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    Combustor liner for a gas turbine engine and an associated method thereof
    54.
    发明授权
    Combustor liner for a gas turbine engine and an associated method thereof 有权

    公开(公告)号：US10816202B2

    公开(公告)日：2020-10-27

    申请号：US15823633

    申请日：2017-11-28

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Mayank Krisna Amble ,  Perumallu Vukanti ,  Steven Clayton Vise ,  Michael Anthony Benjamin

    IPC: F23R3/06 ,  F23R3/00 ,  F23R3/26 ,  F02K1/82 ,  F02C7/18 ,  F02C3/04

    Abstract: A combustor liner, a gas turbine engine including a combustor having the combustor liner, and a method for regulating jet wakes in the combustor are disclosed. The combustor liner includes a panel, at least one first through-hole, and a plurality of second through-holes including first and second set of through-holes. The at least one first through-hole is disposed on a section of the panel in a first row. The plurality of second through-holes is disposed on the section along axial and circumferential directions and arranged adjacent to the at least one first through-hole. The first set and the second set of through-holes are arranged in a second row and a third row respectively. The first, second, and third rows extend along the circumferential direction. The at least one first through-hole and the plurality of second through-holes collectively cover circumferential plane of the section along the first, second, and third rows.

    Engine With Rotating Detonation Combustion System
    57.
    发明申请
    Engine With Rotating Detonation Combustion System 审中-公开

    公开(公告)号：US20190264919A1

    公开(公告)日：2019-08-29

    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 ,  F23R3/34 ,  F23R3/56 ,  F02K7/10 ,  F02K7/08

    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.

    ROTATING DETONATION COMBUSTOR WITH FLUID DIODE STRUCTURE
    60.
    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.

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