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    Co-swirl orientation of combustor effusion passages for gas turbine engine combustor
    22.
    发明授权
    Co-swirl orientation of combustor effusion passages for gas turbine engine combustor 有权

    公开(公告)号：US10317080B2

    公开(公告)日：2019-06-11

    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: F23R3/00 ,  F23R3/06

    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.

    GAS TURBINE ENGINE WALL ASSEMBLY INTERFACE
    25.
    发明申请
    GAS TURBINE ENGINE WALL ASSEMBLY INTERFACE 审中-公开
    气体涡轮发动机壁组件接口

    公开(公告)号：US20160377296A1

    公开(公告)日：2016-12-29

    申请号：US15038847

    申请日：2014-08-29

    Applicant: United Technologies Corporation

    Inventor： James P. Bangerter ,  Thomas R. Russo ,  Russell B. Hanson ,  Kevin J. Low

    IPC: F23R3/60 ,  F02K1/82 ,  F23R3/06 ,  F23M5/04 ,  F02C3/04 ,  F02C7/24 ,  F23R3/00

    CPC classification number: F23R3/60 ,  F02C3/04 ,  F02C7/24 ,  F02K1/822 ,  F05D2260/30 ,  F23M5/04 ,  F23R3/002 ,  F23R3/06 ,  F23R2900/00018 ,  F23R2900/03042 ,  Y02T50/675

    Abstract: A wall assembly is provided for a gas turbine engine. This wall assembly includes a support shell with a contoured region; and a multiple of liner panels mounted to the support shell. At least one of the multiple of liner panels includes an end rail. The contoured region is deformable to selectively contact at least a portion of the end rail. A method of assembling a wall assembly within a gas turbine engine is also provided. This method includes locating a stud that extends from a cold side of a liner panel through a support shell; and attaching a fastener onto the stud to at least partially close a gap defined between the panel and shell.

    Abstract translation: 为燃气涡轮发动机提供壁组件。 该壁组件包括具有轮廓区域的支撑壳体; 以及安装到支撑壳体上的多个衬板。 多个衬板中的至少一个包括端轨。 轮廓区域可变形以选择性地接触端轨的至少一部分。 还提供了一种在燃气涡轮发动机内组装壁组件的方法。 该方法包括定位从衬板的冷侧延伸穿过支撑壳的螺柱; 以及将紧固件附接到所述螺柱上以至少部分地闭合限定在所述面板和壳体之间的间隙。

    SYSTEM FOR ACTUATING AN EXHAUST COWL
    27.
    发明申请
    SYSTEM FOR ACTUATING AN EXHAUST COWL 审中-公开
    用于执行排气的系统

    公开(公告)号：US20160208737A1

    公开(公告)日：2016-07-21

    申请号：US14600824

    申请日：2015-01-20

    Applicant: United Technologies Corporation

    Inventor： Donald W. Peters ,  James P. Bangerter

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

    CPC classification number: F02K1/06 ,  F01D25/24 ,  F02C3/10 ,  F02K1/09 ,  F02K1/10 ,  F02K1/1261 ,  F02K1/15 ,  F16H21/04 ,  F16H21/54

    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.

    Abstract translation: 在各种实施例中，整流罩致动系统可以包括整流罩，致动器，钟形曲柄和引导臂。 整流罩可以构造成调制燃气涡轮发动机的排气流的至少一部分。 钟形曲柄可以具有第一端和第二端。 第一端可以可操作地联接到致动器。 第二端可以可操作地联接到整流罩。 钟形曲柄可以被配置为围绕位于第一端和第二端之间的第一点枢转。 第一点也可以沿直径定位。 引导臂可以具有第三端和第四端。 第三端可以安装到第二点。 第四端可以可操作地联接到整流罩。 第二点可以沿直径定位。

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