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    PASSAGE GEOMETRY FOR GAS TURBINE ENGINE COMBUSTOR
    23.
    发明申请
    PASSAGE GEOMETRY FOR GAS TURBINE ENGINE COMBUSTOR 审中-公开
    用于气体涡轮发动机的通气几何

    公开(公告)号：US20160238253A1

    公开(公告)日：2016-08-18

    申请号：US15027082

    申请日：2014-10-21

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Dennis M. Moura ,  Jonathan J. Eastwood ,  Lee E. Bouldin

    IPC: F23R3/06

    Abstract: An annular grommet is provided for a wall assembly of a combustor section of a gas turbine engine. The annular grommet includes a wall that at least partially defines a chamber. A wall assembly within a gas turbine engine includes a liner panel with a hot side and a cold side. The wall assembly also includes an annular grommet with a passage wall and a flange wall transverse to the passage wall. The annular grommet includes a chamber therein. A method of cooling a wall assembly within a gas turbine engine includes injecting air through a chamber in an annular grommet.

    Abstract translation: 为燃气涡轮发动机的燃烧器部分的壁组件提供环形垫圈。 环形垫圈包括至少部分地限定腔室的壁。 燃气涡轮发动机内的壁组件包括具有热侧和冷侧的衬板。 壁组件还包括具有通道壁和横向于通道壁的凸缘壁的环形垫圈。 环形索环包括其中的室。 一种冷却燃气涡轮发动机内的壁组件的方法包括将空气喷射通过环形垫圈中的室。

    BOSS FOR COMBUSTOR PANEL
    25.
    发明申请
    BOSS FOR COMBUSTOR PANEL 审中-公开

    公开(公告)号：US20160186994A1

    公开(公告)日：2016-06-30

    申请号：US14912175

    申请日：2014-08-06

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Lee Edward Bouldin ,  Monica Pacheco-Tougas ,  Dennis M. Moura ,  Jonathan Jeffery Eastwood

    IPC: F23M5/08 ,  F23R3/00 ,  F23R3/06 ,  F23R3/60

    CPC classification number: F23M5/085 ,  F23R3/002 ,  F23R3/06 ,  F23R3/60 ,  F23R2900/03044 ,  Y02T50/675

    Abstract: A combustor for use in a gas turbine engine has a combustor outer shell. A panel has an inner face which will face hot products of combustion, and a boss surrounding a feature, with the boss extending to an outer end. A spacing surface is spaced from the boss, and is at an outer position that is inward of the outer end of the boss. The spacing surface spaces the panel from the outer shell. A trough is intermediate the boss and the spacing surface. The trough extends to an outer end which is inward of the outer position of the spacing surface. A gas turbine engine is also disclosed.

    Abstract translation: 用于燃气涡轮发动机的燃烧器具有燃烧器外壳。 面板具有面向热的燃烧产物的内表面和围绕特征的凸台，凸台延伸到外端。 间隔表面与凸台间隔开，并且处于位于凸台的外端内侧的外部位置。 间隔表面将面板与外壳隔开。 槽位于凸台和间隔表面之间。 槽延伸到位于间隔表面的外部位置内侧的外端。 还公开了一种燃气涡轮发动机。

    TUBE ASSEMBLY
    26.
    发明申请
    TUBE ASSEMBLY 有权
    管组件

    公开(公告)号：US20160003556A1

    公开(公告)日：2016-01-07

    申请号：US14789496

    申请日：2015-07-01

    Applicant: United Technologies Corporation

    Inventor： Joe Ott ,  John J. Rup, JR. ,  Dennis M. Moura ,  Lyutsia Dautova ,  Roger O. Coffey

    IPC: F28F1/00

    CPC classification number: F28F1/00 ,  F16L9/18 ,  F16L59/14 ,  F23D2211/00 ,  F23D2900/00016 ,  F23R3/283

    Abstract: A tube assembly that may be for a fuel nozzle of a fuel system of a gas turbine engine may have a first tube defining a first flowpath along a centerline, a second tube generally spaced radially outward from the first tube with a first void located between and defined by the first and second tubes, and a support structure located in the first void and extending between the first and second tubes. The support structure is constructed and arranged to minimize or eliminate thermal conduction between the tubes. The entire assembly may be additive manufactured as one unitary piece. One example of a method of operation may include designed-for breakage of the structural support due to then al stresses thereby further minimizing thermal conduction between tubes.

    Abstract translation: 可用于燃气涡轮发动机的燃料系统的燃料喷嘴的管组件可以具有限定沿中心线的第一流动路径的第一管，大体上与第一管径向向外隔开的第二管， 由第一和第二管限定，以及位于第一空隙中并在第一和第二管之间延伸的支撑结构。 支撑结构被构造和布置成最小化或消除管之间的热传导。 整个组件可以是作为一体式制造的添加剂。 操作方法的一个实例可以包括由于由此而产生的结构支撑件的破坏，从而进一步最小化管之间的热传导。

    Apparatus and method for mitigating particulate accumulation on a component of a gas turbine
    28.
    发明授权
    Apparatus and method for mitigating particulate accumulation on a component of a gas turbine 有权

    公开(公告)号：US11092339B2

    公开(公告)日：2021-08-17

    申请号：US16239879

    申请日：2019-01-04

    Applicant: United Technologies Corporation

    Inventor： Dennis M. Moura ,  Carey Clum

    IPC: F23R3/08 ,  F01D25/12 ,  F23R3/00 ,  F23R3/06 ,  F23R3/04

    Abstract: A gas turbine engine component assembly comprising: a first component having a first surface and a second surface opposite the first surface, wherein the first component includes a cooling hole extending from the second surface to the first surface; a second component having a first surface and a second surface, the first surface of the first component and the second surface of the second component defining a cooling channel therebetween; and a lateral flow injection device secured to first component, the lateral flow injection device fluidly connecting a flow path located proximate to the second surface of the first component to the cooling channel, the lateral flow injection device being configured to direct airflow from the airflow path into the cooling channel in about a lateral direction parallel to the second surface of the second component such that a cross flow is generated in the cooling channel.

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