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    DUAL-FUEL FUEL NOZZLE WITH GAS AND LIQUID FUEL CAPABILITY
    1.
    发明申请
    DUAL-FUEL FUEL NOZZLE WITH GAS AND LIQUID FUEL CAPABILITY 审中-公开

    公开(公告)号：US20180363911A1

    公开(公告)日：2018-12-20

    申请号：US15626387

    申请日：2017-06-19

    Applicant: General Electric Company

    Inventor： Kaitlin Marie Graham ,  Thomas Edward Johnson ,  Geoffrey David Myers

    IPC: F23R3/36 ,  F02C7/22 ,  F23R3/28

    Abstract: The present disclosure is directed to a fuel nozzle including a center body having a tube shape and a ring manifold disposed at an aft end of the center body. The fuel nozzle also includes an inner tube extending axially through the ring manifold and disposed within the center body. The inner tube is in fluid communication with a diluent supply. The fuel nozzle further includes a fuel tube extending helically around a portion of the inner tube. The fuel tube fluidly couples a fuel plenum of the ring manifold to a liquid fuel supply. Furthermore, the fuel nozzle includes a plurality of fuel injectors circumferentially spaced within an outer band of the ring manifold and in fluid communication with the fuel plenum. Each fuel injector is oriented to direct atomized liquid fuel radially outward from the center body. The ring manifold and the inner tube are thermally decoupled.

    GAS TURBINE BURNER
    3.
    发明申请
    GAS TURBINE BURNER 有权
    燃气涡轮燃烧器

    公开(公告)号：US20140123652A1

    公开(公告)日：2014-05-08

    申请号：US14081062

    申请日：2013-11-15

    Applicant: General Electric Company

    Inventor： Jesse Blair Butler ,  David Leach ,  Kevin Weston McMahan ,  Mark Allan Hadley ,  Geoffrey David Myers

    IPC: F23R3/28 ,  F23R3/14

    CPC classification number: F23R3/286 ,  F23C2900/07001 ,  F23D2900/14004 ,  F23D2900/14701 ,  F23R3/14

    Abstract: A gas turbine includes a compressor and at least one combustor downstream from the compressor. The combustor includes a burner having an inner shroud extending axially along at least a portion of the burner, an outer shroud radially separated from the inner shroud and extending axially along at least a portion of the burner, and a plurality of stator vanes extending radially between the inner shroud and the outer shroud. The stator vanes have an inner end proximate the inner shroud and an outer end proximate the outer shroud. The burner further includes a vortex tip at one of either the inner end or the outer end of the stator vanes. The vortex tip provides a gap between the inner end and the inner shroud or the outer end and the outer shroud, and the vortex tip includes a plurality of fuel ports. The gas turbine further includes a turbine downstream from the combustor.

    Abstract translation: 燃气轮机包括压缩机和至少一个在压缩机下游的燃烧器。 所述燃烧器包括燃烧器，所述燃烧器具有沿所述燃烧器的至少一部分轴向延伸的内罩，所述外护罩与所述内护罩径向分离并且沿着所述燃烧器的至少一部分轴向延伸;以及多个定子叶片， 内护罩和外护罩。 定子叶片具有靠近内护罩的内端和靠近外护罩的外端。 燃烧器还包括在定子叶片的内端或外端之一处的涡流尖端。 涡流尖端在内端和内护罩或外端和外护罩之间提供间隙，并且涡流尖端包括多个燃料口。 燃气轮机还包括从燃烧器下游的涡轮机。

    Dual-fuel fuel nozzle with gas and liquid fuel capability
    5.
    发明授权
    Dual-fuel fuel nozzle with gas and liquid fuel capability 有权

    公开(公告)号：US10663171B2

    公开(公告)日：2020-05-26

    申请号：US15626435

    申请日：2017-06-19

    Applicant: General Electric Company

    Inventor： Kaitlin Marie Graham ,  Thomas Edward Johnson ,  Geoffrey David Myers

    IPC: F23R3/28 ,  F23R3/34 ,  F23R3/36 ,  F23D17/00 ,  F23D11/38 ,  F23D14/02

    Abstract: The present disclosure is directed to a dual-fuel fuel nozzle that includes a center body having a tube shape and a gas fuel plenum defined within the center body. The duel-fuel fuel nozzle also includes a ring manifold defining a liquid fuel plenum disposed within the center body. The duel-fuel fuel nozzle further includes a plurality of radially oriented fuel injectors in fluid communication with the liquid fuel plenum. Additionally, the duel-fuel fuel nozzle includes an inner fuel tube extending axially within the center body. A portion of the inner fuel tube extends helically about an axial centerline of the center body. The inner fuel tube is in fluid communication with an axially oriented fuel injector. Furthermore, the duel-fuel fuel nozzle includes first fuel tube extending helically around a portion of the inner fuel tube within the center body. The first fuel tube is fluidly coupled to the fuel plenum.

    Pre-film liquid fuel cartridge
    6.
    发明授权
    Pre-film liquid fuel cartridge 有权

    公开(公告)号：US10508812B2

    公开(公告)日：2019-12-17

    申请号：US15303544

    申请日：2014-05-12

    Applicant: General Electric Company

    Inventor： Geoffrey David Myers ,  Borys Borysovych Shershnyov ,  Alexey Yurievich Gerasimov

    IPC: F23R3/28 ,  F23R3/34

    Abstract: A pre-film liquid fuel cartridge (20) includes a primary liquid fuel passage (106), a plurality of inner fuel ports (116) and a plurality of outer fuel ports (124) that are in fluid communication with the primary liquid fuel passage. An inner pre-filming surface (142) is defined downstream from the plurality of inner fuel ports. The inner pre-filming surface (142) terminates at a first shear edge (140). An outer pre-filming surface (152) is defined downstream from the plurality of outer fuel ports. The outer pre-filming surface (152) terminates at a second shear edge (154). The first and second shear edges are relatively oriented so that a first pre-filmed liquid fuel sheet exiting the first shear edge intersects with a second pre-filmed liquid fuel sheet exiting the second shear edge, thereby atomizing the first and second pre-filmed liquid fuel sheets.

    NOZZLE ASSEMBLY FOR A DUAL-FUEL FUEL NOZZLE
    7.
    发明申请
    NOZZLE ASSEMBLY FOR A DUAL-FUEL FUEL NOZZLE 审中-公开

    公开(公告)号：US20180363912A1

    公开(公告)日：2018-12-20

    申请号：US15626461

    申请日：2017-06-19

    Applicant: General Electric Company

    Inventor： Kaitlin Marie Graham ,  Thomas Edward Johnson ,  Geoffrey David Myers

    IPC: F23R3/36 ,  F02C7/22

    Abstract: The present disclosure is directed to a nozzle assembly including a header manifold and a ring manifold, which defines a liquid fuel plenum, spaced from the header manifold. An outer sleeve connects to the ring manifold, and a nozzle body connects to the outer sleeve. The ring manifold, the outer sleeve, and the nozzle body define a fluid chamber. An inner fuel tube extends from the header manifold to the nozzle body. A portion of the inner fuel tube extends helically about an axial centerline of the nozzle assembly between the ring manifold and the nozzle body. A first fuel tube extends helically around a portion of the inner fuel tube. The first fuel tube fluidly couples the liquid fuel plenum to the header manifold. A second fuel tube extends helically around a portion of the inner fuel tube and fluidly couples the liquid fuel plenum to the header manifold.

    AERODYNAMIC FASTENING OF TURBOMACHINE FUEL INJECTORS
    8.
    发明申请
    AERODYNAMIC FASTENING OF TURBOMACHINE FUEL INJECTORS 审中-公开

    公开(公告)号：US20180363909A1

    公开(公告)日：2018-12-20

    申请号：US15626783

    申请日：2017-06-19

    Applicant: General Electric Company

    Inventor： Thomas Edward Johnson ,  Kaitlin Marie Graham ,  Geoffrey David Myers

    IPC: F23R3/28 ,  F02C9/26 ,  F02M61/14 ,  F02M61/18

    Abstract: A premixing fuel nozzle assembly for a turbomachine is disclosed as having at least one fuel injector with an outer jacket having a first end and a second end and a threaded surface disposed therebetween. The first end has a cylindrical sealing surface and the second end has at least one wrenching pocket. An annular hub is disclosed as having an aperture with a first end and a second end and a threaded surface disposed therebetween, wherein the aperture is configured to at least partially house the fuel injector therein and the annular hub further has a conical seat about the first end. The fuel injector cylindrical sealing surface swages inward to form a hermetic seal when contacting the annular hub conical seat as the fuel injector is threaded into the aperture.

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