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    Combustor Acoustic Damping Structure
    24.
    发明申请
    Combustor Acoustic Damping Structure 审中-公开

    公开(公告)号：US20180274780A1

    公开(公告)日：2018-09-27

    申请号：US15468172

    申请日：2017-03-24

    Applicant: General Electric Company

    Inventor： Kwanwoo Kim ,  Owen Graham ,  Clayton Stuart Cooper

    IPC: F23M20/00

    CPC classification number: F23R3/10 ,  F05D2240/35 ,  F05D2260/964 ,  F23R3/002 ,  F23R2900/00014

    Abstract: The present disclosure is directed to a combustor assembly for a gas turbine engine. The combustor assembly includes an annular bulkhead adjacent to a diffuser cavity; a deflector downstream of the bulkhead and adjacent to a combustion chamber; a bulkhead support coupled to an upstream side of the deflector; a first walled enclosure coupled to the bulkhead support; and a second walled enclosure coupled to the first walled enclosure. The deflector and the bulkhead support together define a bulkhead conduit therethrough to the combustion chamber. The first walled enclosure defines a first cavity and a hot side orifice. The hot side orifice is adjacent to and in fluid communication with the bulkhead conduit. The second walled enclosure defines a second cavity and a second opening adjacent to a diffuser cavity.

    Multiple chamber rotating detonation combustor
    28.
    发明授权
    Multiple chamber rotating detonation combustor 有权

    公开(公告)号：US11674476B2

    公开(公告)日：2023-06-13

    申请号：US15618289

    申请日：2017-06-09

    Applicant: General Electric Company

    Inventor： Steven Clayton Vise ,  Joseph Zelina ,  Arthur Wesley Johnson ,  Clayton Stuart Cooper ,  Sibtosh Pal

    IPC: F02K7/06 ,  F02C5/12 ,  F02K7/08 ,  F02C5/11 ,  F23R7/00 ,  F02K7/10

    CPC classification number: F02K7/06 ,  F02C5/11 ,  F02C5/12 ,  F02K7/08 ,  F23R7/00 ,  F02K7/10 ,  F05D2220/80

    Abstract: The present disclosure is directed to a rotating detonation combustion system for a propulsion system including a plurality of combustors in adjacent arrangement along the circumferential direction. Each combustor defines a combustor centerline extended through each combustor, and each combustor comprises an outer wall defining a combustion chamber and a combustion inlet. Each combustion chamber is defined by an annular gap and a combustion chamber length together defining a volume of each combustion chamber. Each combustor defines a plurality of nozzle assemblies each disposed at the combustion inlet in adjacent arrangement around each combustor centerline. Each nozzle assembly defines a nozzle wall extended along a lengthwise direction, a nozzle inlet, a nozzle outlet, and a throat therebetween, and each nozzle assembly defines a converging-diverging nozzle. A first array of combustors defines a first volume and a second array of combustors defines a second volume different from the first volume.

    ENGINE WITH ROTATING DETONATION COMBUSTION SYSTEM
    29.
    发明申请
    ENGINE WITH ROTATING DETONATION COMBUSTION SYSTEM 有权

    公开(公告)号：US20230020803A1

    公开(公告)日：2023-01-19

    申请号：US17935646

    申请日：2022-09-27

    Applicant: General Electric Company

    Inventor： Sibtosh Pal ,  Steven Clayton Vise ,  Arthur Wesley Johnson ,  Clayton Stuart Cooper ,  Joseph Zelina

    IPC: F23R7/00 ,  F02K7/08 ,  F02K7/10 ,  F02K7/16

    Abstract: A Brayton cycle engine and method for operation. The engine includes an inner wall assembly and an upstream wall assembly each extended from a longitudinal wall into a gas flowpath. An actuator adjusts a depth of the detonation combustion region into the gas flowpath between the inner wall assembly and the upstream wall assembly. The engine flows an oxidizer through the gas flowpath and the inner wall captures a portion of the oxidizer. The engine further adjusts the captured flow of oxidizer via the upstream wall and flows a first flow of fuel to the captured flow of oxidizer to produce rotating detonation gases. The engine flows the detonation gases downstream and to mix with the flow of oxidizer, and flows and burns a second flow of fuel to the detonation gases/oxidizer mixture to produce thrust.

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