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    System for actuating an exhaust cowl
    1.
    发明授权
    System for actuating an exhaust cowl 有权

    公开(公告)号：US10371089B2

    公开(公告)日：2019-08-06

    申请号：US14600824

    申请日：2015-01-20

    Applicant: United Technologies Corporation

    Inventor： Donald W. Peters ,  James P. Bangerter

    IPC: F02K1/06 ,  F02C3/10 ,  F01D25/24 ,  F16H21/04 ,  F16H21/54 ,  F02K1/09 ,  F02K1/15 ,  F02K1/12 ,  F02K1/10

    Abstract: In various embodiments, a cowl actuation system may comprise a cowl, an actuator, a bell crank, and a guide arm. The cowl may be configured to modulate at least a portion of the exhaust flow of a gas turbine engine. The bell crank may have a first end and a second end. The first end may be operatively coupled to the actuator. The second end may be operatively coupled to the cowl. The bell crank may be configured to pivot about a first point located between the first end and the second end. The first point may also be located along a diameter. The guide arm may have a third end and a fourth end. The third end may be mounted to a second point. The fourth end may be operatively coupled to the cowl. The second point may be located along the diameter.

    COOLED POCKET IN A TURBINE VANE PLATFORM
    2.
    发明申请
    COOLED POCKET IN A TURBINE VANE PLATFORM 审中-公开
    冷却水箱在涡轮机平台

    公开(公告)号：US20160160652A1

    公开(公告)日：2016-06-09

    申请号：US14751192

    申请日：2015-06-26

    Applicant: United Technologies Corporation

    Inventor： James P. Bangerter ,  Corneil S. Paauwe

    IPC: F01D5/18

    CPC classification number: F01D5/18 ,  F01D9/041 ,  F05D2240/81 ,  Y02T50/676

    Abstract: An airfoil includes a platform including a pocket, a continuous solid cover plate bonded over the pocket, and a plurality of apertures in the platform in fluid communication with the pocket and adjacent the continuous solid cover plate. A gas turbine engine including the airfoil and a method of cooling an article of a gas turbine engine are also disclosed.

    Abstract translation: 机翼包括平台，其包括口袋，连接在口袋上的连续固体盖板以及平台中的与口袋流体连通且与连续固体盖板相邻的多个孔。 还公开了一种包括翼型的燃气涡轮发动机和一种冷却燃气涡轮发动机的物品的方法。

    CO-SWIRL ORIENTATION OF COMBUSTOR EFFUSION PASSAGES FOR GAS TURBINE ENGINE COMBUSTOR
    7.
    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。

    GAS TURBINE ENGINE WALL ASSEMBLY WITH SUPPORT SHELL CONTOUR REGIONS
    8.
    发明申请
    GAS TURBINE ENGINE WALL ASSEMBLY WITH SUPPORT SHELL CONTOUR REGIONS 审中-公开
    气体涡轮发动机壁组件与支撑壳体区域

    公开(公告)号：US20160201909A1

    公开(公告)日：2016-07-14

    申请号：US14910964

    申请日：2014-08-29

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： James P. Bangerter ,  Kevin J. Low ,  Russell B. Hanson ,  Nurhak Erbas-Sen ,  Frank J. Cunha

    IPC: F23R3/00 ,  F23R3/60 ,  F23R3/06

    Abstract: A wall assembly for a combustor of a gas turbine engine is provided. The wall assembly includes a support shell with a contoured region to define at least one convergent passage between the support shell and a multiple of liner panels. A method of cooling a wall assembly for a combustor of a gas turbine engine is also provided. This method includes a step of directing cooling air into at least one convergent passage between the support shell and a multiple of liner panels.

    Abstract translation: 提供了一种用于燃气涡轮发动机的燃烧器的壁组件。 壁组件包括具有轮廓区域的支撑壳体，以在支撑壳体和多个衬板之间限定至少一个会聚通道。 还提供了一种冷却燃气涡轮发动机的燃烧器的壁组件的方法。 该方法包括将冷却空气引导到支撑壳和多个衬板之间的至少一个会聚通道的步骤。

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