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    Combustor for Use in a Turbine Engine
    11.
    发明申请
    Combustor for Use in a Turbine Engine 审中-公开

    公开(公告)号：US20180252410A1

    公开(公告)日：2018-09-06

    申请号：US15447847

    申请日：2017-03-02

    申请人： General Electric Company

    发明人： Joseph Zelina ,  Sarah Marie Monahan ,  Michael Anthony Benjamin ,  Venkat Eswarlu Tangirala ,  Sibtosh Pal ,  William Thomas Ross

    IPC分类号： F23R3/06 ,  F23R3/00 ,  F23R3/42

    摘要： A combustor for a turbine engine includes an inner combustion liner and an outer combustion liner together defining at least in part an interior. The interior includes a combustion chamber and a main portion. The combustor also includes an inlet combustion liner at least partially defining the combustion chamber of the interior and including an inlet assembly. The inlet assembly includes at least two cavity air tubes arranged along the axial direction, each cavity air tube extending between an inlet and an outlet, the outlet of each cavity air tube in airflow communication with the combustion chamber for providing the combustion chamber with a flow of air.

    CAVITY STAGING IN A COMBUSTOR
    12.
    发明申请
    CAVITY STAGING IN A COMBUSTOR 审中-公开
    在一个COMBUSTOR的CAVITY STAGING

    公开(公告)号：US20170009993A1

    公开(公告)日：2017-01-12

    申请号：US14791684

    申请日：2015-07-06

    申请人： General Electric Company

    发明人： Sarah Marie Monahan ,  Narendra Digamber Joshi ,  Venkat Eswarlu Tangirala ,  Matthieu Marc Masquelet

    IPC分类号： F23R3/28 ,  F23R3/34

    CPC分类号： F23R3/286 ,  F05D2240/35 ,  F23C5/00 ,  F23C5/08 ,  F23C5/10 ,  F23C5/24 ,  F23C5/32 ,  F23R3/02 ,  F23R3/04 ,  F23R3/045 ,  F23R3/06 ,  F23R3/10 ,  F23R3/12 ,  F23R3/34 ,  F23R3/346 ,  F23R3/42 ,  F23R3/58 ,  F23R2900/00015 ,  F23R2900/03041 ,  F23R2900/03042 ,  Y02T50/675

    摘要： A combustor assembly including a combustor liner defining therein a combustion chamber for the downstream flow of a main fluid. At least two annular trapped vortex cavities are located on the combustor liner and staged axially spaced apart. A cavity opening is located at a radially inner end of each of the at least two annular trapped vortex cavities spaced apart from a radially outer wall and extending between an aft wall and a forward wall of each cavity. A plurality of injectors are configured tangentially relative to the circular radially outer wall to provide for an injection of air and fuel to form an annular rotating trapped vortex of a fuel and air mixture within a respective annular trapped vortex cavity. The annular rotating trapped vortex of the fuel and air mixture at the cavity openings is substantially perpendicular to the downstream flow of the main fluid. A gas turbine engine including the combustor assembly is disclosed.

    摘要翻译： 一种燃烧器组件，其包括在其中限定用于主流体的下游流动的燃烧室的燃烧器衬套。 至少两个环形的被捕获的涡流腔位于燃烧器衬套上并且沿轴向间隔分开。 空腔开口位于与径向外壁间隔开并在每个空腔的后壁和前壁之间延伸的至少两个环形捕获涡流腔中的每一个的径向内端。 多个喷射器相对于圆形径向外壁切向配置，以提供空气和燃料的喷射，以在相应的环形捕获的涡流空腔内形成燃料和空气混合物的环形旋转捕获涡流。 空腔开口处的燃料和空气混合物的环形旋转捕获的涡流基本上垂直于主流体的下游流动。 公开了一种包括燃烧器组件的燃气涡轮发动机。

    AIR-SHIELDED FUEL INJECTION ASSEMBLY TO FACILITATE REDUCED NOX EMISSIONS IN A COMBUSTOR SYSTEM
    13.
    发明申请
    AIR-SHIELDED FUEL INJECTION ASSEMBLY TO FACILITATE REDUCED NOX EMISSIONS IN A COMBUSTOR SYSTEM 审中-公开
    空气燃料燃料注入装置，以帮助减少排放系统中的NOx排放

    公开(公告)号：US20160363319A1

    公开(公告)日：2016-12-15

    申请号：US14461069

    申请日：2014-08-15

    申请人： General Electric Company

    发明人： Sarah Marie Monahan ,  Joel Meier Haynes ,  Narendra Digamber Joshi ,  David James Walker ,  Junwoo Lim ,  Krishna Kumar Venkatesan

    IPC分类号： F23R3/28 ,  F23R3/00 ,  F02C3/04 ,  F02C7/22

    CPC分类号： F23R3/286 ,  F02C7/222 ,  F05D2240/35 ,  F05D2240/36 ,  F23D14/64 ,  F23D2206/10 ,  F23D2900/11002

    摘要： An air-shielded fuel injection assembly for use in a combustion chamber of a turbine assembly. The air-shielded fuel injection assembly generally includes a fuel manifold including a plurality of fuel injection ports and an air manifold including a plurality of air injection ports. Each of the plurality of fuel injection ports is configured to introduce a fuel column into an annular cavity of a mixer assembly. Each of the plurality of air injection ports is configured to introduce an air curtain about an associated fuel injection column to minimize recirculation upstream of the fuel injection column and increase penetration of the fuel injection column into the cavity. Also disclosed are a mixer assembly and a turbine assembly including the air-shielded fuel injection assembly.

    摘要翻译： 一种用于涡轮机组件的燃烧室中的空气屏蔽燃料喷射组件。 空气屏蔽燃料喷射组件通常包括包括多个燃料喷射端口的燃料歧管和包括多个空气喷射端口的空气歧管。 多个燃料喷射口中的每一个构造成将燃料柱引入混合器组件的环形腔中。 多个空气喷射端口中的每一个构造成围绕相关联的燃料喷射塔引入空气幕，以使燃料喷射塔的上游的再循环最小化并且增加燃料喷射塔到空腔中的穿透。 还公开了一种混合器组件和包括空气屏蔽燃料喷射组件的涡轮组件。

    Fuel staging for rotating detonation combustor
    15.
    发明授权
    Fuel staging for rotating detonation combustor 有权

    公开(公告)号：US11236908B2

    公开(公告)日：2022-02-01

    申请号：US16169645

    申请日：2018-10-24

    申请人： General Electric Company

    发明人： Andrew Joseph Wickersham ,  Sarah Marie Monahan ,  Thomas Michael Lavertu ,  Kapil Kumar Singh

    IPC分类号： F23R7/00 ,  F23R3/34

    摘要： A combustion system includes an annular tube disposed between an inner wall and an outer wall, the annular tube extending from an inlet end to an outlet end; at least one fluid inlet disposed in the annular tube proximate the inlet end, the fluid inlet providing a conduit through which fluid flows into the annular tube; at least one outlet disposed in the annular tube proximate the outlet end; at least one primary fuel injector, the primary fuel injector dispersing fuel into a fluid stream entering the annular tube via the fluid inlet; and at least one secondary fuel injector, the secondary fuel injector disposed in the annular tube.

    COMBUSTOR FOR USE IN A TURBINE ENGINE
    18.
    发明申请
    COMBUSTOR FOR USE IN A TURBINE ENGINE 审中-公开

    公开(公告)号：US20180187888A1

    公开(公告)日：2018-07-05

    申请号：US15398496

    申请日：2017-01-04

    申请人： General Electric Company

    发明人： Venkat Eswarlu Tangirala ,  Narendra Digamber Joshi ,  Sarah Marie Monahan

    IPC分类号： F23R3/00 ,  F02C3/04

    CPC分类号： F23R3/002 ,  F23R3/06 ,  F23R3/58 ,  F23R2900/03042

    摘要： A combustor for use in a turbine engine that includes an inner combustion liner and an outer combustion liner. An interior is defined between the inner combustion liner and the outer combustion liner, and the interior includes a cavity portion and a main portion extending radially inward from the cavity portion. The cavity portion includes a flow inlet and the main portion includes a flow outlet. A plurality of film cooling holes are formed in at least one of the inner combustion liner and the outer combustion liner. The plurality of film cooling holes are configured such that cooling airflow discharged therefrom flows helically relative to a centerline of the turbine engine and towards the flow outlet.

    COMBUSTOR ASSEMBLY FOR USE IN A GAS TURBINE ENGINE AND METHOD OF ASSEMBLING
    19.
    发明申请
    COMBUSTOR ASSEMBLY FOR USE IN A GAS TURBINE ENGINE AND METHOD OF ASSEMBLING 审中-公开
    用于燃气涡轮发动机的燃烧器组件和组装方法

    公开(公告)号：US20170016620A1

    公开(公告)日：2017-01-19

    申请号：US14801962

    申请日：2015-07-17

    申请人： General Electric Company

    发明人： Matthieu Marc Masquelet ,  Narendra Digamber Joshi ,  Venkat Eswarlu Tangirala ,  Sarah Marie Monahan

    IPC分类号： F23R3/00 ,  F23R3/28

    摘要： A combustor assembly for use in a gas turbine engine is provided. The combustor assembly includes a dome assembly, a fuel nozzle coupled to the dome assembly, and a cowl assembly. The cowl assembly includes a radially inner cowl coupled to the dome assembly, and a radially outer cowl including a first cowl member and a second cowl member each positioned about the fuel nozzle. The first and second cowl members substantially align to define a substantially continuous flow path configured to direct a flow of air about the dome assembly.

    摘要翻译： 提供了一种用于燃气涡轮发动机的燃烧器组件。 燃烧器组件包括圆顶组件，联接到圆顶组件的燃料喷嘴和整流罩组件。 整流罩组件包括联接到圆顶组件的径向内部整流罩，以及包括第一整流罩构件和每个围绕燃料喷嘴定位的第二整流罩构件的径向外罩。 第一和第二整流罩构件基本上对准以限定基本上连续的流动路径，其构造成引导围绕圆顶组件的空气流。

    CORRUGATED CYCLONE MIXER ASSEMBLY TO FACILITATE REDUCED NOX EMISSIONS AND IMPROVE OPERABILITY IN A COMBUSTOR SYSTEM
    20.
    发明申请
    CORRUGATED CYCLONE MIXER ASSEMBLY TO FACILITATE REDUCED NOX EMISSIONS AND IMPROVE OPERABILITY IN A COMBUSTOR SYSTEM 审中-公开
    腐蚀性气旋混合器组装，以减少NOx排放并提高COMBUSTOR系统的可操作性

    公开(公告)号：US20160061452A1

    公开(公告)日：2016-03-03

    申请号：US14469029

    申请日：2014-08-26

    申请人： General Electric Company

    发明人： David James Walker ,  Joel Meier Haynes ,  Narendra Digamber Joshi ,  Junwoo Lim ,  Krishna Kumar Venkatesan ,  Sarah Marie Monahan

    IPC分类号： F23R3/28

    摘要： A corrugated cyclone mixer for use in a fuel injection assembly of a turbine engine. The corrugated cyclone mixer generally includes an annular housing including a flange portion and a lip portion configured downstream of the flange portion. The mixer further including a swirler disposed therein the annular housing for inducing a cyclonic motion in the corrugated cyclone mixer. The swirler is configured upstream of the flange portion and including a plurality of swirler vanes to produce a swirling air flow. The lip portion forming an outlet downstream of the swirler and including a plurality of corrugations at an aft end. The plurality of corrugations are configured to mix the swirling air flow and an injected fuel stream flowing therethrough the corrugated cyclone mixer. Additionally disclosed is a fuel injection assembly and a turbine assembly including the corrugated cyclone mixer.

    摘要翻译： 一种用于涡轮发动机的燃料喷射组件的波纹旋风混合器。 波纹旋风混合器通常包括环形壳体，其包括凸缘部分和配置在凸缘部分下游的唇部。 混合器还包括设置在其中的旋流器，用于在波纹旋风混合器中引起气旋运动。 旋流器构造在凸缘部分的上游并且包括多个旋流器叶片以产生旋转空气流。 所述唇部形成在所述旋流器下游的出口并且在后端处包括多个波纹。 多个波纹被配置成将旋转空气流和流经波纹旋风混合器的喷射燃料流混合。 另外公开了一种燃料喷射组件和包括波纹旋风混合器的涡轮组件。