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    COMBUSTOR PANELS FOR GAS TURBINE ENGINES
    31.
    发明申请
    COMBUSTOR PANELS FOR GAS TURBINE ENGINES 有权

    公开(公告)号：US20210025591A1

    公开(公告)日：2021-01-28

    申请号：US16519518

    申请日：2019-07-23

    Applicant: United Technologies Corporation

    Inventor： Thomas Pritchard ,  Stephen K. Kramer

    IPC: F23R3/00 ,  F23R3/06

    Abstract: Combustor panels of gas turbine engines and gas turbine engines are described. The combustor panels include a hot side configured to be exposed to combustion within a gas turbine engine, a cold side opposite the hot side of the combustor panel, the cold side configured to receive cooling flow thereon, and a peak-valley gridded pattern formed on the cold side, the peak-valley gridded pattern comprising a plurality of recessed cells arranged in a grid pattern, with each recessed cell having a peak, angled sidewalls, and an effusion hole located at a bottom of the angled sidewalls.

    AERATING FUEL INJECTOR SYSTEM FOR A GAS TURBINE ENGINE
    33.
    发明申请
    AERATING FUEL INJECTOR SYSTEM FOR A GAS TURBINE ENGINE 审中-公开
    燃气涡轮发动机的燃油喷射系统

    公开(公告)号：US20160010866A1

    公开(公告)日：2016-01-14

    申请号：US14768995

    申请日：2014-02-19

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Ken F. Blaney ,  Stephen K. Kramer

    IPC: F23R3/28

    Abstract: An aeration system for a fuel injector system of a gas turbine engine includes a air tank in communication with a fuel injector and method of operation thereof.

    Abstract translation: 燃气涡轮发动机的燃料喷射器系统的曝气系统包括与燃料喷射器连通的空气罐及其操作方法。

    SELECTIVELY DEOXYGENATED STORED FUEL SYSTEM
    34.
    发明申请
    SELECTIVELY DEOXYGENATED STORED FUEL SYSTEM 审中-公开
    选择性脱氧储存燃料系统

    公开(公告)号：US20150204244A1

    公开(公告)日：2015-07-23

    申请号：US14599855

    申请日：2015-01-19

    Applicant: United Technologies Corporation

    Inventor： Alexander W. Williams ,  Stephen K. Kramer

    IPC: F02C7/232

    CPC classification number: F02C7/232 ,  F02C7/22 ,  F02C9/40 ,  F05D2260/607 ,  F05D2260/95 ,  F23D2900/00016 ,  F23K5/04 ,  F23K5/08 ,  F23R2900/00004 ,  Y02T50/671 ,  Y02T50/675

    Abstract: A gas turbine engine includes a multi-stage fuel injection system including at least a first fuel injection stage and a second fuel injection stage, a first fuel reservoir fluidly connected to the first fuel injection stage and fluidly connected to a selective valve, and a second fuel reservoir fluidly connected to the selective valve. The selective valve connects one of the first fuel reservoir and the second fuel reservoir to the second fuel injection stage.

    Abstract translation: 燃气涡轮发动机包括多级燃料喷射系统，其包括至少第一燃料喷射级和第二燃料喷射级，流体连接到第一燃料喷射级并且流体地连接到选择阀的第一燃料储存器， 燃油箱与选择阀流体连接。 选择阀将第一燃料储存器和第二燃料储存器中的一个连接到第二燃料喷射级。

    Combustor liner attachment assembly for gas turbine engine
    35.
    发明授权
    Combustor liner attachment assembly for gas turbine engine 有权

    公开(公告)号：US11255547B2

    公开(公告)日：2022-02-22

    申请号：US16160321

    申请日：2018-10-15

    Applicant: United Technologies Corporation

    Inventor： Kevin W. White ,  Stephen K. Kramer

    IPC: F23R3/60 ,  F02C3/14 ,  F16B5/02 ,  F23R3/00 ,  F02C7/20

    Abstract: A combustor liner panel attachment assembly includes a liner extending from a first end to a second end, and circumferentially to partially define a combustion zone. The assembly also includes a spring element located adjacent to a portion of the liner and operatively coupled to a stationary structure, the spring element having a recessed segment. The assembly further includes a protrusion feature extending radially outwardly from the liner, the protrusion feature disposed within the recessed segment of the spring element to axially retain the liner.

    Mounting a ceramic component to a non-ceramic component in a gas turbine engine
    36.
    发明授权
    Mounting a ceramic component to a non-ceramic component in a gas turbine engine 有权

    公开(公告)号：US11215367B2

    公开(公告)日：2022-01-04

    申请号：US16591841

    申请日：2019-10-03

    Applicant: United Technologies Corporation

    Inventor： Stephen K. Kramer

    IPC: F23R3/60 ,  F23R3/00

    Abstract: A combustor with a centerline is provided that includes a support structure and a heat shield. The heat shield extends circumferentially about and axially along the centerline. The heat shield is configured from or otherwise includes ceramic material. The heat shield is mounted to the support structure by an interlocking joint connection. The interlocking joint connection includes a projection and a groove. The projection is configured with the support structure and includes a plurality of fingers arranged along and projecting into the groove. The groove is formed in the heat shield.

    MODULATED COMBUSTOR BYPASS AND COMBUSTOR BYPASS VALVE
    39.
    发明申请
    MODULATED COMBUSTOR BYPASS AND COMBUSTOR BYPASS VALVE 审中-公开

    公开(公告)号：US20190211751A1

    公开(公告)日：2019-07-11

    申请号：US15864266

    申请日：2018-01-08

    Applicant: United Technologies Corporation

    Inventor： Anton G. Banks ,  Stephen K. Kramer

    IPC: F02C9/18 ,  F23R3/26 ,  F02C9/22

    CPC classification number: F02C9/18 ,  F01D17/145 ,  F01D17/162 ,  F05D2240/35 ,  F23R3/26

    Abstract: A combustor section of a gas turbine engine includes a combustor having a combustor inlet, and a combustor bypass passage having a passage inlet located upstream of the combustor inlet, the combustor bypass passage configured to divert a selected bypass airflow around the combustor. A combustor bypass valve is located at the combustor bypass passage to control the selected bypass airflow along the combustor bypass passage. The combustor bypass valve including a valve element configured to rotate about an engine central longitudinal axis A to move one or more valve openings relative to one or more bypass passage openings.

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