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    COMBUSTOR HAVING A BEVELED GROMMET
    24.
    发明申请
    COMBUSTOR HAVING A BEVELED GROMMET 审中-公开

    公开(公告)号：US20160273774A1

    公开(公告)日：2016-09-22

    申请号：US15172194

    申请日：2016-06-03

    Applicant: United Technologies Corporation

    Inventor： Crisen McKenzie ,  Timothy S. Snyder

    IPC: F23R3/06 ,  F02C3/04 ,  F23R3/50

    Abstract: A combustor includes a shell that at least partially defines a combustion chamber and a grommet mounted in the shell. The grommet has a body that defines a passage through the grommet that is operable to communicate air from outside the combustion chamber into the combustion chamber. The body carries a first surface, an opposite, second surface and a third surface that defines the passage and joins the first surface and the second surface. The third surface includes a bevel surface with respect to at least one of the first surface and the second surface.

    SELF-COOLED ORIFICE STRUCTURE
    26.
    发明申请
    SELF-COOLED ORIFICE STRUCTURE 有权
    自冷式结构

    公开(公告)号：US20160003477A1

    公开(公告)日：2016-01-07

    申请号：US14790970

    申请日：2015-07-02

    Applicant: United Technologies Corporation

    Inventor： Tracy A. Propheter-Hinckley ,  Dominic J. Mongillo ,  Joel H. Wagner ,  Mark F. Zelesky ,  Stanislav Kostka ,  Timothy S. Snyder

    IPC: F23R3/06 ,  F23R3/00

    CPC classification number: F23R3/06 ,  F23R3/002 ,  F23R3/005 ,  F23R2900/00019 ,  F23R2900/03042 ,  F23R2900/03044 ,  Y02T50/675

    Abstract: A self-cooled orifice structure that may be for a combustor of a gas turbine engine, and may further be a dilution hole structure, includes a hot side panel, a cold side panel spaced from the hot side panel, and a continuous inner wall extending between the hot and cold side panels and defining an orifice having a centerline and communicating axially through the hot and cold side panels. A plurality of end walls of the structure are in a cooling cavity that is defined in-part by the hot and cold side panels and the inner wall. Each end wall extends between and are engaged to the hot and cold side panels and are circumferentially spaced from the next adjacent end wall. A plurality of inlet apertures extend through the cold side panel and are in fluid communication with the cavity, and each one of the plurality of inlet apertures are proximate to a first side of a respective one of the plurality of end walls. A plurality of outlet apertures extend through the hot side panel and are in fluid communication with the cavity, and each one of the plurality of outlet apertures are associated with an opposite second side of a respective one of the plurality of end walls.

    Abstract translation: 可以用于燃气涡轮发动机的燃烧器的自冷却孔结构，并且还可以是稀释孔结构，包括热侧板，与热侧板间隔开的冷侧板，以及连续的内壁，其延伸 在热和冷侧板之间并且限定具有中心线并且轴向地通过热和冷侧板的孔口。 该结构的多个端壁位于由冷热侧板和内壁部分限定的冷却腔中。 每个端壁在热侧面板和冷侧面板之间延伸并与之接合，并与下一个相邻的端壁沿圆周间隔开。 多个入口孔延伸穿过冷侧面板并且与空腔流体连通，并且多个入口孔中的每一个靠近多个端壁中的相应一个的第一侧。 多个出口孔延伸穿过热侧面板并且与空腔流体连通，并且多个出口孔中的每一个与多个端壁中的相应一个端壁的相对的第二侧相关联。

    Combustor Cooled Quench Zone Array
    27.
    发明申请
    Combustor Cooled Quench Zone Array 审中-公开
    燃烧器冷却淬火区域阵列

    公开(公告)号：US20150354819A1

    公开(公告)日：2015-12-10

    申请号：US14759811

    申请日：2013-01-16

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Timothy S. Snyder ,  James B. Hoke

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

    Abstract: In accordance with one aspect of the disclosure, a combustor is disclosed. The combustor may include a shell and a liner disposed within the shell. The combustor may further include a grommet at least partially defining a hole communicating through the shell and liner and a cooling channel communicating through the grommet.

    Abstract translation: 根据本公开的一个方面，公开了一种燃烧器。 燃烧器可以包括壳体和设置在壳体内的衬套。 燃烧器还可以包括至少部分地限定通过壳体和衬套连通的孔和通过垫圈连通的冷却通道的护环。

    Combustor Bulkhead Cooling Array
    29.
    发明申请
    Combustor Bulkhead Cooling Array 审中-公开
    燃烧器舱壁冷却阵列

    公开(公告)号：US20140102106A1

    公开(公告)日：2014-04-17

    申请号：US13649581

    申请日：2012-10-11

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Timothy S. Snyder ,  John S. Tu

    IPC: F02C1/00

    CPC classification number: F23R3/002 ,  F23R3/04 ,  F23R2900/03041 ,  F23R2900/03044 ,  Y02T50/675

    Abstract: A bulkhead panel is disclosed. The bulkhead panel may comprise a body having a body having a front surface and an opposite back surface, a fuel nozzle opening in the body and communicating through the front and back surfaces, and a plurality of effusion holes disposed in at least one row that surrounds and is generally concentric to the fuel nozzle opening. Each effusion hole may extend from the back surface to the front surface at an incline angle. Each effusion hole may be positioned at a clock angle from a reference line radially extending from a center of the fuel nozzle opening through a center of the effusion hole.

    Abstract translation: 公开了一种隔板。 舱壁板可以包括具有主体的主体，该主体具有前表面和相对的后表面，在主体中的燃料喷嘴开口并通过前表面和后表面连通，并且多个排出孔设置在至少一排中， 并且通常与燃料喷嘴开口同心。 每个渗出孔可以以倾斜角从后表面延伸到前表面。 每个渗出孔可以从从燃料喷嘴开口的中心径向延伸穿过渗出孔的中心的参考线以时钟角定位。

    Combustor heat shield and method of cooling same
    30.
    发明授权
    Combustor heat shield and method of cooling same 有权

    公开(公告)号：US11293638B2

    公开(公告)日：2022-04-05

    申请号：US16549722

    申请日：2019-08-23

    Applicant: United Technologies Corporation

    Inventor： Fumitaka Ichihashi ,  Timothy S. Snyder ,  Jeffrey J. Lienau ,  Baris A. Sen

    IPC: F23R3/08 ,  F01D25/12 ,  F01D25/26

    Abstract: A combustor for a gas turbine engine includes an annular shell, an annular bulkhead connected to the shell, and a heat shield panel. The heat shield panel has a first surface facing a combustion chamber and a second surface opposite the first surface. The heat shield panel is mounted to the bulkhead and defines a cooling chamber between the bulkhead and the heat shield panel. The heat shield panel has a wall extending from the heat shield panel toward the bulkhead around at least a portion of a periphery of the heat shield panel. The wall includes a circumferential wall portion including at least one cooling air passage extending between the cooling chamber and a cavity defined between the circumferential wall portion and the shell. The at least one cooling air passage is configured to purge the cavity by directing a first cooling air stream from the cooling chamber into the cavity.

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