first and second side walls respectively. The micromixer system includes a first plenum having a first inlet formed in the casing. The first plenum is disposed around a first portion of the plurality of pipes and fluidically coupled to the plurality of pipes. The micromixer system includes a second plenum having a second inlet formed in the casing and disposed around a second portion of the plurality of pipes. Further, the micromixer system includes a plurality of openings formed in the second side wall, surrounding the outlets of at least some pipes of the plurality of pipes, and fluidically coupled to the second plenum.
Abstract translation: 微混合器系统包括具有第一侧壁和第二侧壁的壳体。 此外，微混合器系统包括彼此间隔开并设置在壳体内的多个管。 每个管道分别包括形成在第一和第二侧壁中的入口和出口。 微混合器系统包括具有形成在壳体中的第一入口的第一增压室。 第一增压室设置在多个管的第一部分周围并流体耦合到多个管。 微混合器系统包括第二增压室，其具有形成在壳体中并设置在多个管道的第二部分周围的第二入口。 此外，微混合器系统包括形成在第二侧壁中的多个开口，围绕多个管道中的至少一些管道的出口，并且流体耦合到第二增压室。
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公开(公告)号：US09217373B2
公开(公告)日：2015-12-22
申请号：US13778222
申请日：2013-02-27
Applicant: General Electric Company
Inventor： Gregory Allen Boardman , James Harold Westmoreland, III , Sarah Lori Crothers , Ronald James Chila
CPC classification number: F02C7/24 , F23R3/28 , F23R3/286 , F23R2900/00014
Abstract: A fuel nozzle includes a center body that extends axially along an axial centerline for a length. A shroud circumferentially surrounds the center body for at least a portion of the length of the center body. A plurality of helical passages circumferentially surround the center body along at least a portion of the length of the center body, and a fuel port in each helical passage has a different convective time.
Abstract translation: 燃料喷嘴包括沿轴向中心线轴向延伸长度的中心体。 围绕中心体的护罩周向地围绕中心体的长度的至少一部分。 多个螺旋形通道沿着中心体的长度的至少一部分周向地包围中心体，并且每个螺旋通道中的燃料口具有不同的对流时间。
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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：US20150219018A1
公开(公告)日：2015-08-06
申请号：US14170716
申请日：2014-02-03
Applicant: General Electric Company
Inventor： Sarah Lori Crothers , Gregory Allen Boardman
CPC classification number: F02C9/28 , F02C9/16 , F05D2270/083
Abstract: A system and method for operating a gas turbine include a controller that determines, for at least one combustion instability, a frequency; a quantification of the frequency or a quantification of the frequency through time; and, optionally, a phase and/or an amplitude. The logic also causes the controller to compare the frequency, the quantification of the frequency or the quantification of the frequency through time, the phase, and/or the amplitude of the at least one combustion instability to an associated predetermined limit. When the frequency is actionable relative to its predetermined limit and one of the quantification of the frequency or the quantification of the frequency through time is actionable relative to its respective predetermined limit, at least one parameter of the gas turbine is adjusted. The quantification of the frequency is one of the standard deviation, the coefficient of variation, the index of dispersion, and the variance.
Abstract translation: 用于操作燃气轮机的系统和方法包括控制器，用于至少一个燃烧不稳定性确定频率; 时间的频率或频率的量化的量化; 以及可选的相位和/或幅度。 逻辑还使得控制器将频率的量化，频率的量化或通过时间，相位和/或至少一个燃烧不稳定性的振幅的量化到相关联的预定极限。 当频率相对于其预定极限是可操作的，并且频率的量化或通过时间的频率的量化中的一个相对于其相应的预定极限是可操作的，则调节燃气轮机的至少一个参数。 频率的量化是标准偏差，变异系数，色散指数和方差之一。
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公开(公告)号：US20140283522A1
公开(公告)日：2014-09-25
申请号：US13797859
申请日：2013-03-12
Applicant: General Electric Company
IPC: F23R3/28
CPC classification number: F23R3/286
Abstract: Embodiments of the present disclosure are directed to a system having components for premixing fuel and air prior to combustion within a combustion chamber. The system includes a plurality of mixing tubes configured to receive and to mix fuel and air. Each mixing tube is paired with a fuel injector, and the fuel injector is positioned axially within a portion of the mixing tube. Fuel is injected from the fuel injector into the respective mixing tube, and air flows radially into each mixing tube through one or more apertures formed on the mixing tube. The fuel and air are mixed within the mixing tube and are deposited into a combustion chamber for combustion.
Abstract translation: 本公开的实施例涉及具有用于在燃烧室内燃烧之前预混燃料和空气的部件的系统。 该系统包括配置成接收和混合燃料和空气的多个混合管。 每个混合管与燃料喷射器配对，并且燃料喷射器轴向位于混合管的一部分内。 燃料从燃料喷射器喷射到相应的混合管中，并且空气通过形成在混合管上的一个或多个孔径向流入每个混合管。 燃料和空气在混合管内混合并沉积到用于燃烧的燃烧室中。
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公开(公告)号：US20140144150A1
公开(公告)日：2014-05-29
申请号：US13687103
申请日：2012-11-28
Applicant: GENERAL ELECTRIC COMPANY
IPC: F23R3/28
Abstract: A fuel nozzle for use in a turbine engine is provided. The fuel nozzle includes a fuel injector configured to discharge a flow of fuel therefrom and a premixer tube coupled in flow communication with the fuel injector. The premixer tube is configured to receive the fuel flow and a flow of air at an upstream end of the premixer tube, wherein the fuel and air are progressively mixed as the fuel and air are channeled through the length of the premixer tube.
Abstract translation: 提供了一种用于涡轮发动机的燃料喷嘴。 燃料喷嘴包括燃料喷射器，该燃料喷射器构造成从其中排出燃料流，以及与燃料喷射器流动连通地联接的预混合管。 预混合器管被配置为在预混合管的上游端接收燃料流和空气流，其中当燃料和空气通过预混合管的长度时，燃料和空气逐渐混合。
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公开(公告)号：US11181269B2
公开(公告)日：2021-11-23
申请号：US16191850
申请日：2018-11-15
Applicant: General Electric Company
Inventor： Gregory Allen Boardman , Pradeep Naik
Abstract: A gas turbine engine including a trapped vortex combustor assembly is generally provided. The combustor assembly includes an inner liner wall extended annularly around a combustor centerline, and an outer liner wall extended annularly around the combustor centerline. The inner liner wall and the outer liner wall together define an involute wall extended at least partially as a spiral curve from a circumferential reference line around the combustor centerline. The involute wall defines an involute combustion chamber. One or more of the inner liner wall and the outer liner wall each define a first dilution opening and a shaped dilution opening.
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公开(公告)号：US11156361B2
公开(公告)日：2021-10-26
申请号：US16516586
申请日：2019-07-19
Applicant: General Electric Company
Inventor： Gregory Allen Boardman , Pradeep Naik , Manampathy Gangadharan Giridharan , David Albin Lind , Jeffrey Michael Martini , Clayton S. Cooper
Abstract: The present disclosure is directed to a fuel injector for a gas turbine engine. The fuel injector includes an end wall, a centerbody, an outer sleeve surrounding the centerbody from the end wall toward the downstream end of the fuel injector, and a thermal management conduit. The centerbody includes an axially extended outer wall and inner wall extended from the end wall toward a downstream end of the fuel injector. The outer wall, the inner wall, and the end wall together define a fluid conduit extended in a first direction toward the downstream end of the fuel injector and in a second direction toward an upstream end of the fuel injector. The outer sleeve and the centerbody define a premix passage radially therebetween and an outlet at the downstream end of the premix passage. The outer sleeve defines a plurality of radially oriented first air inlet ports in circumferential arrangement at a first axial portion of the outer sleeve. The outer sleeve defines a plurality of radially oriented second air inlet ports in circumferential arrangement at a second axial portion of the outer sleeve. The outer sleeve further defines a first fluid passage arranged between each first air inlet port and extended from the end wall. A fluid passage wall extends from the end wall within the first fluid passage to define a second fluid passage extended from the end wall within the first fluid passage. The outer sleeve further defines a first injection port in fluid communication with the first fluid passage and a second injection port in fluid communication with the second fluid passage. The thermal management conduit is defined by the fluid communication of the fluid conduit and the first fluid passage and the thermal communication of the second fluid passage in adjacent arrangement with the first fluid passage.
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