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    LARGE-FOOTPRINT TURBINE COOLING HOLE
    11.
    发明申请
    LARGE-FOOTPRINT TURBINE COOLING HOLE 审中-公开
    大型涡轮机冷却孔

    公开(公告)号：US20160186576A1

    公开(公告)日：2016-06-30

    申请号：US14627587

    申请日：2015-02-20

    Applicant: United Technologies Corporation

    Inventor： Lane Thornton ,  Scott D. Lewis ,  Matthew A. Devore

    IPC: F01D5/18 ,  F01D25/12 ,  F01D9/04

    CPC classification number: F01D5/186 ,  F01D9/041 ,  F01D25/12 ,  F05D2220/30 ,  F05D2230/12 ,  F05D2230/13 ,  F05D2260/202 ,  Y02T50/673 ,  Y02T50/676

    Abstract: A cooling hole for a component includes a meter section and a diffuser section. The diffuser section has a footprint region defined by five sides, a first side of the five sides extending along substantially an entire height of the diffuser section and second and third sides of the five sides meeting in an obtuse angle opposite the first side. A component having the cooling hole and a method of forming the cooling hole are also disclosed.

    Abstract translation: 用于组件的冷却孔包括仪表部分和扩散器部分。 扩散器部分具有由五个侧面限定的覆盖区域，五个侧面的第一侧沿着扩散器部分的大致整个高度延伸，五边的第二和第三侧以与第一侧相对的钝角相交。 还公开了具有冷却孔的部件和形成冷却孔的方法。

    DIFFUSED PLATFORM COOLING HOLES
    12.
    发明申请
    DIFFUSED PLATFORM COOLING HOLES 审中-公开
    扩散平台冷却孔

    公开(公告)号：US20160169001A1

    公开(公告)日：2016-06-16

    申请号：US14908573

    申请日：2014-08-14

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Lane Thornton ,  Matthew Andrew Hough

    IPC: F01D5/18

    CPC classification number: F01D5/186 ,  F01D5/187 ,  F05D2220/32 ,  F05D2240/11 ,  F05D2240/81 ,  F05D2250/292 ,  F05D2250/324 ,  Y02T50/676

    Abstract: A gas turbine engine component has first and second components each having a platform with an upper surface and a lower surface and with a plurality of side faces extending between the upper and lower surfaces. The platforms are arranged adjacent to one another such that one side face of the platform faces a mating side face of an adjacent platform. At least one cooling hole is formed within the platform and has an inlet to receive a cooling flow and an outlet at least at one of the side faces. The at least one cooling hole increases in size in a direction toward the outlet. A method of cooling a gas turbine engine is also disclosed.

    Abstract translation: 燃气涡轮发动机部件具有第一和第二部件，每个部件具有一个具有上表面和下表面的平台，并且多个侧面在上表面和下表面之间延伸。 平台彼此相邻设置，使得平台的一个侧面面向相邻平台的配合侧面。 在平台内形成至少一个冷却孔，并且至少在一个侧面具有用于接收冷却流的入口和出口。 至少一个冷却孔在朝向出口的方向上尺寸增大。 还公开了一种冷却燃气涡轮发动机的方法。

    Trailing edge platform seals
    16.
    发明授权
    Trailing edge platform seals 有权

    公开(公告)号：US10196915B2

    公开(公告)日：2019-02-05

    申请号：US14726722

    申请日：2015-06-01

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Lane Thornton

    IPC: F01D11/00 ,  F01D5/22 ,  F01D5/14

    Abstract: A platform trailing edge seal for a turbomachine airfoil (e.g., a blade or vane) assembly includes a body configured to extend into an aft portion of a mateface gap defined between a circumferentially adjacent pair of turbomachine airfoil platforms to minimize flow from entering a blade-vane cavity through the aft portion of the mateface gap.

    GAS TURBINE ENGINE COMPONENT WITH SEPARATION RIB FOR COOLING PASSAGES
    17.
    发明申请
    GAS TURBINE ENGINE COMPONENT WITH SEPARATION RIB FOR COOLING PASSAGES 审中-公开
    具有用于冷却通道的分离RIB的气体涡轮发动机部件

    公开(公告)号：US20160326909A1

    公开(公告)日：2016-11-10

    申请号：US15111517

    申请日：2015-01-21

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Charles Thistle ,  Lane Thornton

    IPC: F01D25/12 ,  F01D11/08 ,  F02C7/12 ,  F01D5/18 ,  F02C3/10 ,  F02K3/06

    CPC classification number: F01D25/12 ,  F01D5/187 ,  F01D11/08 ,  F01D11/24 ,  F02C3/10 ,  F02C7/12 ,  F02K3/06 ,  F05D2240/11 ,  F05D2250/11 ,  F05D2250/121 ,  F05D2250/22 ,  F05D2250/23 ,  F05D2250/25 ,  F05D2260/2212 ,  F05D2260/2214 ,  Y02T50/676

    Abstract: A gas turbine engine component comprises a body extending between two ends and having at least two cooling passages. The body has a first wall and second wall. At least two cooling passages include a first passage that is closer to the first wall than is a second of the passages at upstream locations along a flow path. The second passage has upstream locations that are closer to the second wall than are upstream portions of the first passage. The first and second passages cross along a length of the flow path such that downstream portions of the second passage are closer to the first wall than are downstream portions of the first passage, and downstream portions of the first passage are closer to the second wall than are downstream portions of the second passage.

    Abstract translation: 燃气涡轮发动机部件包括在两端之间延伸并且具有至少两个冷却通道的主体。 身体有第一个墙壁和第二个墙壁。 至少两个冷却通道包括比沿着流动路径的上游位置处的第二通道更靠近第一壁的第一通道。 第二通道具有比第一通道的上游部分更靠近第二壁的上游位置。 所述第一通道和所述第二通道沿所述流动路径的长度交叉，使得所述第二通道的下游部分比所述第一通道的下游部分更靠近所述第一壁，并且所述第一通道的下游部分比所述第一通道的下游部分更靠近所述第二壁 是第二通道的下游部分。

    GAS TURBINE ENGINE TURBINE BLADE LEADING EDGE TIP TRENCH COOLING
    18.
    发明申请
    GAS TURBINE ENGINE TURBINE BLADE LEADING EDGE TIP TRENCH COOLING 审中-公开
    气体涡轮发动机涡轮叶片前沿叶片倾斜冷却

    公开(公告)号：US20140165593A1

    公开(公告)日：2014-06-19

    申请号：US13713371

    申请日：2012-12-13

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： San Quach ,  Lane Thornton

    IPC: F01D5/12

    CPC classification number: F01D5/186 ,  F01D5/20 ,  F05D2240/303 ,  F05D2240/307 ,  Y02T50/673 ,  Y02T50/676

    Abstract: An airfoil for a gas turbine engine includes pressure and suction walls spaced apart from one another and joined at leading and trailing edges to provide an airfoil having an exterior surface that extends in a radial direction to a tip. A tip trench is provided in the tip and wrapping at least a portion of the airfoil from the pressure side wall around the leading edge to the suction side wall. The tip trench is provided by a recess.

    Abstract translation: 用于燃气涡轮发动机的翼型件包括彼此间隔开并在前缘和后缘连接的压力和吸力壁，以提供具有沿径向方向延伸到尖端的外表面的翼型件。 尖端沟槽设置在尖端中，并且将翼型件的至少一部分从前缘的压力侧壁包裹到吸力侧壁。 尖端沟槽由凹槽提供。

    GAS TURBINE ENGINE COMPONENT COOLING CIRCUIT
    19.
    发明申请
    GAS TURBINE ENGINE COMPONENT COOLING CIRCUIT 审中-公开
    气体涡轮发动机组件冷却电路

    公开(公告)号：US20140075947A1

    公开(公告)日：2014-03-20

    申请号：US13621968

    申请日：2012-09-18

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Steven Bruce Gautschi ,  Lane Thornton

    IPC: F01D5/18 ,  F01D25/12 ,  F01D9/00

    CPC classification number: F01D5/189 ,  F05D2240/126 ,  Y02T50/676

    Abstract: A component for a gas turbine engine, according to an exemplary aspect of the present disclosure includes, among other things, a body portion and a cooling circuit disposed inside of the body portion. The cooling circuit includes a first baffle received within a first core cavity that extends inside of the body portion, a second baffle received within a second core cavity that extends inside of the body portion, and a first rib disposed between the first core cavity and the second core cavity. The first baffle is in fluid communication with the second baffle through the first rib.

    Abstract translation: 根据本公开的示例性方面的用于燃气涡轮发动机的部件包括设置在主体部分内部的主体部分和冷却回路。 冷却回路包括容纳在主体部分内部延伸的第一芯腔内的第一挡板，容纳在主体部分内延伸的第二芯腔内的第二挡板，以及设置在第一芯腔和第二芯腔之间的第一肋 第二核心腔。 第一挡板通过第一肋与第二挡板流体连通。

    Gas turbine engine turbine blade leading edge tip trench cooling
    20.
    发明授权
    Gas turbine engine turbine blade leading edge tip trench cooling 审中-公开

    公开(公告)号：US10655473B2

    公开(公告)日：2020-05-19

    申请号：US13713371

    申请日：2012-12-13

    Applicant: United Technologies Corporation

    Inventor： San Quach ,  Lane Thornton

    IPC: F01D5/18

    Abstract: An airfoil for a gas turbine engine includes pressure and suction walls spaced apart from one another and joined at leading and trailing edges to provide an airfoil having an exterior surface that extends in a radial direction to a tip. A tip trench is provided in the tip and wrapping at least a portion of the airfoil from the pressure side wall around the leading edge to the suction side wall. The tip trench is provided by a recess.

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