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    BAFFLE INSERT FOR A GAS TURBINE ENGINE COMPONENT AND COMPONENT WITH BAFFLE INSERT
    131.
    发明申请
    BAFFLE INSERT FOR A GAS TURBINE ENGINE COMPONENT AND COMPONENT WITH BAFFLE INSERT 有权

    公开(公告)号：US20170159456A1

    公开(公告)日：2017-06-08

    申请号：US14961726

    申请日：2015-12-07

    Applicant: United Technologies Corporation

    Inventor： Brandon W. Spangler ,  Atul Kohli

    IPC: F01D5/18 ,  F01D25/12 ,  F01D11/08 ,  F23R3/00 ,  F01D9/02

    Abstract: A component of a gas turbine engine having: an internal cooling cavity; a baffle insert configured to be inserted into the internal cooling cavity; a plurality of trip strips extending upwardly from an exterior surface of the baffle insert; at least one separating feature located between a pair of ends of a pair of the plurality of trip strips, wherein the plurality of trip strips and the at least one separating feature are spaced from an interior surface of the internal cooling cavity; a plurality of trip strips extending upwardly from the interior surface; and at least one separating feature located between a pair of ends of the plurality of trip strips located on the interior surface of the internal cooling cavity, wherein the plurality of trip strips and the at least one separating feature of the interior surface are spaced from the exterior surface of the baffle insert.

    SEAL ARRANGEMENT FOR TURBINE ENGINE COMPONENT
    135.
    发明申请
    SEAL ARRANGEMENT FOR TURBINE ENGINE COMPONENT 审中-公开
    涡轮发动机部件的密封安装

    公开(公告)号：US20160326898A1

    公开(公告)日：2016-11-10

    申请号：US14704278

    申请日：2015-05-05

    Applicant: United Technologies Corporation

    Inventor： Dominic J. Mongillo, JR. ,  Brandon W. Spangler ,  Lane Thornton

    IPC: F01D11/00

    CPC classification number: F01D11/006 ,  F01D11/005 ,  F01D25/246 ,  F05D2240/11 ,  F05D2240/57 ,  F05D2250/182 ,  Y02T50/672

    Abstract: A component for a gas turbine engine according to an example of the present disclosure includes, among other things, a body including a cold side surface adjacent to a mate face. A plurality of ridges extends from the cold side surface. A seal member abuts the plurality of ridges to define a plurality of cooling passages. The seal member is configured to move between a first position and a second position relative to the plurality of ridges. Each of the plurality of cooling passages includes a first inlet defined at the first position and a second, different inlet defined at the second position. A method of sealing between adjacent components of a gas turbine engine is also disclosed.

    Abstract translation: 根据本公开的示例的用于燃气涡轮发动机的部件包括包括邻近配合面的冷侧表面的主体。 多个脊从冷侧表面延伸。 密封构件邻接多个脊以限定多个冷却通道。 密封构件被构造成相对于多个脊在第一位置和第二位置之间移动。 多个冷却通道中的每一个包括限定在第一位置处的第一入口和限定在第二位置处的第二不同入口。 还公开了一种在燃气涡轮发动机的相邻部件之间的密封方法。

    BAFFLE INSERTS
    136.
    发明申请
    BAFFLE INSERTS 审中-公开
    宝贝插件

    公开(公告)号：US20160258306A1

    公开(公告)日：2016-09-08

    申请号：US14635168

    申请日：2015-03-02

    Applicant: United Technologies Corporation

    Inventor： Brandon W. Spangler ,  Gina Cavallo

    IPC: F01D9/06 ,  F01D25/12 ,  F01D9/04

    CPC classification number: F01D9/065 ,  F01D5/188 ,  F01D9/041 ,  F01D25/12 ,  F05D2220/32 ,  F05D2230/64 ,  F05D2230/642 ,  F05D2240/12 ,  F05D2240/126 ,  F05D2260/221

    Abstract: An airfoil includes an airfoil body extending from an inner diameter platform to an opposed outer diameter platform along a longitudinal axis. The airfoil body defines a leading edge and a trailing edge and has a cavity defined between the leading edge, the trailing edge, the inner diameter platform and the outer diameter platform. The cavity includes an airfoil protrusion extending inward from an inner surface of the airfoil body. The airfoil includes a baffle body within the cavity extending along a baffle body axis. The baffle body has a baffle protrusion extending along a central protrusion axis at an angle with respect to the baffle body axis. The end of the baffle protrusion abuts an end of the airfoil protrusion. A flow path is defined between the inner surface of the airfoil body and the outer surface of the baffle body.

    Abstract translation: 机翼包括从内径平台沿着纵向轴线延伸到相对的外径平台的翼型件主体。 机翼本体限定前缘和后缘，并且具有限定在前缘，后缘，内径平台和外径平台之间的空腔。 空腔包括从翼型体的内表面向内延伸的翼型突起。 翼型件包括沿着挡板主体轴线延伸的腔体内的挡板体。 挡板体具有挡板突出部，该挡板突起沿着中心突出轴线相对于挡板主体轴线成一定角度延伸。 挡板突出部的端部邻接翼型件突出部的一端。 在翼型体的内表面和挡板体的外表面之间限定流动路径。

    AIRFOIL SUPPORT AND COOLING SCHEME
    137.
    发明申请
    AIRFOIL SUPPORT AND COOLING SCHEME 有权
    气翼支撑和冷却方案

    公开(公告)号：US20160215628A1

    公开(公告)日：2016-07-28

    申请号：US14605366

    申请日：2015-01-26

    Applicant: United Technologies Corporation

    Inventor： Brandon W. Spangler ,  Edwin Otero ,  Daniel A. Snyder ,  Jaimie Taraskevich ,  Di Wu

    IPC: F01D5/18 ,  F02C3/04 ,  F02C7/18 ,  F01D5/14

    CPC classification number: F01D5/187 ,  F01D5/147 ,  F02C3/04 ,  F02C7/18 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2260/22141 ,  Y02T50/676

    Abstract: In various embodiments, an airfoil used as a turbine blade for a turbine wheel in a gas turbine engine is provided. The airfoil may comprise a root, a tip, and a body. The root may have a first area. The tip may have a second area. The body may have a chord bounded by the root and the tip. The body may also define a cooling chamber. The cooling chamber may have a first rib substantially perpendicular to the chord. The cooling chamber may also have a second rib extending partially between the root and the tip.

    Abstract translation: 在各种实施例中，提供了用作燃气涡轮发动机中的涡轮机叶轮的涡轮叶片的翼型件。 翼型件可以包括根部，尖端和主体。 根可能有第一个区域。 尖端可以具有第二区域。 身体可能有一个由根和尖端限定的和弦。 主体还可以限定冷却室。 冷却室可以具有基本上垂直于弦的第一肋。 冷却室还可以具有部分地在根部和尖端之间延伸的第二肋条。

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