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    Combustor liner having dilution openings with swirl vanes
    21.
    发明授权
    Combustor liner having dilution openings with swirl vanes 有权

    公开(公告)号：US11692708B1

    公开(公告)日：2023-07-04

    申请号：US17809379

    申请日：2022-06-28

    Applicant: General Electric Company

    Inventor： Karthikeyan Sampath ,  Perumallu Vukanti ,  Ajoy Patra ,  Pradeep Naik ,  Hiranya Nath

    IPC: F23R3/14 ,  F23R3/06

    CPC classification number: F23R3/14 ,  F23R3/06 ,  F23R2900/03044

    Abstract: A combustor liner for a gas turbine includes a liner that at least partially defines a combustion chamber, and that a plurality of dilution openings therethrough. Each dilution opening includes an outer wall defining an outer perimeter of the dilution opening and defining a dilution opening centerline axis through the dilution opening. A plurality of swirl vanes extend from the outer wall into a dilution airflow passage that extends through the dilution opening. Each of the plurality of swirl vanes extends from the outer wall into the dilution airflow passage at a respective swirl vane angle with respect to the outer wall. The plurality of swirl vanes are arranged in a successive arrangement about the outer wall, and successive respective ones of the plurality of swirl vanes extend from the outer wall at a different swirl vane angle.

    Canted combustor for gas turbine engine
    24.
    发明授权
    Canted combustor for gas turbine engine 有权

    公开(公告)号：US10598380B2

    公开(公告)日：2020-03-24

    申请号：US15711203

    申请日：2017-09-21

    Applicant: General Electric Company

    Inventor： David Albin Lind ,  Rishikesh Karande ,  Pradeep Naik ,  Ajoy Patra ,  Gregory Allen Boardman

    IPC: F23R3/04 ,  F23R3/00 ,  F23R3/28 ,  F02C7/24 ,  F02C7/12 ,  F23R3/02 ,  F23R3/50

    Abstract: The present disclosure is directed to a combustion section for a gas turbine engine including a combustor assembly, an outer casing, a fuel injector assembly, and an inner casing. An inner liner and an outer liner are each extended at least partially along a lengthwise direction and at an acute angle. A dome assembly is extended between the inner liner and the outer liner, and the inner liner, and the outer liner together define a combustion chamber therebetween. A bulkhead assembly defining a plurality of walls is coupled to the inner liner and generally surrounding the outer liner and dome assembly. The outer casing surrounds the combustor assembly. The inner casing, the outer casing, and the combustor assembly together define a primary flowpath. An oxidizer flows through the primary flowpath in serial flow through the plenum and the fuel injector assembly into the combustion chamber.

    Floating primary vane swirler
    25.
    发明授权
    Floating primary vane swirler 有权

    公开(公告)号：US12276423B2

    公开(公告)日：2025-04-15

    申请号：US17649129

    申请日：2022-01-27

    Applicant: General Electric Company

    Inventor： Pradeep Naik ,  David A. Lind ,  Shai Birmaher ,  Ranganatha Narasimha Chiranthan ,  Ajoy Patra ,  Saket Singh

    IPC: F23R3/14 ,  F02C7/22 ,  F23R3/28 ,  F23R3/42

    Abstract: A swirler assembly includes a primary swirler having a primary swirler connecting portion, a fuel nozzle connecting portion for connecting a fuel nozzle to the primary swirler, and a primary oxidizer flow passage that extends at least partially in the longitudinal direction, and a secondary swirler having a secondary swirler connecting member, where the primary swirler connecting portion and the secondary swirler connecting member engage to connect the primary swirler and the secondary swirler in the longitudinal direction, and to permit radial movement of the primary swirler with respect to the secondary swirler.

    Varying dilution hole design for combustor liners
    28.
    发明授权
    Varying dilution hole design for combustor liners 有权

    公开(公告)号：US12163660B2

    公开(公告)日：2024-12-10

    申请号：US18484987

    申请日：2023-10-11

    Applicant: General Electric Company

    Inventor： Rimple Rangrej ,  Saket Singh ,  Pradeep Naik ,  Ajoy Patra

    IPC: F23R3/06

    Abstract: A combustor for a turbomachine engine includes a combustion chamber, a liner forming a boundary of the combustion chamber, and multiple dilution holes through the liner to permit airflow into the combustion chamber. The dilution holes include converging dilution holes and diverging dilution holes, the converging dilution holes having a converging cross-sectional profile and the diverging dilution holes having a diverging cross-sectional profile.

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