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    Combustor mixer purge cooling structure
    4.
    发明授权
    Combustor mixer purge cooling structure 有权

    公开(公告)号：US10801726B2

    公开(公告)日：2020-10-13

    申请号：US15710921

    申请日：2017-09-21

    Applicant: General Electric Company

    Inventor： Eric John Stevens ,  Allen Michael Danis ,  Ravi Chandra ,  Jayanth Sekar ,  Perumallu Vukanti

    IPC: F23R3/28 ,  F23R3/14 ,  F23D11/38 ,  F23D11/00 ,  F23R3/50 ,  F23R3/04

    Abstract: The present disclosure is directed to a combustor assembly for a gas turbine engine. The combustor assembly includes a deflector wall, an annular axial wall, and an annular shroud. The deflector wall is extended at least partially along a radial direction and a circumferential direction relative to an axial centerline and adjacent to a combustion chamber. A fuel nozzle opening is defined through the deflector wall, and a nozzle centerline is extended through the fuel nozzle opening along a lengthwise direction. The annular axial wall is coupled to the deflector wall and extended through the fuel nozzle opening. The axial wall is defined around the nozzle centerline. The annular shroud is defined around the nozzle centerline and extended co-directional to the axial wall. The axial wall and the annular shroud are each coupled to a radial wall defined upstream of the deflector wall. The annular shroud, the axial wall, and the radial wall together define a cooling plenum therebetween. The axial wall defines a discrete inlet opening therethrough providing fluid communication from a diffuser cavity to the cooling plenum. The cooling plenum defines an exit opening providing fluid communication from the cooling plenum to the combustion chamber.

    Combustor assembly for a turbine engine
    5.
    发明授权
    Combustor assembly for a turbine engine 有权

    公开(公告)号：US11022313B2

    公开(公告)日：2021-06-01

    申请号：US15189061

    申请日：2016-06-22

    Applicant: General Electric Company

    Inventor： Gregory Allen Boardman ,  Pradeep Naik ,  Allen Michael Danis

    IPC: F23R3/28 ,  F02C3/04 ,  F02C7/12 ,  F02C7/22 ,  F23R3/00 ,  F23R3/06

    Abstract: A rich-quench-lean combustor assembly for a gas turbine engine includes a liner extending between a forward end and an aft end. The liner includes a plurality of quench air jets positioned between the forward end and the aft end. The combustor assembly additionally includes a dome attached to or formed integrally with the liner, the dome and the liner together defining at least in part a combustion chamber. A fuel nozzle is attached to the dome, the fuel nozzle configured as a premix fuel nozzle for providing a substantially homogenous mixture of fuel and air to the combustion chamber, the mixture of fuel and air having an equivalence ratio of at least 1.5.

    COMBUSTOR MIXER PURGE COOLING STRUCTURE
    6.
    发明申请
    COMBUSTOR MIXER PURGE COOLING STRUCTURE 审中-公开

    公开(公告)号：US20190086088A1

    公开(公告)日：2019-03-21

    申请号：US15710921

    申请日：2017-09-21

    Applicant: General Electric Company

    Inventor： Eric John Stevens ,  Allen Michael Danis ,  Ravi Chandra ,  Jayanth Sekar ,  Perumallu Vukanti

    IPC: F23R3/14 ,  F23R3/28 ,  F23D11/38

    Abstract: The present disclosure is directed to a combustor assembly for a gas turbine engine. The combustor assembly includes a deflector wall, an annular axial wall, and an annular shroud. The deflector wall is extended at least partially along a radial direction and a circumferential direction relative to an axial centerline and adjacent to a combustion chamber. A fuel nozzle opening is defined through the deflector wall, and a nozzle centerline is extended through the fuel nozzle opening along a lengthwise direction. The annular axial wall is coupled to the deflector wall and extended through the fuel nozzle opening. The axial wall is defined around the nozzle centerline. The annular shroud is defined around the nozzle centerline and extended co-directional to the axial wall. The axial wall and the annular shroud are each coupled to a radial wall defined upstream of the deflector wall. The annular shroud, the axial wall, and the radial wall together define a cooling plenum therebetween. The axial wall defines a discrete inlet opening therethrough providing fluid communication from a diffuser cavity to the cooling plenum. The cooling plenum defines an exit opening providing fluid communication from the cooling plenum to the combustion chamber.

    Combustor And Method Of Operation For Improved Emissions And Durability
    10.
    发明申请
    Combustor And Method Of Operation For Improved Emissions And Durability 审中-公开

    公开(公告)号：US20190234615A1

    公开(公告)日：2019-08-01

    申请号：US15883573

    申请日：2018-01-30

    Applicant: General Electric Company

    Inventor： Eric John Stevens ,  Allen Michael Danis

    IPC: F23R3/26 ,  F23R3/00 ,  F23R3/16

    CPC classification number: F23R3/26 ,  F05D2240/35 ,  F05D2270/08 ,  F23R3/002 ,  F23R3/16

    Abstract: A combustor assembly comprising a deflector wall in which a plurality of openings is defined through the deflector wall and around the fuel nozzle opening. The plurality of openings defines a first set of openings at a first radius, a second set of openings at or greater than a second radius greater than the first radius, and a third set of openings at one or more of a third radius between the first radius and the second radius. The first set of openings defines one or more of a first angle relative to the radial direction between approximately 60 degrees and approximately 100 degrees. The second set of openings defines one or more of a second angle between approximately zero and approximately 30 degrees. The third set of openings defines one or more of a third angle between the first angle and the second angle.

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