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    SWIRLER MOUNT INTERFACE FOR GAS TURBINE ENGINE COMBUSTOR
    1.
    发明申请
    SWIRLER MOUNT INTERFACE FOR GAS TURBINE ENGINE COMBUSTOR 审中-公开
    燃气轮机发动机喷油器接口

    公开(公告)号：WO2015053818A3

    公开(公告)日：2015-06-18

    申请号：PCT/US2014038214

    申请日：2014-05-15

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： DRAKE CHRISTOPHER ,  MAX SETH A ,  HARRIS MEGGAN

    IPC: F23R3/14

    CPC classification number: F23R3/14 ,  B23P19/00 ,  F23R3/002 ,  F23R3/283 ,  F23R2900/00012 ,  Y02T50/675

    Abstract: A swirler for a combustor of a gas turbine engine includes a swirler outer body with a swirler threaded section defined around a swirler central longitudinal axis. A bulkhead support shell for a combustor of a gas turbine engine includes a swirler boss with a boss threaded section defined around a swirler central longitudinal axis. A combustor of a gas turbine engine includes a bulkhead support shell with a swirler boss. The combustor also includes a swirler mountable to the swirler boss at a threaded interface defined around a swirler central longitudinal axis.

    Abstract translation: 用于燃气涡轮发动机的燃烧器的旋流器包括围绕旋流器中心纵向轴线限定的旋流器螺纹部分的旋流器外部主体。 用于燃气涡轮发动机的燃烧器的隔板支撑壳包括旋流器凸台，其具有围绕旋流器中心纵向轴线限定的凸起螺纹部分。 燃气涡轮发动机的燃烧器包括具有旋流器凸台的隔板支撑壳体。 燃烧器还包括旋流器，其可以围绕旋流器中心纵向轴线限定的螺纹接口安装到旋流器凸台。

    VENA CONTRACTA SWIRLING DILUTION PASSAGES FOR GAS TURBINE ENGINE COMBUSTOR
    7.
    发明申请
    VENA CONTRACTA SWIRLING DILUTION PASSAGES FOR GAS TURBINE ENGINE COMBUSTOR 审中-公开
    VENA CONTRACTA发动机燃油涡轮增压通道

    公开(公告)号：WO2015047509A2

    公开(公告)日：2015-04-02

    申请号：PCT/US2014044873

    申请日：2014-06-30

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： DRAKE CHRISTOPHER ,  CUNHA FRANK J ,  KOSTKA JR STANISLAV ,  JAUSE JONATHAN M ,  HANSON RUSSELL B

    IPC: F23M5/08 ,  F02C7/18 ,  F23R3/42

    CPC classification number: F23R3/06 ,  F02C7/18 ,  F23R3/002 ,  F23R3/005 ,  F23R3/04 ,  F23R3/045 ,  F23R3/26 ,  F23R2900/03041 ,  F23R2900/03042 ,  F23R2900/03044 ,  Y02T50/675

    Abstract: A liner panel for use in a combustor of a gas turbine engine includes a nozzle includes an inner periphery along an axis. The inner periphery includes a flow guide around the axis. A wall assembly for use in a combustor of a gas turbine engine includes a support shell with a first inner periphery along an axis. The wall assembly also includes a liner panel with a second inner periphery along the axis, the second inner periphery including a spiral flow guide around the axis. A method of reducing recirculation into a dilution passage in a combustor liner panel of a gas turbine engine includes contouring a dilution passage to match a natural vena contracta of a fluid flowing therethrough.

    Abstract translation: 用于燃气涡轮发动机的燃烧器的衬板包括：喷嘴，其包括沿轴线的内周边。 内周边包括围绕轴的流动引导件。 用于燃气涡轮发动机的燃烧器的壁组件包括具有沿轴线的第一内周边的支撑壳体。 壁组件还包括具有沿着轴线的第二内周边的衬板，第二内周包括围绕轴的螺旋形流动引导件。 减少在燃气涡轮发动机的燃烧器衬板中的再循环进入稀释通道的方法包括对稀释通道进行轮廓化，以匹配流过其中的流体的天然收缩膜。

    SEALED COMBUSTOR LINER PANEL FOR A GAS TURBINE ENGINE
    9.
    发明公开
    SEALED COMBUSTOR LINER PANEL FOR A GAS TURBINE ENGINE 审中-公开
    ABGEDICHTETE BRENNKAMMERWANDPLATTEFÜREINEN GASTURBINENMOTOR

    公开(公告)号：EP3044444A4

    公开(公告)日：2016-10-05

    申请号：EP14843958

    申请日：2014-07-11

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： DRAKE CHRISTOPHER

    IPC: F02C7/24 ,  F02C7/28 ,  F23R3/42

    CPC classification number: F23R3/06 ,  F02C7/18 ,  F02C7/24 ,  F02C7/28 ,  F23R3/005 ,  F23R3/60 ,  F23R2900/00012 ,  F23R2900/00017 ,  F23R2900/03041 ,  F23R2900/03042 ,  F23R2900/03044 ,  Y02T50/675

    Abstract: A liner panel for a combustor of a gas turbine engine includes a rail which at least partially defines an impingement cavity. The rail includes a notch which faces toward the impingement cavity. A method of cooling a wall assembly within a combustor for of a gas turbine engine includes directing air through a support shell and a liner panel to form a pressure drop across the support shell that is less than about 80% of a pressure drop across the combustor and to also form a pressure drop across the liner panel greater than about 20% of the pressure drop across the combustor.

    Abstract translation: 用于燃气涡轮发动机的燃烧器的衬板包括至少部分地限定冲击腔的轨道。 导轨包括朝向冲击腔的凹口。 一种冷却用于燃气涡轮发动机的燃烧器内的壁组件的方法包括将空气引导通过支撑壳体和衬套板，以形成穿过该支撑壳体的压降，其小于穿过该燃烧器的压降的约80％ 并且还在衬板上形成超过燃烧器上的压降的约20％的压降。

    VENA CONTRACTA SWIRLING DILUTION PASSAGES FOR GAS TURBINE ENGINE COMBUSTOR
    10.
    发明公开
    VENA CONTRACTA SWIRLING DILUTION PASSAGES FOR GAS TURBINE ENGINE COMBUSTOR 有权
    弗吉尼亚州

    公开(公告)号：EP3039340A4

    公开(公告)日：2016-08-24

    申请号：EP14848461

    申请日：2014-06-30

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： DRAKE CHRISTOPHER ,  CUNHA FRANK J ,  KOSTKA JR STANISLAV ,  JAUSE JONATHAN M ,  HANSON RUSSELL B

    IPC: F23M5/08 ,  F02C7/18 ,  F23R3/04 ,  F23R3/42

    CPC classification number: F23R3/06 ,  F02C7/18 ,  F23R3/002 ,  F23R3/005 ,  F23R3/04 ,  F23R3/045 ,  F23R3/26 ,  F23R2900/03041 ,  F23R2900/03042 ,  F23R2900/03044 ,  Y02T50/675

    Abstract: A liner panel for use in a combustor of a gas turbine engine includes a nozzle includes an inner periphery along an axis. The inner periphery includes a flow guide around the axis. A wall assembly for use in a combustor of a gas turbine engine includes a support shell with a first inner periphery along an axis. The wall assembly also includes a liner panel with a second inner periphery along the axis, the second inner periphery including a spiral flow guide around the axis. A method of reducing recirculation into a dilution passage in a combustor liner panel of a gas turbine engine includes contouring a dilution passage to match a natural vena contracta of a fluid flowing therethrough.

    Abstract translation: 用于燃气涡轮发动机的燃烧器的衬板包括：喷嘴，包括沿轴线的内周边。 内周边包括围绕轴的流动引导件。 用于燃气涡轮发动机的燃烧器的壁组件包括具有沿轴线的第一内周边的支撑壳体。 壁组件还包括具有沿着轴线的第二内周边的衬板，第二内周包括绕轴线的螺旋形流动引导件。 减少燃气涡轮发动机的燃烧器衬板中的稀释通道的再循环的方法包括对稀释通道进行轮廓化，以匹配流过其中的流体的天然收缩膜。

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