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    COMBUSTOR SWIRLER
    102.
    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.

    COMBUSTOR MIXER PURGE COOLING STRUCTURE
    103.
    发明申请
    COMBUSTOR MIXER PURGE COOLING STRUCTURE 审中-公开

    公开(公告)号：US20190086088A1

    公开(公告)日：2019-03-21

    申请号：US15710921

    申请日：2017-09-21

    Applicant: General Electric Company

    Inventor： Eric John Stevens ,  Allen Michael Danis ,  Ravi Chandra ,  Jayanth Sekar ,  Perumallu Vukanti

    IPC: F23R3/14 ,  F23R3/28 ,  F23D11/38

    Abstract: The present disclosure is directed to a combustor assembly for a gas turbine engine. The combustor assembly includes a deflector wall, an annular axial wall, and an annular shroud. The deflector wall is extended at least partially along a radial direction and a circumferential direction relative to an axial centerline and adjacent to a combustion chamber. A fuel nozzle opening is defined through the deflector wall, and a nozzle centerline is extended through the fuel nozzle opening along a lengthwise direction. The annular axial wall is coupled to the deflector wall and extended through the fuel nozzle opening. The axial wall is defined around the nozzle centerline. The annular shroud is defined around the nozzle centerline and extended co-directional to the axial wall. The axial wall and the annular shroud are each coupled to a radial wall defined upstream of the deflector wall. The annular shroud, the axial wall, and the radial wall together define a cooling plenum therebetween. The axial wall defines a discrete inlet opening therethrough providing fluid communication from a diffuser cavity to the cooling plenum. The cooling plenum defines an exit opening providing fluid communication from the cooling plenum to the combustion chamber.

    COMBUSTOR INCLUDING A STEAM INJECTOR OPERABLY INJECTING STEAM INOT A TRAPPED VORTEX CAVITY
    104.
    发明申请
    COMBUSTOR INCLUDING A STEAM INJECTOR OPERABLY INJECTING STEAM INOT A TRAPPED VORTEX CAVITY 有权

    公开(公告)号：US20250067439A1

    公开(公告)日：2025-02-27

    申请号：US18453506

    申请日：2023-08-22

    Applicant: General Electric Company

    Inventor： Pradeep Naik ,  Clayton S. Cooper ,  Perumallu Vukanti ,  Michael A. Benjamin ,  Steven C. Vise ,  Sripathi Mohan

    IPC: F23R3/28

    Abstract: A combustor includes a combustion chamber having an outer liner and an inner liner and defining a first combustion zone, an annular dome coupled to the outer liner and the inner liner, and a trapped vortex cavity extending from at least one of the outer liner or the inner liner and defining a second combustion zone. A plurality of first mixing assemblies are disposed through the annular dome, and operably inject a first fuel-air mixture into the first combustion zone. A plurality of second mixing assemblies are disposed at the trapped vortex cavity, and operably inject a second fuel-air mixture into the second combustion zone defined in the trapped vortex cavity to produce combustion gases. A steam system includes a steam injector in fluid communication with the trapped vortex cavity. The steam injector operably injects steam into the trapped vortex cavity and the steam mixes with the combustion gases.

    Swirler-ferrule assembly
    107.
    发明授权
    Swirler-ferrule assembly 有权

    公开(公告)号：US12130013B2

    公开(公告)日：2024-10-29

    申请号：US17396155

    申请日：2021-08-06

    Applicant: General Electric Company

    Inventor： Steven C. Vise ,  Clayton S. Cooper ,  Michael A. Benjamin ,  Pradeep Naik ,  Kwanwoo Kim ,  Shai Birmaher ,  Perumallu Vukanti ,  Saket Singh ,  Karthikeyan Sampath

    IPC: F23D11/38 ,  B05B7/10

    CPC classification number: F23D11/383 ,  B05B7/10

    Abstract: A swirler-ferrule assembly includes a radial swirler, a ferrule, a fuel nozzle, and a surface feature. The radial swirler includes a primary swirler vane having a primary air passage and a secondary swirler vane having a secondary air passage. The ferrule may be connected to the radial swirler. The surface feature may be located on the primary swirler vane and/or the ferrule. The surface feature may be configured to direct an air flow through the primary air passage away from a recirculation zone located upstream of the primary swirler vane. The surface feature has a trailing end and a distal end, and the fuel nozzle is axially aligned with the trailing end of the surface feature or is located axially downstream of the trailing end of the surface feature. The surface feature may have a plurality of grooves.

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