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    SYSTEMS AND METHODS FOR SPRAYING FUEL IN AN AUGMENTED GAS TURBINE ENGINE
    74.
    发明申请
    SYSTEMS AND METHODS FOR SPRAYING FUEL IN AN AUGMENTED GAS TURBINE ENGINE 有权

    公开(公告)号：US20220243915A1

    公开(公告)日：2022-08-04

    申请号：US17166477

    申请日：2021-02-03

    Applicant: General Electric Company

    Inventor： Brett A. Rich ,  Michael A. Benjamin ,  Nicholas R. Overman ,  Aaron J. Glaser

    IPC: F23R3/20 ,  F23R3/28

    Abstract: In some embodiments, systems, apparatuses and methods are provided herein useful for spraying fuel in an augmented gas turbine engine. The embodiments may include a spray bar with a fuel injection aperture to inject a fuel jet into a fuel conduit; the fuel conduit having a fuel window to discharge the fuel jet into a core exhaust flow of an augmented gas turbine engine; a first airflow conduit having a first orifice to discharge a first air stream into the core exhaust flow; and a second airflow conduit having a second orifice to discharge a second air stream into the core exhaust flow. The first orifice and the second orifice may be paired with the fuel window to cooperatively shape the fuel jet coming out of the fuel window.

    COMBUSTOR WITH A DILUTION PASSAGE
    75.
    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
    78.
    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.

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