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    HYBRID COMBUSTOR ASSEMBLY AND METHOD OF OPERATION
    51.
    发明申请
    HYBRID COMBUSTOR ASSEMBLY AND METHOD OF OPERATION 审中-公开

    公开(公告)号：US20180355793A1

    公开(公告)日：2018-12-13

    申请号：US15618682

    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: F02C3/16 ,  F23R3/00 ,  F02C7/22

    CPC classification number: F02C3/16 ,  F02C7/222 ,  F23R3/002

    Abstract: A hybrid combustion system, and method of operation, for a propulsion system is provided. The hybrid combustion system defines a radial direction, a circumferential direction, and a longitudinal centerline in common with the propulsion system extended along a longitudinal direction. The hybrid combustion system includes a rotating detonation combustion (RDC) system comprising an annular outer wall and an annular inner wall each generally concentric to the longitudinal centerline and together defining a RDC chamber and a RDC inlet, the RDC system further comprising a nozzle located at the RDC inlet defined by a nozzle wall. The nozzle defines a lengthwise direction extended between a nozzle inlet and a nozzle outlet along the lengthwise direction, and the nozzle inlet is configured to receive a flow of oxidizer. The nozzle further defines a throat between the nozzle inlet and the nozzle outlet, and wherein the nozzle defines a converging-diverging nozzle. The hybrid combustion system further includes an inner liner extended generally along the longitudinal direction; an outer liner extended generally along the longitudinal direction and disposed outward of the inner liner along the radial direction; a bulkhead wall disposed at the upstream end of the inner and outer liners, in which the bulkhead wall extends generally in the radial direction and couples the inner liner and the outer liner, and wherein the inner liner, the outer liner, and the bulkhead wall together define a primary combustion chamber, and further wherein the RDC system and bulkhead wall together define a RDC outlet through the bulkhead wall and adjacent to the primary combustion chamber; and a fuel manifold assembly extended at least partially through the bulkhead wall, in which the fuel manifold assembly defines a fuel manifold assembly exit disposed adjacent to the primary combustion chamber.

    Multiple chamber rotating detonation combustor
    56.
    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
    57.
    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.

    Combustion section heat transfer system for a propulsion system
    59.
    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.

    Turbine Engine With Rotating Detonation Combustion System
    60.
    发明申请
    Turbine Engine With Rotating Detonation Combustion System 审中-公开

    公开(公告)号：US20190271268A1

    公开(公告)日：2019-09-05

    申请号：US15909196

    申请日：2018-03-01

    Applicant: General Electric Company

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

    IPC: F02C7/22 ,  F23R3/28 ,  F23R3/10 ,  F01D9/02 ,  F02C3/08

    Abstract: A turbine engine including a compressor rotor and a rotating detonation combustion (RDC) system. The compressor rotor includes a compressor airfoil defining a trailing edge disposed within a core flowpath of the turbine engine. The core flowpath defines a radial distance between an outer radius and an inner radius at the compressor rotor. The RDC system includes an outer wall and an inner wall each extended along a lengthwise direction and defining a detonation chamber therebetween. The RDC system further includes a strut defining a nozzle assembly and a fuel injection opening providing a flow of fuel to the detonation chamber. The compressor rotor provides a flow of oxidizer in direct fluid communication to the nozzle assembly of the RDC system.

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