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    AXIALLY ORIENTED INTERNALLY MOUNTED CONTINUOUS IGNITION DEVICE: REVERSE FLOW AXIAL ORIENTATION
    2.
    发明申请
    AXIALLY ORIENTED INTERNALLY MOUNTED CONTINUOUS IGNITION DEVICE: REVERSE FLOW AXIAL ORIENTATION 有权

    公开(公告)号：US20220195935A1

    公开(公告)日：2022-06-23

    申请号：US17125107

    申请日：2020-12-17

    Applicant: Delavan Inc.

    Inventor： Jason Ryon ,  Lev Alexander Prociw ,  Brandon P. Williams

    IPC: F02C7/264 ,  F02C7/22 ,  F23R3/28 ,  F23R3/42

    Abstract: An embodiment of a combustor for a gas turbine engine includes a combustor case, a combustor liner disposed within the combustor case, a fuel nozzle, and a torch igniter within the combustor case. The torch igniter includes a combustion chamber, a cap defining the upstream end of the combustion chamber, a tip defining the downstream end of the combustion chamber, an annular igniter wall extending from the cap to the tip and defining a radial extent of the combustion chamber, a structural wall coaxial with and surrounding the igniter wall, and an outlet passage within the tip that fluidly connects the combustion chamber to the combustor. The tip is mounted through the combustor liner, the cap is downstream of the tip, and the torch igniter is downstream of the fuel nozzle and disposed radially between the combustor liner and the combustor case.

    FUEL SYSTEMS FOR TORCH IGNITION DEVICES
    3.
    发明申请
    FUEL SYSTEMS FOR TORCH IGNITION DEVICES 有权

    公开(公告)号：US20220154932A1

    公开(公告)日：2022-05-19

    申请号：US16951631

    申请日：2020-11-18

    Applicant: Delavan Inc.

    Inventor： Jason Ryon ,  Lev Alexander Prociw ,  Brandon P. Williams

    IPC: F23R3/36 ,  F02C7/266 ,  F02C9/40

    Abstract: A torch igniter system for a combustor of a gas turbine engine includes a housing defining a combustion chamber, an ignition source disposed at least partially in the combustion chamber, a fuel injector, a first fluid path connecting a first fuel source to the fuel injector, a second fluid path connecting an air source to the fuel injector, and a third fluid path connecting a second fuel source to the combustion chamber. The fuel injector is configured to inject fuel, air, or a mixture of fuel and air into the combustion chamber and to impinge on the ignition source.

    Fuel systems for torch ignition devices
    5.
    发明授权
    Fuel systems for torch ignition devices 有权

    公开(公告)号：US11635027B2

    公开(公告)日：2023-04-25

    申请号：US16951631

    申请日：2020-11-18

    Applicant: Delavan Inc.

    Inventor： Jason Ryon ,  Lev Alexander Prociw ,  Brandon P. Williams

    IPC: F02C7/264 ,  F23R3/36 ,  F02P21/00 ,  F23Q9/00 ,  F02C7/266

    Abstract: A torch igniter system for a combustor of a gas turbine engine includes a housing defining a combustion chamber, an ignition source disposed at least partially in the combustion chamber, a fuel injector, a first fluid path connecting a first fuel source to the fuel injector, a second fluid path connecting an air source to the fuel injector, and a third fluid path connecting a second fuel source to the combustion chamber. The fuel injector is configured to inject fuel, air, or a mixture of fuel and air into the combustion chamber and to impinge on the ignition source.

    RADIALLY ORIENTED INTERNALLY MOUNTED CONTINUOUS IGNITION DEVICE
    6.
    发明申请
    RADIALLY ORIENTED INTERNALLY MOUNTED CONTINUOUS IGNITION DEVICE 有权

    公开(公告)号：US20220195933A1

    公开(公告)日：2022-06-23

    申请号：US17125072

    申请日：2020-12-17

    Applicant: Delavan Inc.

    Inventor： Jason Ryon ,  Brandon P. Williams ,  Lev Alexander Prociw

    IPC: F02C7/264 ,  F02C7/232 ,  F23R3/00

    Abstract: An embodiment of a combustor for a gas turbine engine includes a combustor case, a combustor liner disposed within the combustor case, a fuel nozzle, and a torch igniter within the combustor case. The torch igniter includes a combustion chamber, a cap defining the upstream end of the combustion chamber and configured to receive a fuel injector and a surface igniter, a tip defining the downstream end of the combustion chamber, an annular igniter wall extending from the cap to the tip and defining a radial extent of the combustion chamber, a structural wall coaxial with and surrounding the igniter wall, and an outlet passage within the tip that fluidly connects the combustion chamber to the combustor. The torch igniter is situated such that the tip is mounted through the combustor liner, the combustion chamber is within the combustor case, and the cap extends through the combustor case.

    LEAN BURN INJECTORS HAVING MULTIPLE PILOT CIRCUITS
    8.
    发明申请
    LEAN BURN INJECTORS HAVING MULTIPLE PILOT CIRCUITS 有权
    AN AN。。。。。。。。。。。。。。。。。。。

    公开(公告)号：US20140041390A1

    公开(公告)日：2014-02-13

    申请号：US14057511

    申请日：2013-10-18

    Applicant: Delavan Inc.

    Inventor： Brandon P. Williams ,  Jeremy T. Rhyan

    IPC: F23R3/28

    CPC classification number: F23R3/286 ,  F23D2900/00015 ,  F23R3/343

    Abstract: A fuel injector for a gas turbine engine includes a nozzle body defining a central axis and having a main fuel circuit. An air circuit is formed within the nozzle body inboard of the main fuel circuit. A primary pilot fuel circuit is formed within the nozzle body inboard of the air circuit. A secondary pilot fuel circuit is formed within the nozzle body inboard of the air circuit and outboard of the primary pilot fuel circuit.

    Abstract translation: 一种用于燃气涡轮发动机的燃料喷射器包括限定中心轴线并具有主燃料回路的喷嘴体。 在主燃料回路内的喷嘴体内部形成有空气回路。 在空气回路的内部的喷嘴体内形成有主要的先导燃料回路。 二次引燃燃料电路形成在空气回路内部的喷嘴体内部和主导向燃料回路外侧。

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