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    CO-SWIRL ORIENTATION OF COMBUSTOR EFFUSION PASSAGES FOR GAS TURBINE ENGINE COMBUSTOR
    1.
    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：WO2015126501A3

    公开(公告)日：2015-10-22

    申请号：PCT/US2014068377

    申请日：2014-12-03

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： TU JOHN S ,  SNYDER TIMOTHY S ,  HOKE JAMES B ,  BANGERTER JAMES P ,  DUHAMEL DENNIS J ,  BURNS DAVID A

    IPC: F23R3/12 ,  F23R3/26 ,  F23R3/42

    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套面板包括稀释通道前方的前部区域和前部区域的后部后部区域。 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致定向的排出通道。 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 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。

    TURBINE ENGINE COMBUSTOR AND STATOR VANE ASSEMBLY
    4.
    发明公开
    TURBINE ENGINE COMBUSTOR AND STATOR VANE ASSEMBLY 审中-公开
    TURBINENBRENNKAMMER UND LEI​​TSCHAUFELANORDNUNG

    公开(公告)号：EP2877726A4

    公开(公告)日：2016-08-03

    申请号：EP13822793

    申请日：2013-07-29

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： BANGERTER JAMES P ,  DUHAMEL DENNIS J ,  SONNTAG ROBERT M ,  REZVANI REZA

    IPC: F02C3/14 ,  F01D9/02 ,  F02C7/00 ,  F02C7/20 ,  F23R3/00 ,  F23R3/06 ,  F23R3/50

    CPC classification number: F01D9/023 ,  F05D2260/202 ,  F23R3/002 ,  F23R3/06 ,  F23R3/50 ,  F23R2900/00012 ,  F23R2900/03041 ,  F23R2900/03042 ,  F23R2900/03044

    Abstract: A turbine engine assembly includes a combustor and a stator vane arrangement having a plurality of stator vanes. The combustor includes a combustor wall that extends axially from a combustor bulkhead to a distal combustor wall end, which is located adjacent to the stator vane arrangement. The combustor wall includes a support shell with a plurality of impingement apertures, and a heat shield with a plurality of effusion apertures. The combustor wall end includes a plurality of circumferentially extending film cooled regions. At least one of the film cooled regions is circumferentially aligned with one of the stator vanes and includes a cooling aperture.

    Abstract translation: 涡轮发动机组件包括具有多个定子叶片的燃烧器和定子叶片装置。 燃烧器包括从燃烧器隔板轴向延伸到位于邻近定子叶片装置的远侧燃烧器壁端部的燃烧室壁。 燃烧器壁包括具有多个冲击孔的支撑壳和具有多个喷射孔的隔热罩。 燃烧器壁端部包括多个周向延伸的膜冷却区域。 薄膜冷却区域中的至少一个与定子叶片中的一个周向对齐并且包括冷却孔。

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