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    Method for 3-D printing a pattern for the surface of a turbine shroud
    61.
    发明授权
    Method for 3-D printing a pattern for the surface of a turbine shroud 有权
    用于3D打印涡轮机护罩表面的图案的方法

    公开(公告)号：US09289917B2

    公开(公告)日：2016-03-22

    申请号：US14043031

    申请日：2013-10-01

    Applicant: General Electric Company

    Inventor： David Vincent Bucci ,  Srikanth Chandrudu Kottilingam ,  Prabhjot Singh

    IPC: B05D5/00 ,  C04B35/48 ,  C04B35/515 ,  B28B1/00 ,  B28B17/02 ,  F01D11/12 ,  B33Y10/00 ,  B29C67/00 ,  F01D5/20

    CPC classification number: B28B1/001 ,  B05D5/00 ,  B28B17/02 ,  B29C64/00 ,  B29C64/165 ,  B33Y10/00 ,  F01D5/20 ,  F01D11/125 ,  F05D2230/30 ,  F05D2230/50 ,  F05D2230/60 ,  F05D2230/90 ,  F05D2250/18 ,  F05D2250/181

    Abstract: A method of making an article of manufacture is provided and includes the steps of spraying a first coating onto a substrate, and depositing a second coating on the first coating by 3-D printing a material disposed in a pattern. The pattern includes ridges disposed at a base surface of a turbine part. Each ridge defined by first and second sidewalls, each sidewall having a first and second end. The ends extend from the base surface, the sidewalls slope toward each other until meeting at second ends of respective first and second sidewalls defining a centerline and a top portion of the ridge. The sidewalls are inclined with substantially equal but opposite slopes with respect to the base surface. The ridges correspond to a back portion of a turbine bucket and are oriented at a first angle with respect to an axis of rotation of the bucket.

    Abstract translation: 提供了一种制造制品的方法，包括以下步骤：将第一涂层喷涂到基材上，并通过3D印刷以图案布置的材料在第一涂层上沉积第二涂层。 该图案包括设置在涡轮部分的基面处的脊。 每个脊由第一和第二侧壁限定，每个侧壁具有第一和第二端。 所述端部从所述基部表面延伸，所述侧壁朝向彼此倾斜，直到在限定所述脊的中心线和顶部的相应的第一和第二侧壁的第二端处相遇。 侧壁相对于基面具有大致相等但相反的倾斜倾斜。 脊对应于涡轮机叶片的后部并相对于铲斗的旋转轴线以第一角度定向。

    METAL CHEMISTRY FOR IMPROVED WELDABILITY OF SUPER ALLOYS
    63.
    发明申请
    METAL CHEMISTRY FOR IMPROVED WELDABILITY OF SUPER ALLOYS 有权
    用于改善超合金焊接性的金属化学

    公开(公告)号：US20150129644A1

    公开(公告)日：2015-05-14

    申请号：US14602865

    申请日：2015-01-22

    Applicant: General Electric Company

    Inventor： Yan Cui ,  Srikanth Chandrudu Kottilingam ,  Dechao Lin ,  Brian Lee Tollison

    IPC: B23K35/30 ,  B23K31/02 ,  B23K35/02

    CPC classification number: B23K35/304 ,  B23K31/02 ,  B23K35/0261 ,  B23K35/3033 ,  C22C19/051 ,  C22C19/056 ,  C22C19/057

    Abstract: A metal chemistry includes an amount of chromium weight of between about 9.0% and about 16% by weight, an amount of cobalt of between about 7.0% and about 14% by weight, an amount of molybdenum of between about 10% and about 20% by weight, an amount of iron of between about 1.0% and about 5.0% by weight, an amount of aluminum of between about 0.05% and about 0.75% by weight, an amount of titanium of between about 0.5% and about 2.0% by weight, an amount of manganese not to exceed about 0.8% by weight, an amount of carbon of between about 0.02% and about 0.10% by weight, an amount of a titanium+aluminum alloy of between about 0.55% and about 2.75% by weight, and an amount of nickel.

    Abstract translation: 金属化学性质包括约9.0％至约16％重量的铬重量，约7.0％至约14％重量的钴的量，约10％至约20％的钼的量， 的铁量为约1.0％至约5.0％，铝的量为约0.05％至约0.75％重量，钛的量为约0.5％至约2.0％重量 ，锰的量不超过约0.8重量％，碳量在约0.02重量％至约0.10重量％之间，钛+铝合金的量在约0.55重量％至约2.75重量％之间， 和一定量的镍。

    TURBINE COMPONENT AND METHODS OF ASSEMBLING THE SAME
    65.
    发明申请
    TURBINE COMPONENT AND METHODS OF ASSEMBLING THE SAME 有权
    涡轮组件及其组装方法

    公开(公告)号：US20150017018A1

    公开(公告)日：2015-01-15

    申请号：US13940806

    申请日：2013-07-12

    Applicant: General Electric Company

    Inventor： Benjamin Paul Lacy ,  Brian Gene Brzek ,  Srikanth Chandrudu Kottilingam ,  David Edward Schick

    IPC: F01D5/18 ,  B23P15/04 ,  F01D25/14

    CPC classification number: F01D5/186 ,  B23P15/04 ,  B23P2700/06 ,  F01D5/288 ,  F01D25/145 ,  F05D2260/202 ,  Y10T29/49337

    Abstract: A turbine component is provided. The turbine component includes an airfoil having a first surface and a second surface. A thermal barrier coating is coupled to the second surface, wherein the thermal barrier coating includes a first portion, a second portion and a trench defined between the first and second portions. A channel is coupled in flow communication to the first surface and the trench, wherein the channel includes a first sidewall and a second sidewall opposite of the first sidewall. The first and second sidewalls extend from the first surface and toward the trench at an angle. The turbine component includes a cover coupled to the second surface, wherein the cover includes a first end coupled to the first portion and a second end extending into the trench and spaced from the second portion.

    Abstract translation: 提供涡轮机部件。 涡轮机部件包括具有第一表面和第二表面的翼型件。 热障涂层耦合到第二表面，其中热障涂层包括限定在第一和第二部分之间的第一部分，第二部分和沟槽。 通道以与第一表面和沟槽流动连通的方式耦合，其中该通道包括第一侧壁和与第一侧壁相对的第二侧壁。 第一和第二侧壁以一定角度从第一表面延伸到沟槽。 涡轮机部件包括联接到第二表面的盖，其中盖包括联接到第一部分的第一端和延伸到沟槽中并与第二部分间隔开的第二端。

    COMPONENTS WITH NEAR-SURFACE COOLING MICROCHANNELS AND METHODS FOR PROVIDING THE SAME
    66.
    发明申请
    COMPONENTS WITH NEAR-SURFACE COOLING MICROCHANNELS AND METHODS FOR PROVIDING THE SAME 审中-公开
    具有表面冷却微型通道的组件及其提供方法

    公开(公告)号：US20140170433A1

    公开(公告)日：2014-06-19

    申请号：US13719772

    申请日：2012-12-19

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： David Edward Schick ,  Srikanth Chandrudu Kottilingam ,  Benjamin Paul Lacy ,  John Wesley Harris, JR.

    IPC: B22F7/08

    CPC classification number: B22F7/08 ,  B22F5/009 ,  B22F5/04 ,  B22F5/10 ,  B23P2700/06 ,  C22C1/0433 ,  F01D5/187 ,  F05D2230/22 ,  F05D2260/204 ,  Y02T50/671 ,  Y02T50/676 ,  Y10T428/12028 ,  Y10T428/24744

    Abstract: Methods for providing a near-surface cooling microchannel in a component include forming a near-surface cooling microchannel in a first surface of a pre-sintered preform, disposing the first surface of the pre-sintered preform onto an outer surface of the base article such that an opening of the outer surface of the base article is aligned with the near-surface cooling microchannel in the first surface of the pre-sintered preform, and, heating the pre-sintered preform to bond it to the base article, wherein the opening of the outer surface of the base article remains aligned with the near-surface cooling microchannel in the first surface of the pre-sintered preform.

    Abstract translation: 在组件中提供近表面冷却微通道的方法包括在预烧结预型件的第一表面中形成近表面冷却微通道，将预烧结预制件的第一表面设置在基底制品的外表面上， 基底制品的外表面的开口与预烧结预型件的第一表面中的近表面冷却微通道对准，并且加热预烧结的预成型件以将其粘合到基底制品上，其中开口 基底制品的外表面与预烧结预制件的第一表面中的近表面冷却微通道保持一致。

    Coolant delivery via an independent cooling circuit
    68.
    发明授权
    Coolant delivery via an independent cooling circuit 有权

    公开(公告)号：US11480070B2

    公开(公告)日：2022-10-25

    申请号：US16663873

    申请日：2019-10-25

    Applicant: General Electric Company

    Inventor： Matthew Troy Hafner ,  Brad Wilson VanTassel ,  Christopher Donald Porter ,  Srikanth Chandrudu Kottilingam

    IPC: F01D5/18 ,  F01D25/12 ,  F01D25/14 ,  F23R3/00 ,  B33Y80/00

    Abstract: A coolant delivery system for a component of a gas turbine system includes: a plurality of independent circuits of cooling channels embedded within an exterior wall of the component, each independent circuit of cooling channels including a plurality of headers and a plurality of feed tubes fluidly coupling the plurality of headers to a supply of cooling fluid; and an impingement plate connected to the exterior wall of the component by the plurality of feed tubes of the independent circuits of cooling channels, wherein, in each of the plurality of independent circuits of cooling channels, the cooling fluid flows through the plurality of feed tubes and the plurality of headers into the circuit of cooling channels only in response to a formation of a breach in the exterior wall of the component that exposes at least one of the cooling channels of the circuit of cooling channels.

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