中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

6 records (took 0.012 seconds)

    High shear swirler for gas turbine engine
    1.
    发明授权
    High shear swirler for gas turbine engine 有权

    公开(公告)号：US12007115B1

    公开(公告)日：2024-06-11

    申请号：US18115111

    申请日：2023-02-28

    Applicant: Raytheon Technologies Corporation

    Inventor： Baris A. Sen ,  Zhongtao Dai ,  Wookyung Kim ,  Stephen K. Kramer

    IPC: F23R3/14

    CPC classification number: F23R3/14

    Abstract: A fuel injector assembly for a gas turbine engine includes a swirler and a fuel nozzle. The swirler has an outer wall having a SOW inner wall surface, an inner wall having a SIW inner wall surface and a SIW outer wall surface, an outer passage, and an inner passage. The SIW inner wall surface includes first and second sections. The first section extends between a first airflow inlet and the second section, and the second section extends between the first section and an inner wall distal end. The first section tapers radially inward, and the second section extends parallel the center axis. The outer wall circumscribes the inner wall and extends axially along the center axis to a distal outer wall end, and the distal end wall is axially recessed within the swirler from the distal outer wall end. The fuel nozzle projects into the inner passage.

    FUEL INJECTOR ASSEMBLY FOR GAS TURBINE ENGINE
    2.
    发明公开
    FUEL INJECTOR ASSEMBLY FOR GAS TURBINE ENGINE 审中-公开

    公开(公告)号：US20240159398A1

    公开(公告)日：2024-05-16

    申请号：US17985863

    申请日：2022-11-13

    Applicant: Raytheon Technologies Corporation

    Inventor： Zhongtao Dai ,  Wookyung Kim ,  Stephen K. Kramer ,  Baris A. Sen ,  Gary J. Dillard

    IPC: F23R3/28 ,  F02C7/22

    CPC classification number: F23R3/28 ,  F02C7/22

    Abstract: An assembly is provided for a gas turbine engine. This engine assembly includes a fuel injector assembly, and the fuel injector assembly includes a fuel swirler and an air swirler. The fuel swirler is configured to swirl fuel in a direction about the axis to provide swirled fuel. The fuel injector assembly is configured to inject the swirled fuel as an annular fuel flow along an axis. The air swirler is configured to swirl air in the direction about the axis to provide swirled air. The fuel injector assembly is configured to inject the swirled air as an annular air flow along the axis, adjacent and circumscribing the annular fuel flow.

    TURBINE ENGINE COMBUSTOR WALL WITH APERTURE DEFLECTOR
    4.
    发明公开
    TURBINE ENGINE COMBUSTOR WALL WITH APERTURE DEFLECTOR 审中-公开

    公开(公告)号：US20240302042A1

    公开(公告)日：2024-09-12

    申请号：US18117924

    申请日：2023-03-06

    Applicant: Raytheon Technologies Corporation

    Inventor： Ian Walters ,  Stephen K. Kramer ,  Baris A. Sen ,  Gary J. Dillard ,  Eunice Allen-Bradley

    IPC: F23R3/00

    CPC classification number: F23R3/002

    Abstract: An apparatus is provided for a turbine engine. This turbine engine apparatus includes a combustor wall, and the combustor wall includes a panel, a deflector and a quench aperture that extends along an aperture centerline through the combustor wall to an aperture outlet into a combustion chamber. The panel extends axially along and circumferentially about an axis. The panel extends radially between a first panel side and a second panel side. The first panel side forms a peripheral boundary of the combustion chamber. The panel forms a downstream side of the aperture outlet at the first panel side. The deflector projects out from the panel at the first panel side into the combustion chamber. The deflector forms an upstream side of the aperture outlet.

    FUEL INJECTOR AIR SWIRLER STRUCTURE WITH CANTED FLOW GUIDE SURFACE
    5.
    发明公开
    FUEL INJECTOR AIR SWIRLER STRUCTURE WITH CANTED FLOW GUIDE SURFACE 审中-公开

    公开(公告)号：US20240288169A1

    公开(公告)日：2024-08-29

    申请号：US18114691

    申请日：2023-02-27

    Applicant: Raytheon Technologies Corporation

    Inventor： Baris A. Sen ,  Andrew W. Justice ,  Stephen K. Kramer ,  Gary J. Dillard

    IPC: F23R3/28 ,  F02C7/232

    CPC classification number: F23R3/286 ,  F02C7/232 ,  F05D2220/32 ,  F05D2240/36

    Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes an air swirler structure, an injector nozzle and a nozzle guide. The air swirler structure includes a swirler wall, an inner passage and an air swirler passage. The swirler wall includes a flow guide surface. At least an inner portion of the flow guide surface has a frustoconical geometry. The inner passage extends axially along an axis within the air swirler structure to a swirler outlet. The air swirler passage extends radially into the air swirler structure, longitudinally along the flow guide surface and to the inner passage. The injector nozzle projects axially into the inner passage. The nozzle guide couples the injector nozzle to the air swirler structure. The nozzle guide is axially abutted against the swirler wall.

Patent Agency Ranking