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    Turbine nozzle and method for cooling a turbine nozzle of a gas turbine engine
    11.
    发明授权
    Turbine nozzle and method for cooling a turbine nozzle of a gas turbine engine 有权
    涡轮喷嘴和用于冷却燃气涡轮发动机的涡轮喷嘴的方法

    公开(公告)号：US09562439B2

    公开(公告)日：2017-02-07

    申请号：US14141789

    申请日：2013-12-27

    Applicant: General Electric Company

    Inventor： Michelle Jessica Iduate ,  Gregory Thomas Foster ,  David Wayne Weber

    IPC: F01D9/06 ,  F01D9/04 ,  F01D9/02 ,  F01D5/18

    CPC classification number: F01D9/065 ,  F01D5/186 ,  F01D9/02 ,  F01D9/041 ,  F05D2240/81 ,  F05D2250/185 ,  F05D2260/202

    Abstract: The present application and the resultant patent provide a turbine nozzle for a gas turbine engine. The turbine nozzle may include a first nozzle vane, a second nozzle vane, and a platform connecting the first nozzle vane and the second nozzle vane. The platform may include a first cooling passage and a separate second cooling passage defined therein. The first cooling passage may be configured to direct a first flow of cooling fluid in a first direction, and the second cooling passage may be configured to direct a second flow of cooling fluid in a second direction substantially opposite the first direction. The present application and the resultant patent further provide a method for cooling a turbine nozzle of a gas turbine engine.

    Abstract translation: 本申请和所得专利提供了一种用于燃气涡轮发动机的涡轮喷嘴。 涡轮喷嘴可以包括第一喷嘴叶片，第二喷嘴叶片和连接第一喷嘴叶片和第二喷嘴叶片的平台。 平台可以包括第一冷却通道和限定在其中的单独的第二冷却通道。 第一冷却通道可以被构造成在第一方向上引导冷却流体的第一流动，并且第二冷却通道可以被配置成在基本上与第一方向相反的第二方向上引导第二冷却流体流。 本申请和所得到的专利还提供了一种用于冷却燃气涡轮发动机的涡轮喷嘴的方法。

    SEALING DEVICE FOR PROVIDING A SEAL IN A TURBOMACHINE
    12.
    发明申请
    SEALING DEVICE FOR PROVIDING A SEAL IN A TURBOMACHINE 有权
    用于在涡轮机中提供密封的密封装置

    公开(公告)号：US20150211377A1

    公开(公告)日：2015-07-30

    申请号：US14164707

    申请日：2014-01-27

    Applicant: General Electric Company

    Inventor： Benjamin Paul Lacy ,  Srikanth Chandrudu Kottilingam ,  Christopher Donald Porter ,  David Edward Schick ,  David Wayne Weber

    IPC: F01D11/00 ,  F16J15/02

    CPC classification number: F01D11/005 ,  F01D9/023 ,  F01D11/003 ,  F05D2240/11 ,  F05D2240/55 ,  F16J15/02 ,  F16J15/061 ,  F16J15/126

    Abstract: Sealing device for providing seals between adjacent components, and turbomachines utilizing such sealing devices, are provided. A sealing device includes a seal plate insertable between the adjacent components, the seal plate comprising a first face and an opposing second face. The sealing device further includes a plurality of pins extending from one of the first face or the second face, the plurality of pins configured to space the one of the first face or the second face from contact surfaces of the adjacent components.

    Abstract translation: 提供了用于在相邻部件之间提供密封的密封装置，以及利用这种密封装置的涡轮机。 密封装置包括可插入相邻部件之间的密封板，密封板包括第一面和相对的第二面。 所述密封装置还包括从所述第一面或所述第二面中的一个延伸的多个销，所述多个销用于将所述第一面或所述第二面中的一个从所述相邻部件的接触表面间隔开。

    TURBINE NOZZLE AND METHOD FOR COOLING A TURBINE NOZZLE OF A GAS TURBINE ENGINE
    13.
    发明申请
    TURBINE NOZZLE AND METHOD FOR COOLING A TURBINE NOZZLE OF A GAS TURBINE ENGINE 有权
    涡轮喷嘴和用于冷却气体涡轮发动机涡轮喷嘴的方法

    公开(公告)号：US20150184530A1

    公开(公告)日：2015-07-02

    申请号：US14141789

    申请日：2013-12-27

    Applicant: General Electric Company

    Inventor： Michelle Jessica Iduate ,  Gregory Thomas Foster ,  David Wayne Weber

    IPC: F01D9/06

    CPC classification number: F01D9/065 ,  F01D5/186 ,  F01D9/02 ,  F01D9/041 ,  F05D2240/81 ,  F05D2250/185 ,  F05D2260/202

    Abstract: The present application and the resultant patent provide a turbine nozzle for a gas turbine engine. The turbine nozzle may include a first nozzle vane, a second nozzle vane, and a platform connecting the first nozzle vane and the second nozzle vane. The platform may include a first cooling passage and a separate second cooling passage defined therein. The first cooling passage may be configured to direct a first flow of cooling fluid in a first direction, and the second cooling passage may be configured to direct a second flow of cooling fluid in a second direction substantially opposite the first direction. The present application and the resultant patent further provide a method for cooling a turbine nozzle of a gas turbine engine.

    Abstract translation: 本申请和所得专利提供了一种用于燃气涡轮发动机的涡轮喷嘴。 涡轮喷嘴可以包括第一喷嘴叶片，第二喷嘴叶片和连接第一喷嘴叶片和第二喷嘴叶片的平台。 平台可以包括第一冷却通道和限定在其中的单独的第二冷却通道。 第一冷却通道可以被构造成在第一方向上引导冷却流体的第一流动，并且第二冷却通道可以被配置成在基本上与第一方向相反的第二方向上引导第二冷却流体流。 本申请和所得到的专利还提供了一种用于冷却燃气涡轮发动机的涡轮喷嘴的方法。

    MICROCHANNEL SYSTEMS AND METHODS FOR COOLING TURBINE COMPONENTS OF A GAS TURBINE ENGINE
    14.
    发明申请
    MICROCHANNEL SYSTEMS AND METHODS FOR COOLING TURBINE COMPONENTS OF A GAS TURBINE ENGINE 审中-公开
    用于冷却涡轮发动机涡轮机组件的微通道系统和方法

    公开(公告)号：US20140360155A1

    公开(公告)日：2014-12-11

    申请号：US13912582

    申请日：2013-06-07

    Applicant: General Electric Company

    Inventor： David Wayne Weber ,  Aaron Ezekiel Smith

    IPC: F02C7/18

    CPC classification number: F01D11/08 ,  F01D5/187 ,  F05D2240/11 ,  F05D2260/204 ,  Y10T29/49236

    Abstract: The present application and the resultant patent thus provide a microchannel system for cooling a hot gas path surface of a turbine. The microchannel system may include a turbine component having an outer surface extending along a hot gas path of the turbine, a microchannel defined within the turbine component and extending about the outer surface, and a number of pockets defined within the turbine component and positioned along the microchannel. The present application and the resultant patent further provide a method of forming a microchannel system for cooling a hot gas path surface of a turbine. The method may include the steps of forming a turbine component having an outer surface extending along a hot gas path of the turbine, defining a microchannel within the turbine component and extending about the outer surface, and defining a number of pockets within the turbine component and positioned along the microchannel.

    Abstract translation: 因此，本申请和所得到的专利提供了一种用于冷却涡轮机的热气体路径表面的微通道系统。 微通道系统可以包括具有沿着涡轮机的热气体路径延伸的外表面的涡轮机部件，限定在涡轮机部件内并围绕外表面延伸的微通道以及限定在涡轮机部件内并沿着该涡轮机部件定位的多个凹部 微通道。 本申请和所得专利进一步提供了一种形成用于冷却涡轮机的热气体通道表面的微通道系统的方法。 该方法可以包括以下步骤：形成涡轮机部件，其具有沿着涡轮机的热气体路径延伸的外表面，在涡轮机部件内限定微通道并围绕外表面延伸，并且在涡轮机部件内限定多个凹穴， 沿着微通道定位。

    FLARED CENTRAL CAVITY AFT OF AIRFOIL LEADING EDGE
    17.
    发明申请
    FLARED CENTRAL CAVITY AFT OF AIRFOIL LEADING EDGE 审中-公开

    公开(公告)号：US20200063574A1

    公开(公告)日：2020-02-27

    申请号：US16669756

    申请日：2019-10-31

    Applicant: General Electric Company

    Inventor： Brendon James Leary ,  Gregory Thomas Foster ,  Michelle Jessica Iduate ,  David Wayne Weber

    IPC: F01D5/18 ,  F01D9/04

    Abstract: A blade includes an airfoil defined by a pressure side outer wall and a suction side outer wall connecting along leading and trailing edges and form a radially extending chamber for receiving a coolant flow. A rib configuration may include: a leading edge transverse rib connecting the pressure side outer wall and the suction side outer wall and partitioning the radially extending chamber into a leading edge passage within the leading edge of the airfoil and a central passage adjacent to the leading edge passage. One or both camber line ribs connect to a corresponding pressure side outer wall and suction side outer wall at a point aft of the leading edge transverse rib causing the central passage to extend towards one or both of the pressure side outer wall and the suction side outer wall, resulting in a flared center cavity aft of the leading edge.

    Cooling circuit for a multi-wall blade
    18.
    发明授权
    Cooling circuit for a multi-wall blade 有权

    公开(公告)号：US10208607B2

    公开(公告)日：2019-02-19

    申请号：US15239940

    申请日：2016-08-18

    Applicant: General Electric Company

    Inventor： David Wayne Weber ,  Gregory Thomas Foster ,  Lana Maria Osusky

    IPC: F01D5/18 ,  F01D25/12 ,  F01D5/14 ,  F01D9/02 ,  F02C3/04

    Abstract: A cooling circuit according to an embodiment includes: a cooling circuit for a multi-wall blade, the cooling circuit including: a pressure side cavity with a surface adjacent a pressure side of the multi-wall blade; a suction side cavity with a surface adjacent a suction side of the multi-wall blade; a central cavity disposed between the pressure side and suction side cavities, the central cavity including no surfaces adjacent the pressure and suction sides of the multi-wall blade; a first leading edge cavity with surfaces adjacent the pressure and suction sides of the multi-wall blade; and at least one impingement opening for fluidly coupling the leading edge cavity with a second leading edge cavity.

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