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    Airblast fuel nozzle
    1.
    发明授权
    Airblast fuel nozzle 有权

    公开(公告)号：US11655979B2

    公开(公告)日：2023-05-23

    申请号：US17841210

    申请日：2022-06-15

    申请人： Parker-Hannifin Corporation

    发明人： Luther Wirtz ,  Jeffrey Lehtinen ,  Adel Mansour ,  David Tibbs ,  Robert Pelletier ,  Jon Stockill

    IPC分类号： F23R3/14 ,  F23R3/12 ,  F23R3/28

    CPC分类号： F23R3/12 ,  F23R3/14 ,  F23R3/28 ,  F23R2900/00005

    摘要： A fuel injector for a gas turbine engine of an aircraft having a fuel nozzle including a fuel swirler and/or an outer air swirler. The fuel swirler may include a manifold for receiving fuel from a fuel conduit, and a plurality of fuel passages to direct fuel from the manifold to discharge orifices that direct fuel with swirling flow. The fuel swirler may be configured to provide uniform spray while minimizing recirculation zones; reduce residence time as fuel enters the manifold; minimize flow disruptions, boundary layer growth, and/or pressure drop as fuel flows through the fuel passages; reduces coking internally of the nozzle; reduces thermal stresses; and is simple and low-cost to manufacture. The outer air swirler may include first and second outer air swirler portions with respective vanes and air passages that provide swirling air flow. The outer air swirler may be configured to improve atomization and spray uniformity with a wide spray angle; and minimize flow disruptions for enhancing flow performance.

    Combustor Assembly for a Turbine Engine
    2.
    发明申请
    Combustor Assembly for a Turbine Engine 审中-公开

    公开(公告)号：US20190203940A1

    公开(公告)日：2019-07-04

    申请号：US15860835

    申请日：2018-01-03

    申请人： General Electric Company

    发明人： Michael Alan Stieg ,  Nicholas John Bloom ,  Brett Joseph Geiser

    IPC分类号： F23R3/04 ,  F23R3/00

    CPC分类号： F23R3/04 ,  F23R3/007 ,  F23R2900/00005 ,  F23R2900/03044

    摘要： A combustor assembly for a gas turbine engine includes a dome defining a slot. The combustor assembly also includes a liner at least partially defining a combustion chamber and extending between an aft end and a forward end. The forward end is received within the slot of the dome. In one aspect, the forward end of the liner defines blind warming openings that allow a warming airflow to actively warm the forward end during transient operation of the engine. In another aspect, the dome defines a plurality of impingement openings that allow a warming airflow to impinge on the forward end to actively warm the liner during transient operation of the engine. In another aspect, a grommet coupling a pin with the liner defines a plurality of warming passages that allow a warming airflow to flow therethrough to warm the forward end of the liner during transient engine operation.

    PREMIXED FUEL NOZZLE
    3.
    发明申请
    PREMIXED FUEL NOZZLE 审中-公开

    公开(公告)号：US20190093895A1

    公开(公告)日：2019-03-28

    申请号：US15718077

    申请日：2017-09-28

    申请人： General Electric Company

    发明人： David Albin Lind ,  Gregory Allen Boardman

    IPC分类号： F23R3/28 ,  F23R3/04

    CPC分类号： F23R3/286 ,  F23D2900/00014 ,  F23D2900/00015 ,  F23R3/045 ,  F23R3/343 ,  F23R2900/00005 ,  F23R2900/00014

    摘要： The present disclosure is directed to a fuel injector assembly and a gas turbine engine including the fuel injector assembly. The fuel injector assembly includes a centerbody extended along a lengthwise direction. The centerbody defines a first fuel nozzle. An annular shroud defining a second fuel nozzle surrounds the centerbody and is extended along the lengthwise direction. A passage is defined through the annular shroud and extended generally along the lengthwise direction. The passage defines an exit opening disposed at a downstream end adjacent to the combustion chamber and in fluid communication therewith. The annular shroud defines a fuel inlet opening disposed at an upstream end of the passage. The annular shroud further defines an air inlet opening in fluid communication with the passage. The air inlet opening is disposed between the fuel inlet opening and the exit opening.

    COMBUSTION CHAMBER
    9.
    发明申请
    COMBUSTION CHAMBER 审中-公开

    公开(公告)号：US20180031242A1

    公开(公告)日：2018-02-01

    申请号：US15637209

    申请日：2017-06-29

    申请人： ROLLS-ROYCE plc

    发明人： Stephen C. HARDING ,  Paul A. HUCKER

    IPC分类号： F23R3/20 ,  F23R3/60 ,  F23R3/44 ,  F23R3/46 ,  F23R3/08 ,  F23R3/00

    CPC分类号： F23R3/20 ,  F23R3/002 ,  F23R3/08 ,  F23R3/44 ,  F23R3/46 ,  F23R3/60 ,  F23R2900/00005

    摘要： A gas turbine engine combustion chamber comprises upstream and downstream ring structures and a plurality of circumferentially arranged combustion chamber segments. Each segment extends the full length of the combustion chamber and each segment is secured to the upstream ring structure and is mounted on the downstream ring structure. The upstream end of each combustion chamber segment comprises a surface having a plurality of circumferentially spaced radially extending holes and the upstream ring structure having a plurality of circumferentially spaced holes extending radially through a portion abutting the surface of the upstream end of each combustion chamber segment. Each combustion chamber segment being removably secured to the upstream ring structure by a plurality of fasteners locatable in the holes in the combustion chamber segment and corresponding holes in the upstream ring structure.