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    AIRFOIL HAVING END WALL CONTOURED PEDESTALS
    31.
    发明申请
    AIRFOIL HAVING END WALL CONTOURED PEDESTALS 审中-公开

    公开(公告)号：US20190071980A1

    公开(公告)日：2019-03-07

    申请号：US15696259

    申请日：2017-09-06

    Applicant: United Technologies Corporation

    Inventor： Brandon W. Spangler ,  Atul Kohli

    IPC: F01D5/18

    Abstract: Airfoils and gas turbine engines having the same, the airfoils including an airfoil body having a leading edge and a trailing edge extending in a radial direction, a cooling cavity defined within the airfoil body, wherein at least one wall of the cooling cavity is a curved end wall, and an end wall contoured pedestal positioned adjacent the curved end wall. The end wall contoured pedestal has a first portion with a contoured side wall and a parallel side wall, and a second portion with tapering side walls, wherein the contoured side wall faces the curved end wall, the contoured side wall paralleling a contour of the curved end wall and defining a meter section therebetween.

    BAFFLE INSERT FOR A GAS TURBINE ENGINE COMPONENT AND COMPONENT WITH BAFFLE INSERT
    34.
    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.

    Multi-lobed cooling hole
    37.
    发明授权
    Multi-lobed cooling hole 有权
    多叶冷却孔

    公开(公告)号：US09482100B2

    公开(公告)日：2016-11-01

    申请号：US13629916

    申请日：2012-09-28

    Applicant: United Technologies Corporation

    Inventor： Atul Kohli ,  Matthew S. Gleiner

    IPC: F01D5/18 ,  F01D9/06 ,  F23R3/00 ,  F23R3/06

    CPC classification number: F01D5/18 ,  F01D5/186 ,  F01D5/187 ,  F01D9/065 ,  F05D2240/81 ,  F05D2250/73 ,  F05D2260/202 ,  F23R3/002 ,  F23R3/06 ,  F23R2900/03042 ,  Y02T50/676

    Abstract: A gas turbine engine component subjected to a flow of high temperature gas includes a wall having first and second wall surfaces and a cooling hole extending through the wall. The cooling hole includes an inlet located at the first wall surface, an outlet located at the second wall surface, a metering section extending downstream from the inlet and a diffusing section extending from the metering section to the outlet. The diffusing section includes a first lobe, a second lobe and a transition region. The first lobe diverges longitudinally and laterally from the metering section and has a first shape. The second lobe is generally opposite the first lobe and diverges longitudinally and laterally from the metering section and has a second shape different from the first shape. The transition region is positioned between the first and second lobes and includes a downstream end adjacent the outlet.

    Abstract translation: 经受高温气体流动的燃气涡轮发动机部件包括具有第一和第二壁表面的壁和延伸穿过壁的冷却孔。 冷却孔包括位于第一壁表面的入口，位于第二壁表面处的出口，从入口下游延伸的计量部分和从计量部分延伸到出口的扩散部分。 扩散部分包括第一凸角，第二凸角和过渡区域。 第一个凸角从计量部分纵向和横向分开并具有第一形状。 第二叶片大致与第一叶片相对，并且从计量部分纵向和横向分叉并且具有不同于第一形状的第二形状。 过渡区域位于第一和第二凸角之间并且包括邻近出口的下游端。

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