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    Engine with rotating detonation combustion system
    22.
    发明授权
    Engine with rotating detonation combustion system 有权

    公开(公告)号：US11320147B2

    公开(公告)日：2022-05-03

    申请号：US15904918

    申请日：2018-02-26

    Applicant: General Electric Company

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

    IPC: F23R3/18 ,  F23R7/00 ,  F02K7/10 ,  F02K7/08 ,  F23R3/34

    Abstract: A Brayton cycle engine including an inner wall assembly defining a detonation combustion region upstream thereof extended from a longitudinal wall into a gas flowpath. An actuator adjusts a depth of the detonation combustion region into the gas flowpath. A method for operating the engine includes flowing an oxidizer through the gas flowpath; capturing a portion of the flow of oxidizer via the inner wall; flowing a first flow of fuel to the captured flow of oxidizer; producing a rotating detonation gases via a mixture of the first flow of fuel and the captured flow of oxidizer; flowing at least a portion of the detonation gases downstream to mix with the flow of oxidizer; flowing a second flow of fuel to the mixture of detonation gases and oxidizer; and burning the mixture of the second flow of fuel and the detonation gases/oxidizer mixture.

    Combustion Section Heat Transfer System for a Propulsion System
    24.
    发明申请
    Combustion Section Heat Transfer System for a Propulsion System 审中-公开

    公开(公告)号：US20200088101A1

    公开(公告)日：2020-03-19

    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: F02C7/18 ,  F02C3/14 ,  F23R3/00 ,  F02C7/10 ,  F01D1/24 ,  F01D9/02

    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.

    MULTIPLE CHAMBER ROTATING DETONATION COMBUSTOR
    26.
    发明申请
    MULTIPLE CHAMBER ROTATING DETONATION COMBUSTOR 审中-公开

    公开(公告)号：US20180355822A1

    公开(公告)日：2018-12-13

    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: F02K7/00

    CPC classification number: F02K7/005

    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.

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