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    GAS TURBINE ENGINE WALL ASSEMBLY INTERFACE
    3.
    发明公开
    GAS TURBINE ENGINE WALL ASSEMBLY INTERFACE 审中-公开
    新加坡国立大学GASTURBINENMOTORWANDANORDNUNG

    公开(公告)号：EP3077729A4

    公开(公告)日：2017-01-11

    申请号：EP14867187

    申请日：2014-08-29

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： BANGERTER JAMES P ,  RUSSO THOMAS R ,  HANSON RUSSELL B ,  LOW KEVIN J

    IPC: F23R3/42 ,  F02C3/14 ,  F02C7/24 ,  F02K1/82 ,  F23M5/04 ,  F23R3/00 ,  F23R3/06 ,  F23R3/60

    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; 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。 还提供了组装在燃气涡轮发动机内的壁组件的方法。 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。

    SWEPT COMBUSTOR LINER PANELS FOR GAS TURBINE ENGINE COMBUSTOR
    8.
    发明公开
    SWEPT COMBUSTOR LINER PANELS FOR GAS TURBINE ENGINE COMBUSTOR 审中-公开
    用于燃气轮机燃烧室的弯曲燃烧壁板

    公开(公告)号：EP3071884A4

    公开(公告)日：2016-12-21

    申请号：EP14862049

    申请日：2014-11-18

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： MAX SETH A ,  LOW KEVIN J

    IPC: F23M5/00 ,  F02C3/14 ,  F02C7/24 ,  F23R3/42

    CPC classification number: F23R3/002 ,  F23R3/58

    Abstract: A liner panel is provided for use in a combustor of a gas turbine engine. The liner panel includes a first liner panel side edge between a liner panel aft edge and a liner panel forward edge. The liner panel also includes a second liner panel side edge between the liner panel aft edge and the liner panel forward edge. The first and the second liner panel side edges are non-perpendicular to the liner panel forward and aft edge edges.

    GAS TURBINE ENGINE COMBUSTOR BULKHEAD ASSEMBLY
    10.
    发明公开
    GAS TURBINE ENGINE COMBUSTOR BULKHEAD ASSEMBLY 审中-公开
    用于燃气轮机的SCHOTT安装

    公开(公告)号：EP3033574A4

    公开(公告)日：2016-08-17

    申请号：EP14836240

    申请日：2014-08-13

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： LOW KEVIN J ,  ERBAS-SEN NURHAK

    IPC: F23R3/10 ,  F02C3/14 ,  F02C7/22 ,  F23R3/12 ,  F23R3/50 ,  F23R3/60

    CPC classification number: F23R3/06 ,  F02C7/18 ,  F05D2260/201 ,  F23R3/002 ,  F23R3/12 ,  F23R3/50 ,  F23R3/60 ,  F23R2900/03042 ,  F23R2900/03044 ,  Y02T50/675

    Abstract: A bulkhead assembly for a combustor of a gas turbine engine includes a bulkhead support shell with a multiple of swirler openings. Each of the multiple of swirler openings is surrounded by a first multiple of cooling impingement passages that define an angle α with respect to a hot side of the bulkhead support shell and a second multiple of cooling impingement passages that define an angle &bgr; with respect to the hot side of the bulkhead support shell. The angle α is different than the angle &bgr;.

    Abstract translation: 用于燃气涡轮发动机的燃烧器的隔板组件包括具有多个旋流器开口的隔板支撑壳体。 多个旋流器开口中的每一个被第一多个冷却冲击通道围绕，该第一多个冷却冲击通道相对于隔板支撑壳体的热侧限定角度α，以及限定角度＆bgr的第二多个冷却冲击通道; 相对于舱壁支撑壳的热侧。 角度α与角度bgr不同。

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