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    Swirler-ferrule assembly
    11.
    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.

    SWIRLER-FERRULE ASSEMBLY
    15.
    发明申请
    SWIRLER-FERRULE ASSEMBLY 有权

    公开(公告)号：US20220412550A1

    公开(公告)日：2022-12-29

    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

    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.

    MULTI-POINT INJECTION MINI MIXING FUEL NOZZLE ASSEMBLY
    16.
    发明申请
    MULTI-POINT INJECTION MINI MIXING FUEL NOZZLE ASSEMBLY 审中-公开

    公开(公告)号：US20180128490A1

    公开(公告)日：2018-05-10

    申请号：US15343634

    申请日：2016-11-04

    Applicant: General Electric Company

    Inventor： Gregory Allen Boardman ,  Pradeep Naik ,  Manampathy Gangadharan Giridharan ,  David Albin Lind ,  Jeffrey Michael Martini ,  Clayton S. Cooper

    IPC: F23R3/28 ,  F23R3/04

    CPC classification number: F23R3/286 ,  F23R3/04 ,  F23R3/14 ,  F23R3/283 ,  Y02T50/675

    Abstract: The present disclosure is directed to a fuel injector for a gas turbine engine. The fuel injector includes an end wall, a centerbody, an outer sleeve surrounding the centerbody from the end wall toward the downstream end of the fuel injector, and a thermal management conduit. The centerbody includes an axially extended outer wall and inner wall extended from the end wall toward a downstream end of the fuel injector. The outer wall, the inner wall, and the end wall together define a fluid conduit extended in a first direction toward the downstream end of the fuel injector and in a second direction toward an upstream end of the fuel injector. The outer sleeve and the centerbody define a premix passage radially therebetween and an outlet at the downstream end of the premix passage. The outer sleeve defines a plurality of radially oriented first air inlet ports in circumferential arrangement at a first axial portion of the outer sleeve. The outer sleeve defines a plurality of radially oriented second air inlet ports in circumferential arrangement at a second axial portion of the outer sleeve. The outer sleeve further defines a first fluid passage arranged between each first air inlet port and extended from the end wall. A fluid passage wall extends from the end wall within the first fluid passage to define a second fluid passage extended from the end wall within the first fluid passage. The outer sleeve further defines a first injection port in fluid communication with the first fluid passage and a second injection port in fluid communication with the second fluid passage. The thermal management conduit is defined by the fluid communication of the fluid conduit and the first fluid passage and the thermal communication of the second fluid passage in adjacent arrangement with the first fluid passage.

    TURBINE ENGINE INCLUDING A FUEL AND STEAM SYSTEM
    17.
    发明申请
    TURBINE ENGINE INCLUDING A FUEL AND STEAM SYSTEM 有权

    公开(公告)号：US20250129748A1

    公开(公告)日：2025-04-24

    申请号：US18492002

    申请日：2023-10-23

    Applicant: General Electric Company

    Inventor： Pradeep Naik ,  Clayton S. Cooper ,  Steven C. Vise ,  Michael A. Benjamin ,  Steven Marakovits ,  Sibtosh Pal ,  Sripathi Mohan

    IPC: F02C3/30 ,  F02C9/28

    Abstract: A turbine engine has a combustor in a core air flow path that generates combustion gases and a fuel and steam system fluidly coupled to the combustor. The fuel and steam system has a steam system to provide a steam flow to the combustor and a fuel system to provide a primary fuel flow and a secondary fuel flow to the combustor. The fuel system has a first state in which there is a first flow rate of the secondary fuel flow to the combustor and a second state in which there is a second flow rate of the secondary fuel flow to the combustor. The first flow rate and the second flow rate are different. The first state and the second state are based on a condition of the steam system.

    TURBINE ENGINE INCLUDING A COMBUSTOR
    20.
    发明申请
    TURBINE ENGINE INCLUDING A COMBUSTOR 有权

    公开(公告)号：US20240401807A1

    公开(公告)日：2024-12-05

    申请号：US18326665

    申请日：2023-05-31

    Applicant: General Electric Company

    Inventor： Hiranya Nath ,  Michael A. Benjamin ,  Richard W. Stickles ,  Clayton S. Cooper ,  Steven C. Vise ,  Ranganatha Narasimha Chiranthan

    IPC: F23R3/00 ,  F23R3/14

    Abstract: A turbine engine includes a combustor having a main combustion chamber, an annular dome positioned at a first angle α with respect to a longitudinal centerline axis of the combustor, and a secondary combustion chamber. The secondary combustion chamber is defined by a portion of the annular dome and an aft wall positioned at a second angle β with respect to the longitudinal centerline axis. A pilot mixer is disposed through the annular dome and injects a pilot mixer fuel-air mixture at a pilot mixer fuel-air mixture angle into the main combustion chamber and generates a first recirculation zone. A main mixer is disposed through the aft wall or the annular dome at the secondary combustion chamber. The main mixer injects a main mixer fuel-air mixture at a main mixer fuel-air mixture angle into the secondary combustion chamber to produce combustion gases and generates a second recirculation zone.

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