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    SYSTEM AND METHOD HAVING ANNULAR FLOW PATH ARCHITECTURE
    121.
    发明申请
    SYSTEM AND METHOD HAVING ANNULAR FLOW PATH ARCHITECTURE 审中-公开
    具有流动路径结构的系统和方法

    公开(公告)号：US20170067639A1

    公开(公告)日：2017-03-09

    申请号：US14849564

    申请日：2015-09-09

    Applicant: General Electric Company

    Inventor： Nan Zong ,  Ahmed Mostafa ELKady ,  Mark Anthony Mueller ,  Pradeep Naik ,  Gerardo Antonio Salazar Lois ,  Rishikesh Prakash Karande ,  Jeffrey Michael Martini

    IPC: F23R3/52 ,  F02C7/20 ,  F02C3/14

    CPC classification number: F02C3/14 ,  F02C7/22 ,  F05D2260/30 ,  F23R3/04 ,  F23R3/283 ,  F23R3/50 ,  Y02T50/675

    Abstract: A system includes an annular combustor having a housing disposed about a head end chamber upstream of a combustion chamber. The annular combustor is configured to extend circumferentially about a rotational axis of a gas turbine engine, and an axis of the combustion chamber is acutely angled relative to the rotational axis. The system also includes a holder coupled to the housing and extending through the head end chamber in an axial direction relative to the axis of the combustion chamber. The holder includes a first receptacle configured to hold a first fuel nozzle, and the holder comprises a first fuel passage extending to the first receptacle.

    Abstract translation: 系统包括环形燃烧器，其具有围绕燃烧室上游的头端室设置的壳体。 环形燃烧器被构造成围绕燃气涡轮发动机的旋转轴线周向延伸，并且燃烧室的轴线相对于旋转轴线成锐角。 该系统还包括联接到壳体并且相对于燃烧室的轴线在轴向方向上延伸穿过头端室的保持器。 保持器包括构造成保持第一燃料喷嘴的第一容器，并且保持器包括延伸到第一容器的第一燃料通道。

    COMBUSTOR INCLUDING A STEAM INJECTOR OPERABLY INJECTING STEAM INOT A TRAPPED VORTEX CAVITY
    122.
    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.

    Combustion liner having a dilution passage
    124.
    发明授权
    Combustion liner having a dilution passage 有权

    公开(公告)号：US12173900B2

    公开(公告)日：2024-12-24

    申请号：US17663093

    申请日：2022-05-12

    Applicant: General Electric Company

    Inventor： Pradeep Naik ,  Shai Birmaher ,  Saket Singh ,  Krishnendu Chakraborty

    IPC: F23R3/06 ,  F23R3/16

    Abstract: A liner for a combustor in a gas turbine engine and a related method. The liner includes a liner body having a cold side and a hot side. The liner includes a dilution passage having a concatenated geometry extending through the liner body. The dilution passage is configured (i) to integrate a first dilution air flow flowing through the dilution passage from the cold side to the hot side and a second dilution air flow flowing through the dilution passage from the cold side to the hot side into an integrated dilution air flow, and (ii) to inject the integrated dilution air flow into a core primary combustion zone of the combustor to attain a predetermined combustion state of the combustor.

    Combustion liner
    126.
    发明授权
    Combustion liner 有权

    公开(公告)号：US12152778B1

    公开(公告)日：2024-11-26

    申请号：US18345342

    申请日：2023-06-30

    Applicant: General Electric Company

    Inventor： Ranganatha Narasimha Chiranthan ,  Rimple Rangrej ,  Saket Singh ,  Pradeep Naik

    IPC: F23R3/06 ,  F23R3/00

    Abstract: A liner for a combustor in a gas turbine engine. The liner includes a liner body having a cold side and a hot side, a dilution opening extending through the liner body, a first passage positioned adjacent the dilution opening and extending through the liner body from the cold side to the hot side, and a second passage positioned adjacent the dilution opening and extending through the liner body from the cold side to the hot side, the second passage being separate from the first passage and being located on a diametrically opposing side of the dilution opening from the first passage. A dilution flow flows through the dilution opening from the cold side to the hot side and a secondary flow flows through the first passage and the second passage from the cold side to the hot side.

    Swirler-ferrule assembly
    127.
    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.

    Mixer vanes
    128.
    发明授权
    Mixer vanes 有权

    公开(公告)号：US12123596B2

    公开(公告)日：2024-10-22

    申请号：US17389022

    申请日：2021-07-29

    Applicant: General Electric Company

    Inventor： Rimple Rangrej ,  Saket Singh ,  Pradeep Naik ,  Neeraj Mishra

    IPC: F23R3/14

    CPC classification number: F23R3/14 ,  F05D2240/127 ,  F05D2240/35 ,  F05D2250/183

    Abstract: A gas turbine combustor includes a main mixer for providing an air flow to mix with a fuel flow in a combustor. The main mixer includes an annular mixer body, a plurality of mixer vanes located circumferentially around the annular mixer body, and a plurality of wedges extending radially outward from each of the plurality of mixer vanes. At least one of the wedges includes serrations. The air flow through the main mixer enters the main mixer at a leading edge of the mixer vane, flows over the plurality of wedges, and exits the mixer vanes at a trailing edge of the main mixer. The wedges create vortices in the air flow to provide a uniform fuel-air flow.

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