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    VOLUTE TRAPPED VORTEX COMBUSTOR ASSEMBLY
    51.
    发明申请
    VOLUTE TRAPPED VORTEX COMBUSTOR ASSEMBLY 审中-公开

    公开(公告)号：US20190120491A1

    公开(公告)日：2019-04-25

    申请号：US15793104

    申请日：2017-10-25

    Applicant: General Electric Company

    Inventor： Gregory Allen Boardman ,  Pradeep Naik ,  Joseph Zelina ,  Clayton Stuart Cooper

    IPC: F23R3/28 ,  F23R3/00 ,  F23R3/58 ,  F23R3/34 ,  F02C3/14

    Abstract: A combustor assembly is generally provided. The combustor assembly includes a volute wall extended annularly around a combustor centerline. The volute wall is extended at least partially as a spiral curve from a circumferential reference line around the combustor centerline. The volute wall defines a combustion chamber therewithin. An annular inner wall is extended at least partially along a lengthwise direction from the volute wall. An annular outer wall is extended at least partially along the lengthwise direction from the volute wall. The inner wall and the outer wall are each separated along a radial direction from the combustor centerline. A primary flow passage is defined between the inner wall and the outer wall in fluid communication from the combustion chamber.

    ROTATING DETONATION COMBUSTOR WITH FLUID DIODE STRUCTURE
    53.
    发明申请
    ROTATING DETONATION COMBUSTOR WITH FLUID DIODE STRUCTURE 审中-公开

    公开(公告)号：US20180355795A1

    公开(公告)日：2018-12-13

    申请号：US15618575

    申请日：2017-06-09

    Applicant: General Electric Company

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

    IPC: F02C5/02 ,  F23R3/28 ,  F23R3/42

    CPC classification number: F02C5/02 ,  F05D2240/35 ,  F23R3/28 ,  F23R3/42

    Abstract: The present disclosure is directed to a rotating detonation combustion system for a propulsion system, the rotating detonation combustion system defining a radial direction, a circumferential direction, and a longitudinal centerline in common with the propulsion system extended along a longitudinal direction. The rotating detonation combustion system includes an outer wall and an inner wall together defining at least in part a combustion chamber and a combustion chamber inlet; a nozzle located at the combustion chamber inlet defined by a nozzle wall, the nozzle defining a lengthwise direction and extending between a nozzle inlet and a nozzle outlet along the lengthwise direction, the nozzle inlet configured to receive a flow of oxidizer, the nozzle further defining a throat between the nozzle inlet and nozzle outlet, and wherein the nozzle defines a converging-diverging nozzle, and wherein a diverging section of the nozzle wall defines a fluid diode; and a fuel injection port defining a fuel outlet located between the nozzle inlet and the nozzle outlet for providing fuel to the flow of oxidizer received through the nozzle inlet.

    HYBRID COMBUSTOR ASSEMBLY AND METHOD OF OPERATION
    54.
    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.

    COMBUSTOR SWIRL VANE APPARATUS
    59.
    发明申请
    COMBUSTOR SWIRL VANE APPARATUS 有权

    公开(公告)号：US20220333779A1

    公开(公告)日：2022-10-20

    申请号：US17232638

    申请日：2021-04-16

    Applicant: General Electric Company

    Inventor： Steven Clayton Vise ,  Clayton Stuart Cooper ,  Allen M. Danis

    IPC: F23R3/14 ,  F23D14/62 ,  F23R3/28

    Abstract: A swirler apparatus for a combustor, including: primary and secondary swirlers disposed axially adjacent to each other along a swirler centerline; the primary swirler including a plurality of primary swirl vanes arrayed around the swirler centerline; and the secondary swirler including a plurality of secondary swirl vanes arrayed around the swirler centerline, each secondary swirl vane including opposed sides bounded between opposed forward and aft edges and opposed leading and trailing edges; wherein the forward edge is oriented at a first vane angle with respect to a radial direction; wherein the aft edge is oriented at a second vane angle with respect to the radial direction; and wherein the second vane angle is different from the first vane angle.

    Engine with rotating detonation combustion system
    60.
    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.

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