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    METHOD FOR MANUFACTURING A HOT GAS PATH COMPONENT
    3.
    发明申请
    METHOD FOR MANUFACTURING A HOT GAS PATH COMPONENT 审中-公开
    制造热气路径成分的方法

    公开(公告)号：US20130313307A1

    公开(公告)日：2013-11-28

    申请号：US13479710

    申请日：2012-05-24

    申请人： Benjamin Paul Lacy ,  Srikanth Chandrudu Kottilingam ,  Brian Lee Tollison

    发明人： Benjamin Paul Lacy ,  Srikanth Chandrudu Kottilingam ,  Brian Lee Tollison

    IPC分类号： B23K31/02

    CPC分类号： F01D5/187 ,  F05D2230/232

    摘要： A method for manufacturing a cooling passage in a component of a machine is described. The method may include: forming a channel in a surface of the component, the channel having a predetermined configuration; forming a cover wire, the cover wire having a predetermined configuration based on the predetermined configuration of the channel; nesting the cover wire in the channel; and welding the nested cover wire to the component such that the channel is enclosed.

    摘要翻译： 描述了一种用于在机器的部件中制造冷却通道的方法。 所述方法可以包括：在所述部件的表面中形成通道，所述通道具有预定的构造; 形成盖线，所述盖线基于所述通道的预定配置具有预定配置; 将盖线嵌入通道中; 并将嵌套的盖线焊接到部件上，使得通道被封闭。

    TURBINE COMPONENT WITH NEAR-SURFACE COOLING PASSAGE AND PROCESS THEREFOR
    7.
    发明申请
    TURBINE COMPONENT WITH NEAR-SURFACE COOLING PASSAGE AND PROCESS THEREFOR 审中-公开
    具有近表面冷却通风的涡轮机组件及其过程

    公开(公告)号：US20120156054A1

    公开(公告)日：2012-06-21

    申请号：US12968410

    申请日：2010-12-15

    申请人： Benjamin Paul Lacy ,  David Vincent Bucci ,  Srikanth Chandrudu Kottilingam ,  Dennis William Cavanaugh

    发明人： Benjamin Paul Lacy ,  David Vincent Bucci ,  Srikanth Chandrudu Kottilingam ,  Dennis William Cavanaugh

    IPC分类号： F01D5/18 ,  B22D23/00 ,  B05D3/12

    CPC分类号： F01D5/288 ,  B23P2700/06 ,  C23C28/321 ,  C23C28/3215 ,  C23C28/3455 ,  F01D5/18 ,  F01D5/186 ,  F05D2230/20 ,  Y02T50/673 ,  Y02T50/676 ,  Y02T50/6765

    摘要： A process for creating a near-surface cooling passage in an air-cooled turbomachine component. The process entails forming a channel in a surface of a surface region of the component so that the channel is open at the surface and fluidically connected to a first cooling passages within the component. A metallic layer is then deposited on the surface and over the channel without filling the channel. The metallic layer closes the channel at the surface of the surface region to define therewith a second cooling passage within the component that is fluidically connected to the first cooling passages. A coating system is then deposited on the metallic layer to define an outermost surface of the component. The second cooling passage is closer to the outermost surface of the component than the first cooling passages.

    摘要翻译： 一种用于在空气冷却涡轮机组件中形成近地面冷却通道的方法。 该过程需要在部件的表面区域的表面中形成通道，使得通道在表面处是开放的并且与部件内的第一冷却通道流体连接。 然后将金属层沉积在表面上并在通道上沉积，而不填充通道。 金属层封闭在表面区域的表面处的通道，以限定该部件内的与第一冷却通道流体连接的第二冷却通道。 然后将涂层系统沉积在金属层上以限定该组件的最外表面。 第二冷却通道比第一冷却通道更靠近部件的最外表面。

    Cooling structures in the tips of turbine rotor blades
    8.
    发明授权
    Cooling structures in the tips of turbine rotor blades 有权
    涡轮转子叶片尖端的冷却结构

    公开(公告)号：US09188012B2

    公开(公告)日：2015-11-17

    申请号：US13479663

    申请日：2012-05-24

    申请人： Benjamin Paul Lacy ,  Brian Peter Arness ,  Xiuzhang James Zhang

    发明人： Benjamin Paul Lacy ,  Brian Peter Arness ,  Xiuzhang James Zhang

    IPC分类号： F01D5/18 ,  F01D5/20

    CPC分类号： F01D5/20 ,  F01D5/186 ,  F05D2260/204

    摘要： A turbine rotor blade used in a gas turbine engine, which includes an airfoil having a tip at an outer radial edge, is described. The airfoil includes a pressure sidewall and a suction sidewall that join together at a leading edge and a trailing edge of the airfoil, the pressure sidewall and the suction sidewall extending from a root to the tip. The tip includes a tip plate and, disposed along a periphery of the tip plate, a rail. The rail includes a microchannel connected to a coolant source.

    摘要翻译： 描述了一种在燃气涡轮发动机中使用的涡轮转子叶片，其包括在外径向边缘处具有尖端的翼型件。 翼型件包括压力侧壁和抽吸侧壁，该侧壁在翼型的前缘和后缘处连接在一起，压力侧壁和吸力侧壁从根部延伸到尖端。 尖端包括尖端板，并且沿着尖端板的周边布置有轨道。 导轨包括连接到冷却剂源的微通道。

    Bucket assembly for turbine system
    9.
    发明授权
    Bucket assembly for turbine system 有权
    用于涡轮机系统的铲斗总成

    公开(公告)号：US08956104B2

    公开(公告)日：2015-02-17

    申请号：US13271751

    申请日：2011-10-12

    申请人： Benjamin Paul Lacy ,  Anthony Louis Giglio

    发明人： Benjamin Paul Lacy ,  Anthony Louis Giglio

    IPC分类号： F01D5/08 ,  F01D11/08 ,  F01D5/22

    CPC分类号： F01D5/225 ,  F05D2230/31 ,  F05D2250/294 ,  F05D2260/204

    摘要： A bucket assembly is disclosed. The bucket assembly includes an airfoil having a generally aerodynamic contour and defining a tip, and a lower body portion extending generally radially inward from the airfoil. The bucket assembly further includes a tip shroud disposed on the tip of the airfoil and comprising a main body and a rail. The rail includes an exterior surface. The exterior surface defines a microchannel. The bucket assembly further includes a cover layer configured on the exterior surface.

    摘要翻译： 公开了一种铲斗组合件。 铲斗组件包括具有大致空气动力学轮廓并限定尖端的翼型件和从翼型件大致径向向内延伸的下主体部分。 铲斗组件还包括设置在翼型件的尖端上并包括主体和轨道的尖端护罩。 导轨包括外表面。 外表面限定了一个微通道。 铲斗组件还包括构造在外表面上的覆盖层。