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    CO-SWIRL ORIENTATION OF COMBUSTOR EFFUSION PASSAGES FOR GAS TURBINE ENGINE COMBUSTOR
    32.
    发明申请
    CO-SWIRL ORIENTATION OF COMBUSTOR EFFUSION PASSAGES FOR GAS TURBINE ENGINE COMBUSTOR 审中-公开
    燃气轮机发动机燃油通风的CO-SWIRL方向

    公开(公告)号：US20160281988A1

    公开(公告)日：2016-09-29

    申请号：US15037484

    申请日：2014-12-03

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： John S. Tu, JR. ,  Timothy S. Snyder ,  James B. Hoke ,  James P. Bangerter ,  Dennis J. Duhamel ,  David A. Burns

    IPC: F23R3/06 ,  F23R3/00

    CPC classification number: F23R3/06 ,  F23R3/002 ,  F23R2900/03041 ,  F23R2900/03044 ,  Y02T50/675

    Abstract: A liner panel for use in a combustor for a gas turbine engine includes a forward region including a multiple of effusion passages each directed at an orientation consistent with a local swirl direction of combustion gases. Another liner panel for use in a combustor for a gas turbine engine includes a forward region forward of a dilution passage and an aft region aft of the forward region. The forward region includes a multiple of effusion passages each directed generally circumferentially. The aft region includes a multiple of effusion passages each directed at an orientation generally axially. A method of cooling a wall assembly within a combustor of a gas turbine engine includes orienting a multiple of effusion passages within a forward region consistent with a local swirl direction of combustion gases.

    Abstract translation: 用于燃气涡轮发动机的燃烧器中的衬板包括一个包括多个喷射通道的前部区域，每个喷射通道以与燃烧气体的局部涡流方向一致的方向指向。 用于燃气涡轮发动机的燃烧器中的另一衬里面板包括稀释通道前方的前部区域和前部区域的尾部后部区域。 前部区域包括多个通常沿周向引导的排出通道。 后部区域包括多个通过轴向大体定向的排出通道。 一种冷却燃气涡轮发动机的燃烧器内的壁组件的方法包括在与燃烧气体的局部涡流方向一致的前向区域内定向多个排出通道。

    LOW NET-SWIRL CONFIGURATIONS FOR GAS TURBINE ENGINE COMBUSTORS
    33.
    发明申请
    LOW NET-SWIRL CONFIGURATIONS FOR GAS TURBINE ENGINE COMBUSTORS 审中-公开
    用于气体涡轮发动机燃烧器的低网速配置

    公开(公告)号：US20160258627A1

    公开(公告)日：2016-09-08

    申请号：US14636689

    申请日：2015-03-03

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Albert K. Cheung ,  Zhongtao Dai ,  James B. Hoke

    IPC: F23R3/14 ,  F23R3/28

    CPC classification number: F23R3/14 ,  F23C7/004 ,  F23R3/06 ,  F23R3/286

    Abstract: The present disclosure relates to gas turbine engines, and in particular to combustor swirlers and swirler configurations. In one embodiment, a swirler includes an inner passage for receiving a fuel injector and a plurality of outer passages concentrically arranged around the inner passage. The plurality of outer passages include an outer vane assembly including a plurality of vane elements arranged at a first angle and a first middle vane assembly include a plurality of vane elements arranged at a second angle, wherein the outer vane assembly is concentrically arranged around the first middle vane assembly, and wherein the outer vane assembly and first middle vane assembly are configured to produce a low net-swirl to control the penetration depth and improve premixing of a fuel air mixture for the fuel injector. According to another embodiment, the swirler includes a second middle vane assembly include a plurality of vane elements arranged at a third angle.

    Abstract translation: 本公开涉及燃气涡轮发动机，特别涉及燃烧器旋流器和旋流器构造。 在一个实施例中，旋流器包括用于接收燃料喷射器的内部通道和围绕内部通道同心地布置的多个外部通道。 多个外部通道包括外部叶片组件，该外部叶片组件包括以第一角度布置的多个叶片元件，第一中间叶片组件包括以第二角度布置的多个叶片元件，其中外部叶片组件围绕第一角度同心地布置 中间叶片组件，并且其中外部叶片组件和第一中间叶片组件构造成产生低的网络涡流以控制穿透深度并改善用于燃料喷射器的燃料空气混合物的预混合。 根据另一个实施例，旋流器包括第二中间叶片组件，其包括以第三角度布置的多个叶片元件。

    HYBRID THROUGH HOLES AND ANGLED HOLES FOR COMBUSTOR GROMMET COOLING
    34.
    发明申请
    HYBRID THROUGH HOLES AND ANGLED HOLES FOR COMBUSTOR GROMMET COOLING 审中-公开
    通过螺栓和螺栓固定用于燃烧器冷却

    公开(公告)号：US20160201913A1

    公开(公告)日：2016-07-14

    申请号：US14886973

    申请日：2015-10-19

    Applicant: United Technologies Corporation

    Inventor： John S. Tu ,  James B. Hoke ,  Monica Pacheco-Tougas ,  Timothy S. Snyder ,  Dennis M. Moura ,  Anthony Van

    IPC: F23R3/06 ,  F23R3/00

    CPC classification number: F23R3/06 ,  F23R3/002 ,  F23R2900/03042 ,  F23R2900/03044 ,  Y02T50/675

    Abstract: Aspects of the disclosure are directed to a cooling design feature for inclusion in a liner of an aircraft, comprising: a plurality of angled holes, and at least one through hole separating all combinations of any two of the angled holes, wherein the at least one through hole is oriented at an angle that is substantially perpendicular to a surface of the liner, and wherein each of the plurality of angled holes are non-parallel to the at least one through hole.

    Abstract translation: 本公开的方面涉及一种用于包含在飞行器的衬套中的冷却设计特征，包括：多个成角度的孔，以及分开任何两个成角度孔的所有组合的至少一个通孔，其中所述至少一个 通孔以基本上垂直于衬套的表面的角度定向，并且其中多个成角度孔中的每一个不平行于至少一个通孔。

    IMPINGEMENT FILM-COOLED FLOATWALL WITH BACKSIDE FEATURE
    35.
    发明申请
    IMPINGEMENT FILM-COOLED FLOATWALL WITH BACKSIDE FEATURE 审中-公开
    带背光功能的薄膜冷却浮筒

    公开(公告)号：US20160131365A1

    公开(公告)日：2016-05-12

    申请号：US14935076

    申请日：2015-11-06

    Applicant: United Technologies Corporation

    Inventor： John S. Tu ,  James B. Hoke ,  Monica Pacheco-Tougas ,  Alexander W. Williams

    IPC: F23R3/16 ,  B64D27/10 ,  F02C7/18

    Abstract: Aspects of the disclosure are directed to a liner associated with an engine of an aircraft. The liner includes a panel and an array of projections configured to enhance a cooling of the panel and distributed on at least part of a first side of the panel that corresponds to a cold side of the panel.

    Abstract translation: 本公开的方面涉及与飞行器的发动机相关联的衬管。 该衬套包括一个面板和一组凸起，其被构造成增强面板的冷却并且分布在对应于面板的冷侧的面板的第一侧的至少一部分上。

    Gas turbine combustor with liner air admission holes associated with interpersed main and pilot swirler assemblies
    37.
    发明授权
    Gas turbine combustor with liner air admission holes associated with interpersed main and pilot swirler assemblies 有权
    燃气轮机燃烧器具有与间接的主和先导式旋流器组件相关联的衬管进气孔

    公开(公告)号：US08789374B2

    公开(公告)日：2014-07-29

    申请号：US13761454

    申请日：2013-02-07

    Applicant: United Technologies Corporation

    Inventor： James B. Hoke

    IPC: F02C1/00 ,  F02G3/00

    CPC classification number: F23R3/14 ,  F23R3/06 ,  F23R3/343 ,  F23R3/50 ,  Y02T50/675

    Abstract: A combustor for a gas turbine engine having an annular combustion chamber includes a plurality of main fuel injection and air swirler assemblies and a plurality of pilot fuel injection and air swirler assemblies disposed in a circumferential ring extending about the circumferential expanse of a forward bulkhead. The plurality of pilot fuel injection and air swirler assemblies are interspersed amongst and disposed in the circumferential ring of main fuel injection and air swirler assemblies. Fuel being supplied to the combustor is selectively distributed between the plurality of main fuel injection and air swirler assemblies and the plurality of pilot fuel injection and air swirler assemblies in response to the level of power demand on the gas turbine engine.

    Abstract translation: 用于具有环形燃烧室的燃气涡轮发动机的燃烧器包括多个主燃料喷射和空气旋流器组件和多个引燃燃料喷射和空气旋流器组件，其设置在围绕前舱壁的周向延伸部延伸的周向环中。 多个先导燃料喷射和空气旋流器组件散布在主燃料喷射和空气旋流器组件的周向环中并且布置在其中。 响应于燃气涡轮发动机的功率需求水平，被供应到燃烧器的燃料被选择性地分布在多个主燃料喷射和空气旋流器组件和多个先导燃料喷射和空气旋流器组件之间。

    EFFUSION COOLING FOR DILUTION/QUENCH HOLE EDGES IN COMBUSTOR LINER PANELS
    39.
    发明申请
    EFFUSION COOLING FOR DILUTION/QUENCH HOLE EDGES IN COMBUSTOR LINER PANELS 有权

    公开(公告)号：US20210018173A1

    公开(公告)日：2021-01-21

    申请号：US16513477

    申请日：2019-07-16

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Fumitaka Ichihashi ,  James B. Hoke

    IPC: F23R3/00

    Abstract: A gas turbine engine component includes a first surface and a second surface. The component further includes a dilution hole defined by the first surface and the second surface. The component further includes a first effusion hole and a second effusion hole each having an inlet defined by the second surface and an outlet defined by the first surface such that the outlet of the first effusion hole is located nearer to the dilution hole than the outlet of the second effusion hole.

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