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    PASSAGE GEOMETRY FOR GAS TURBINE ENGINE COMBUSTOR
    3.
    发明申请
    PASSAGE GEOMETRY FOR GAS TURBINE ENGINE COMBUSTOR 审中-公开
    燃气轮机燃烧器的通道几何

    公开(公告)号：WO2015108584A3

    公开(公告)日：2015-09-11

    申请号：PCT/US2014061572

    申请日：2014-10-21

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： MOURA DENNIS M ,  EASTWOOD JONATHAN J ,  BOULDIN LEE E

    IPC: F23M5/00 ,  F23M5/08 ,  F23R3/42

    CPC classification number: F23R3/06 ,  F23R3/50 ,  F23R2900/00017 ,  F23R2900/00018 ,  F23R2900/03041 ,  F23R2900/03044 ,  F23R2900/03045 ,  Y02T50/675

    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了环形垫圈。 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垫面板。 该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。 环形垫圈在其中包括腔室。 一种冷却燃气涡轮发动机内的壁组件的方法包括将空气注入环形垫圈中的腔室。

    TURBINE ENGINE COMBUSTOR HEAT SHIELD WITH MULTI-HEIGHT RAILS
    4.
    发明申请
    TURBINE ENGINE COMBUSTOR HEAT SHIELD WITH MULTI-HEIGHT RAILS 审中-公开
    涡轮发动机COMBUSTOR加热器与多高度的铁路

    公开(公告)号：WO2015112216A2

    公开(公告)日：2015-07-30

    申请号：PCT/US2014063450

    申请日：2014-10-31

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： EASTWOOD JONATHAN J ,  MOURA DENNIS M

    IPC: F23M5/00 ,  F23M5/04 ,  F23R3/42

    CPC classification number: F23R3/002

    Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall, which includes a shell and a heat shield. The heat shield includes a base and a plurality of panel rails. The panel rails are connected to the base and extend vertically to the shell. The panel rails include first and second rails. A vertical height of the first rail at a first location is less than a vertical height of the second rail at a second location.

    Abstract translation: 提供了一种用于涡轮发动机的组件。 该涡轮发动机组件包括燃烧器壁，其包括外壳和隔热罩。 隔热罩包括基座和多个面板导轨。 面板导轨连接到底座并垂直延伸到外壳。 面板导轨包括第一和第二导轨。 在第一位置处的第一轨道的垂直高度小于在第二位置处的第二轨道的垂直高度。

    QUENCH APERTURE BODY FOR A TURBINE ENGINE COMBUSTOR
    5.
    发明申请
    QUENCH APERTURE BODY FOR A TURBINE ENGINE COMBUSTOR 审中-公开
    用于涡轮发动机燃烧室的QUANCH孔体

    公开(公告)号：WO2015116269A3

    公开(公告)日：2015-10-08

    申请号：PCT/US2014063440

    申请日：2014-10-31

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： MOURA DENNIS M ,  EASTWOOD JONATHAN J ,  BOULDIN LEE E ,  PACHECO-TOUGAS MONICA

    IPC: F23M5/00 ,  F23M5/08 ,  F23R3/42

    CPC classification number: F23R3/002 ,  F23R3/005 ,  F23R3/007 ,  F23R3/045 ,  F23R3/06 ,  F23R2900/03041 ,  F23R2900/03044

    Abstract: An assembly for a turbine engine includes a combustor wall. The combustor wall includes a shell, a heat shield and an annular land. The heat shield is attached to the shell. The land extends vertically between the shell and the heat shield. The land extends laterally between a land outer surface and an inner surface, which at least partially defines a quench aperture in the combustor wall. A lateral distance between the land outer surface and the inner surface varies around the quench aperture.

    Abstract translation: 涡轮发动机的组件包括燃烧器壁。 燃烧器壁包括壳体，隔热罩和环形区域。 隔热罩连接在外壳上。 土地在壳体和隔热罩之间垂直延伸。 焊盘在焊盘外表面和内表面之间横向延伸，其至少部分地限定燃烧器壁中的淬火孔。 焊盘外表面和内表面之间的横向距离在淬火孔周围变化。

    TURBINE ENGINE COMBUSTOR HEAT SHIELD WITH MULTI-ANGLED COOLING APERTURES
    6.
    发明申请
    TURBINE ENGINE COMBUSTOR HEAT SHIELD WITH MULTI-ANGLED COOLING APERTURES 审中-公开
    涡轮发动机燃烧器加热罩具有多角度冷却孔

    公开(公告)号：WO2015112221A2

    公开(公告)日：2015-07-30

    申请号：PCT/US2014063859

    申请日：2014-11-04

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： MOURA DENNIS M ,  PACHECO-TOUGAS MONICA ,  EASTWOOD JONATHAN J ,  BOULDIN LEE E

    IPC: F23M5/08 ,  F23M5/04 ,  F23R3/42

    CPC classification number: F23R3/002 ,  F02C7/18 ,  F02C7/24 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2260/202 ,  F23R3/005 ,  F23R3/007 ,  F23R3/04 ,  F23R3/06 ,  F23R2900/03041 ,  F23R2900/03044

    Abstract: A combustor for a turbine engine is provided that includes a combustor wall. The combustor wall includes a shell and a heat shield, which is attached to the shell. One or more cooling cavities are defined between the shell and the heat shield, and fluidly couple a plurality of apertures defined in the shell with a plurality of apertures defined in the heat shield. The apertures in the heat shield include a first aperture and a second aperture. An angle of incidence between the first aperture and a surface of the heat shield is different than an angle of incidence between the second aperture and the surface.

    Abstract translation: 提供了一种用于涡轮发动机的燃烧器，其包括燃烧器壁。 燃烧器壁包括壳体和连接到壳体的隔热罩。 一个或多个冷却空腔限定在壳体和隔热罩之间，并且将壳体中限定的多个孔与限定在隔热罩中的多个孔流体地联接。 隔热罩中的孔包括第一孔和第二孔。 第一孔与隔热屏表面之间的入射角不同于第二孔与表面之间的入射角。

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