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    Method and apparatus to decrease combustor emissions
    4.
    发明公开
    Method and apparatus to decrease combustor emissions 有权
    用于从燃烧室减少排放的方法和装置

    公开(公告)号：EP1426690A3

    公开(公告)日：2010-08-25

    申请号：EP03257562.3

    申请日：2003-12-02

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Held, Timothy James ,  Xu, Jun ,  Mueller, Mark Anthony

    IPC: F23R3/28 ,  F23R3/14 ,  F23R3/34

    CPC classification number: F23R3/286 ,  F23R3/14 ,  F23R3/343

    Abstract: A combustor (16) for a gas turbine includes a combustion chamber (50), a pilot mixer (42) including a pilot centerbody (54) and at least one axial air swirler (60) that is radially outward from and concentrically mounted with respect to the pilot centerbody. The pilot mixer is upstream from the combustion chamber. A main mixer (44) is radially outward from and is concentrically aligned with respect to the pilot mixer. The main mixer includes at least one swirler (140) that is configured to inject fuel therethrough into the main mixer. The main mixer is upstream from the combustion chamber. An annular centerbody (106) extends between the pilot mixer and the main mixer. The centerbody includes a radially inner surface (102) and a radially outer surface (104). The radially inner surface includes at least one of a divergent portion and a convergent portion.

    Methods and apparatus for reducing gas turbine engine emissions
    5.
    发明公开
    Methods and apparatus for reducing gas turbine engine emissions 审中-公开
    用于减少燃气涡轮发动机的排放的方法和装置

    公开(公告)号：EP1632716A1

    公开(公告)日：2006-03-08

    申请号：EP05255347.6

    申请日：2005-09-01

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Fortuna, Douglas Marti ,  Held, Timothy James ,  Kastrup, David Allen

    IPC: F23D11/24 ,  F23D11/38 ,  F23D17/00 ,  F23L7/00 ,  F23R3/36

    CPC classification number: F23L7/002 ,  F23D11/24 ,  F23D17/002 ,  F23R3/36

    Abstract: A fuel nozzle (50) for a gas turbine engine, including a first injection circuit (82) including an annular discharge opening (94), the first injection circuit for injecting liquid fuel downstream from the nozzle into the gas turbine engine; a second injection circuit (84) aligned substantially concentrically with respect to the first injection circuit; and a third injection circuit (86) aligned substantially concentrically with respect to the first injection circuit, the second injection circuit is between the second and third injection circuits, one of the second and third injection circuits for injecting water downstream from the nozzle into the gas turbine engine, one of the second injection circuit and the third injection circuit comprising an annular discharge opening (132).

    Abstract translation: 一种燃料喷嘴（50），一种用于燃气涡轮发动机，其包括第一注入回路（82）包括在环形排放开口（94），用于喷射从喷嘴到燃气涡轮发动机下游液体燃料的第一注入回路; 相对于所述第一注入回路对准的大致同心的第二注入回路（84）; 和相对于所述第一注入回路对准的大致同心的第三注入回路（86），第二注入回路是在第二和第三注入电路之间，用于从所述喷嘴下游将水注入气体的第二和第三次注射电路中的一个 涡轮发动机中，在第二次注射电路和第三注入电路，其包括环形的设计排出开口（132）中的一个。

    Methods and apparatus to facilitate decreasing combustor acoustics
    8.
    发明公开
    Methods and apparatus to facilitate decreasing combustor acoustics 有权
    一种用于促进燃烧振动的下降装置

    公开(公告)号：EP1909030A2

    公开(公告)日：2008-04-09

    申请号：EP07117177.1

    申请日：2007-09-25

    Applicant: General Electric Company

    Inventor： Mueller, Mark Anthony ,  Held, Timothy James ,  Kelsey, Mark Patrick

    IPC: F23R3/28 ,  F23R3/34

    CPC classification number: F23R3/286 ,  F23R3/343 ,  F23R2900/00014 ,  F23R2900/03343

    Abstract: A combustion system (20) is provided. The combustion system includes a pilot swirler (210), and a main swirler (230) coupled to the pilot swirler such that the main swirler substantially circumscribes the pilot swirler. The main swirler includes a first set of swirler vanes (240) for inducing swirling to fuel supplied to a first fuel circuit defined in the main swirler, each of the first set of swirler vanes includes at least one first fuel passage (242) defined therein, a second set of swirler vanes for inducing swirling to fuel supplied to a second fuel circuit defined in the main swirler, each of the second set of swirler vanes includes at least one second fuel passage (248) defined therein, and a shroud (260) coupled in flow communication to at least one of the first set of swirler vanes and the second set of swirler vanes, the shroud including at least one third fuel passage (262) defined therein.

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