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    GAS TURBINE ENGINE COMBUSTOR BULKHEAD ASSEMBLY
    2.
    发明申请
    GAS TURBINE ENGINE COMBUSTOR BULKHEAD ASSEMBLY 审中-公开
    气体涡轮发动机燃烧器大容量组件

    公开(公告)号：US20160169516A1

    公开(公告)日：2016-06-16

    申请号：US14908830

    申请日：2014-08-13

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Kevin J. Low ,  Nurhak Erbas-Sen

    IPC: F23R3/06 ,  F23R3/00 ,  F02C7/18

    CPC classification number: F23R3/06 ,  F02C3/14 ,  F02C7/18 ,  F05D2260/201 ,  F23R3/002 ,  F23R3/02 ,  F23R3/10 ,  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 β with respect to the hot side of the bulkhead support shell. The angle α is different than the angle β.

    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包围，该第一多个冷却冲击通道相对于舱壁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。

    GAS TURBINE ENGINE WALL ASSEMBLY WITH OFFSET RAIL
    5.
    发明申请
    GAS TURBINE ENGINE WALL ASSEMBLY WITH OFFSET RAIL 审中-公开
    气体涡轮发动机壁组件与偏心轨道

    公开(公告)号：US20160265784A1

    公开(公告)日：2016-09-15

    申请号：US15032354

    申请日：2014-08-29

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： James P. Bangerter ,  Kevin J. Low

    IPC: F23R3/60 ,  F02C7/12 ,  F23R3/00

    Abstract: A liner panel within a gas turbine engine includes a perimeter rail that defines a first height from a cold side. The liner panel also includes an intermediate rail that defines a second height from the cold side, where the second height is less than the first height.

    Abstract translation: 燃气涡轮发动机内的衬板包括从冷侧限定第一高度的周边轨道。 衬板还包括中间轨道，该中间轨道从冷侧限定第二高度，其中第二高度小于第一高度。

    GAS TURBINE ENGINE WALL ASSEMBLY INTERFACE
    7.
    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。

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