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    Turbine engine combustor including a heat shield
    111.
    发明授权
    Turbine engine combustor including a heat shield 有权

    公开(公告)号：US12286932B1

    公开(公告)日：2025-04-29

    申请号：US18441736

    申请日：2024-02-14

    Applicant: General Electric Company

    Inventor： Hejie Li ,  Hiranya Nath ,  Habeeb Kunnummal Manat ,  Shai Birmaher ,  Craig Alan Gonyou ,  Anquan Wang ,  Michael A. Benjamin

    IPC: F02C7/24 ,  F02C7/12 ,  F23R3/28

    Abstract: A combustor of a turbine engine has a combustion chamber for combusting fuel and air, generating heat. A fuel nozzle-mixer assembly mixes and injects fuel and air into the combustion chamber for combustion. The assembly has a heat shield at an aft end for shielding the assembly from the heat. A centerbody outer shell defines a cooling air flow cavity. A cooling air flow gap is defined between the centerbody outer shell and the heat shield. The centerbody outer shell has cooling air exit holes between the cooling air flow cavity and the cooling air flow gap, the air passing through the cooling air exit holes and into the cooling air flow gap. The cooling air exits the cooling air flow gap at a cooling air exit angle, the cooling air exit angle having a non-zero axially aft component, displacing the combustion downstream, to protect the assembly.

    COMBUSTOR WITH A DILUTION PASSAGE
    112.
    发明申请
    COMBUSTOR WITH A DILUTION PASSAGE 有权

    公开(公告)号：US20250067435A1

    公开(公告)日：2025-02-27

    申请号：US18943011

    申请日：2024-11-11

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Manampathy G. Giridharan ,  Pradeep Naik ,  Michael A. Benjamin

    IPC: F23R3/06 ,  F23R3/26

    Abstract: A combustor having a casing, an inner liner, an outer liner, a compressed air passageway, a combustion chamber and a set of dilution passages. The compressed air passageway being formed between the casing, the inner liner and the outer liner. The combustion chamber being at least partially defined by the inner liner and the outer liner. The set of dilution passages extending through at least one of the inner liner or the outer liner. Each dilution passage of the set of dilution passages extending between an inlet fluidly coupled to the compressed air passageway and a dilution hole fluidly coupled to the combustion chamber.

    SWIRLER-FERRULE ASSEMBLY
    115.
    发明申请
    SWIRLER-FERRULE ASSEMBLY 有权

    公开(公告)号：US20250035304A1

    公开(公告)日：2025-01-30

    申请号：US18913347

    申请日：2024-10-11

    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

    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.

    Combustor with a variable primary zone combustion chamber
    118.
    发明授权
    Combustor with a variable primary zone combustion chamber 有权

    公开(公告)号：US12104795B2

    公开(公告)日：2024-10-01

    申请号：US17664975

    申请日：2022-05-25

    Applicant: General Electric Company

    Inventor： Ravindra Shankar Ganiger ,  Hiranya Nath ,  Michael A. Benjamin

    IPC: F23R3/26 ,  F23R3/04 ,  F23R3/42 ,  F23R3/06 ,  F23R3/08

    CPC classification number: F23R3/42 ,  F23R3/04 ,  F23R3/26 ,  F23R3/06 ,  F23R3/08

    Abstract: A combustor for a gas turbine includes a combustor liner that has an outer liner and an inner liner. At least one of the outer liner and the inner liner includes (a) an upstream liner section fixedly connected in the combustor, (b) a downstream liner section fixedly connected in the combustor, and (c) a dilution liner section including a movable portion including at least a part of the dilution liner section and having at least one dilution opening therethrough. The movable portion is arranged to translate in an upstream direction and in a downstream direction. At least one actuator is connected to the movable portion of the dilution liner section and controls translational movement of the movable portion in the upstream direction and the downstream direction to adjust a volume of a primary combustion zone within the combustor.

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