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    BURNER FOR A GAS TURBINE
    1.
    发明申请
    BURNER FOR A GAS TURBINE 审中-公开

    公开(公告)号：US20180195723A1

    公开(公告)日：2018-07-12

    申请号：US15742151

    申请日：2016-06-10

    申请人： SIEMENS AKTIENGESELLSCHAFT

    发明人： Ghenadie BULAT

    IPC分类号： F23R3/14 ,  F23R3/28 ,  F23R3/20

    CPC分类号： F23R3/14 ,  F23D2900/14701 ,  F23R3/20 ,  F23R3/286

    摘要： A burner for a gas turbine engine has a combustion chamber and a swirler adapted to guide a swirler air flow to the combustion chamber, wherein the swirler has a first wall confining the swirler air flow as well as a second wall confining the swirler air flow on the same side as and downstream with respect to the swirler air flow from the first wall and being displaced with respect to the first wall in a direction away from the swirler air flow so that a step being able to cause a flow separation of the swirler air flow is formed by the first wall and the second wall, wherein the second wall has a through hole in its surface adapted to inject a liquid fuel into the swirler air flow.

    Burner
    2.
    发明授权
    Burner 有权

    公开(公告)号：US09982887B2

    公开(公告)日：2018-05-29

    申请号：US14922925

    申请日：2015-10-26

    申请人： WORGAS BRUCIATORI S.R.L.

    发明人： Gabriele Gangale

    IPC分类号： F23D14/02 ,  F23D14/14 ,  F23D14/58 ,  F23D14/70

    CPC分类号： F23D14/02 ,  F23D14/14 ,  F23D14/58 ,  F23D14/70 ,  F23D2900/14701

    摘要： A burner comprises a tubular diffuser wall and an inlet passage a flow of a mixture of gas within the diffuser wall, as well as a first diaphragm arranged in the inlet passage, said diaphragm forming a plurality of through openings and a plurality of guide surfaces delimiting the through openings on a radially outer side thereof so that, when introducing the mixture, said guide surfaces and said through openings direct the mixture towards the inside of the burner and in a radial direction towards the longitudinal axis.

    Gas-turbine burner having inflow guide means
    5.
    发明授权
    Gas-turbine burner having inflow guide means 有权
    具有流入引导装置的燃气轮机燃烧器

    公开(公告)号：US08973369B2

    公开(公告)日：2015-03-10

    申请号：US13715233

    申请日：2012-12-14

    申请人： Robert Angel ,  Drew Ehlert ,  Matthias Hase ,  Michael Huth ,  James Marshall ,  Yevgeniy Shteyman

    发明人： Robert Angel ,  Drew Ehlert ,  Matthias Hase ,  Michael Huth ,  James Marshall ,  Yevgeniy Shteyman

    IPC分类号： F02C1/00 ,  F02G3/00 ,  F23R3/14 ,  F23R3/28 ,  F23R3/34

    CPC分类号： F23R3/14 ,  F23D2900/00008 ,  F23D2900/14701 ,  F23R3/286 ,  F23R3/343

    摘要： A gas-turbine burner having a plurality of main swirl generators which each have an inlet flow opening formed by the main swirl generator edge is provided. In order to achieve a uniform flow of combustion air through the main swirl generator, the gas-turbine burner has an inlet-flow guide means with a flow guide surface which runs from one of the inlet-flow openings to an adjacent inlet-flow opening, to which the main swirl generator edges which form the inlet-flow openings are connected, and the flow guide surface widens from there radially upwards. The main swirl generators are central-symmetrically arranged around a pilot burner and the flow guide surface runs radially outside the main swirl generators.

    摘要翻译： 本发明提供一种燃气轮机燃烧器，其具有多个主漩涡发生器，每个主漩涡发生器具有由主漩涡发生器边缘形成的入口流动开口。 为了实现燃烧空气通过主漩涡发生器的均匀流动，燃气轮机燃烧器具有入口流动引导装置，其具有从一个入口流动开口延伸到相邻入口流动开口的流动引导表面 形成入口流动开口的主漩涡发生器边缘连接到其上，并且流动引导表面从那里径向向上变宽。 主涡旋发生器围绕引燃燃烧器中心对称地布置，并且流动引导表面径向地在主漩涡发生器外部延伸。

    GAS BURNER FOR A COOKTOP
    6.
    发明申请
    GAS BURNER FOR A COOKTOP 审中-公开
    燃烧器燃烧器COOKTOP

    公开(公告)号：US20150034070A1

    公开(公告)日：2015-02-05

    申请号：US14447057

    申请日：2014-07-30

    申请人： Electrolux Professional S.p.A.

    发明人： Stefano FOGOLIN ,  Denis MARSON

    IPC分类号： F24C3/08 ,  F23D14/06

    CPC分类号： F24C3/08 ,  F23D14/06 ,  F23D14/64 ,  F23D14/70 ,  F23D2900/14701

    摘要： A gas burner comprises a flame ring, a Venturi tube to feed said flame ring, and a gas injector having a nozzle with an orifice to inject a burnable gas in said Venturi tube to feed said flame ring, wherein a flow perturbation element is provided in a region between said orifice and a middle portion of said Venturi tube to impact the air-gas mixing.

    摘要翻译： 气体燃烧器包括火焰环，用于供给所述火焰环的文氏管，以及具有喷嘴的气体喷射器，所述喷嘴具有孔口，用于在所述文丘里管中喷射可燃气体以供给所述火焰环，其中在所述气体喷射器中设置流动扰动元件 所述孔和所述文丘里管的中间部分之间的区域，以冲击空气混合。

    MIXED FUEL VACUUM BURNER-REACTOR
    7.
    发明申请
    MIXED FUEL VACUUM BURNER-REACTOR 审中-公开
    混合燃料真空燃烧器 - 反应器

    公开(公告)号：US20140234787A1

    公开(公告)日：2014-08-21

    申请号：US13772075

    申请日：2013-02-20

    申请人： Jorge DE LA SOVERA

    发明人： Jorge DE LA SOVERA

    IPC分类号： F23G5/12 ,  F23G7/00 ,  F23C5/32 ,  F23C1/08 ,  F23C3/00

    CPC分类号： F23G5/12 ,  F23C1/08 ,  F23C3/00 ,  F23C5/32 ,  F23C6/042 ,  F23C2201/301 ,  F23D14/04 ,  F23D17/002 ,  F23D2900/14241 ,  F23D2900/14701 ,  F23G7/008 ,  F23L9/02

    摘要： A mixed-fuel vacuum burner-reactor includes a primary combustion chamber having a conical interior and a first set of directing blades. The conical interior is connected to an intake manifold on one end and a reduction nozzle on the other end. Injectors are mounted perpendicularly to the reduction nozzle to inject a second fuel into the primary combustion chamber. The reduction nozzle is connected to a cylindrical secondary combustion chamber having a second set of directing blades configured to direct air into the secondary combustion chamber. Methods of efficiently burning mixed fuels in a triple-vortex vacuum burner-reactor are also disclosed. Vacuum conditions are created and fuels are introduced into a conical primary combustion chamber. The fuels are passed over a first set of directing blades to form three vortices before additional fuels are injected in a direction opposite to a direction of rotation of the first set of fuels.

    摘要翻译： 混合燃料真空燃烧器 - 反应器包括具有锥形内部的第一燃烧室和第一组引导叶片。 锥形内部连接到一端的进气歧管和另一端的减压喷嘴。 喷射器垂直于减压喷嘴安装，以将第二燃料喷射到主燃烧室中。 还原喷嘴连接到具有构造成将空气引导到二次燃烧室中的第二组引导叶片的圆柱形二次燃烧室。 还公开了在三涡流真空燃烧器 - 反应器中有效燃烧混合燃料的方法。 产生真空条件并将燃料引入锥形初级燃烧室。 在另外的燃料以与第一组燃料的旋转方向相反的方向喷射燃料之前，燃料通过第一组引导叶片形成三个涡流。

    GAS TURBINE BURNER
    9.
    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

    申请人： General Electric Company

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

    IPC分类号： F23R3/28 ,  F23R3/14

    CPC分类号： F23R3/286 ,  F23C2900/07001 ,  F23D2900/14004 ,  F23D2900/14701 ,  F23R3/14

    摘要： 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.

    摘要翻译： 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。

    TURBINE COMBUSTOR SYSTEM HAVING AERODYNAMIC FEED CAP
    10.
    发明申请
    TURBINE COMBUSTOR SYSTEM HAVING AERODYNAMIC FEED CAP 有权
    具有气动进给盖的涡轮机系统

    公开(公告)号：US20130269350A1

    公开(公告)日：2013-10-17

    申请号：US13448283

    申请日：2012-04-16

    申请人： Abdul Rafey Khan ,  Bradley Donald Crawley ,  Robert Joseph Rohrssen ,  Mohan Krishna Bobba

    发明人： Abdul Rafey Khan ,  Bradley Donald Crawley ,  Robert Joseph Rohrssen ,  Mohan Krishna Bobba

    IPC分类号： F23R3/10 ,  F23R3/26 ,  F23R3/28 ,  F23R3/16

    CPC分类号： F23R3/286 ,  F23D14/64 ,  F23D2209/10 ,  F23D2900/14021 ,  F23D2900/14701

    摘要： Present embodiments are directed toward reducing low flow or no flow situations in a head end of a turbine combustor. Embodiments include a system having a turbine combustor. The turbine combustor includes a fuel nozzle having an inner shell and an outer shell, and a feed cap disposed about the fuel nozzle and having an outer wall and a back plate. The back plate joins respective upstream ends of the outer shell of the fuel nozzle and the outer wall of the feed cap. The turbine combustor is configured to flow a first pressurized air via an air path extending along the outer wall of the feed cap, the back plate of the feed cap, and into the fuel nozzle.

    摘要翻译： 本发明的实施例旨在减少涡轮机燃烧器的头端中的低流量或不流动情况。 实施例包括具有涡轮机燃烧器的系统。 涡轮机燃烧器包括具有内壳和外壳的燃料喷嘴和设置在燃料喷嘴周围并且具有外壁和后板的进料盖。 背板连接燃料喷嘴的外壳的各个上游端和进料盖的外壁。 涡轮机燃烧器构造成使第一加压空气经由沿进料盖的外壁，进料盖的后板延伸并进入燃料喷嘴的空气路径。