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    Multiple chamber rotating detonation combustor
    34.
    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
    36.
    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.

    PASSIVE FUEL COUPLED DYNAMIC MITIGATION DEVICE
    37.
    发明申请
    PASSIVE FUEL COUPLED DYNAMIC MITIGATION DEVICE 有权

    公开(公告)号：US20220372915A1

    公开(公告)日：2022-11-24

    申请号：US17323088

    申请日：2021-05-18

    Applicant: General Electric Company

    Inventor： Gurunath Gandikota ,  Steven Clayton Vise ,  Clayton S. Cooper ,  Michael A. Benjamin

    IPC: F02C7/22

    Abstract: A gas turbine engine that is configured to mitigate fuel coupled dynamics. The engine includes a combustor, a fuel delivery system, a fuel manifold line; and a device configured to mitigate fuel coupled dynamics. The device is attached to the fuel manifold line and includes a housing and a reflector. The housing includes a wall and the wall defines a housing surface that is configured to reflect waves conducted by fuel within the fuel delivery system. The reflector is positioned within the housing and the reflector includes an anterior surface that is configured to reflect waves conducted by fuel within the fuel delivery system such that wave the reflected waves can strike the surface.

    Combustion section heat transfer system for a propulsion system
    39.
    发明授权
    Combustion section heat transfer system for a propulsion system 有权

    公开(公告)号：US11143106B2

    公开(公告)日：2021-10-12

    申请号：US16675787

    申请日：2019-11-06

    Applicant: General Electric Company

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

    IPC: F23R7/00 ,  F02C7/18 ,  F01D9/02 ,  F02C3/14 ,  F23R3/00 ,  F02C7/10 ,  F01D1/24 ,  F23R3/28 ,  F01D25/12 ,  F23R3/50

    Abstract: The present disclosure is directed to a propulsion system including a wall defining a combustion chamber inlet, a combustion chamber outlet, and a combustion chamber therebetween, a nozzle assembly disposed at the combustion chamber inlet, the nozzle assembly configured to provide a fuel/oxidizer mixture to the combustion chamber, a turbine nozzle coupled to the wall and positioned at the combustion chamber outlet, wherein the turbine nozzle defines a cooling circuit within the turbine nozzle, and a casing positioned radially adjacent to the wall, wherein a channel structure is positioned between the casing and the wall, the channel structure in fluid communication with the cooling circuit within the turbine nozzle, and wherein a flowpath is formed between the wall and the casing, the flowpath in fluid communication from the cooling circuit at the turbine nozzle to the nozzle assembly to provide a flow of oxidizer to the thereto.

    COMBUSTOR SWIRLER
    40.
    发明申请
    COMBUSTOR SWIRLER 审中-公开

    公开(公告)号：US20200248903A1

    公开(公告)日：2020-08-06

    申请号：US16264775

    申请日：2019-02-01

    Applicant: General Electric Company

    Inventor： Karthikeyan Sampath ,  Saket Singh ,  Gurunath Gandikota ,  Perumallu Vukanti ,  Pradeep Naik ,  Steven Clayton Vise

    IPC: F23R3/14 ,  F23R3/28

    Abstract: A gas turbine engine swirler that includes a tubular body having a forward face, an aft end, and a throat. A plurality of primary swirl vanes that is positioned between the aft end and the forward face. A plurality of secondary swirl vanes that is positioned between the primary swirl vanes and the aft end. The plurality of primary swirl vanes and the plurality of secondary swirl vanes are configured such that the throat is fluidly connected to a plenum that is positioned outside of the tubular body. A tubular ferrule is positioned such that it joins the body at the forward face thereof. Each of the primary swirl vanes extend radially inwardly to a vane lip. The secondary swirl vanes extend radially inwardly for swirling air therefrom. The body also includes a tubular Venturi that extends aft from between the primary swirler vanes and the secondary swirler vanes for radially separating air swirled therefrom. Wherein the primary swirl vanes are configured to swirl air along a passageway and through an outlet that is oriented axially aft.

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