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    IMPINGEMENT COOLING ARRANGEMENT FOR AIRFOILS
    111.
    发明申请
    IMPINGEMENT COOLING ARRANGEMENT FOR AIRFOILS 审中-公开

    公开(公告)号：US20190211689A1

    公开(公告)日：2019-07-11

    申请号：US15866557

    申请日：2018-01-10

    Applicant: United Technologies Corporation

    Inventor： Jason Shenny ,  Jeffrey T. Morton ,  Alberto A. Mateo ,  San Quach ,  Gregory Anselmi

    IPC: F01D5/18 ,  F04D29/32 ,  F04D29/58

    CPC classification number: F01D5/186 ,  F01D5/187 ,  F04D29/324 ,  F04D29/582 ,  F05D2220/32 ,  F05D2240/303 ,  F05D2260/201 ,  F05D2260/202

    Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section that has an internal wall and an external wall. The external wall defines pressure and suction sides that extends in a chordwise direction between a leading edge and a trailing edge, a first impingement cavity and a second impingement cavity bounded by the external wall at a leading edge region that defines the leading edge, a first feeding cavity separated from the first impingement cavity and from the second impingement cavity by the internal wall, and a first crossover passage within the internal wall that connects the first impingement cavity and the first feeding cavity. The first crossover passage defines a first passage axis that intersects a surface of the first impingement cavity. A second crossover passage within the internal wall connects to the second impingement cavity. The second crossover passage defines a second passage axis that intersects a surface of the second impingement cavity.

    Internally cooled engine components
    112.
    发明授权
    Internally cooled engine components 有权

    公开(公告)号：US10344607B2

    公开(公告)日：2019-07-09

    申请号：US15416900

    申请日：2017-01-26

    Applicant: United Technologies Corporation

    Inventor： Jeffrey T. Morton ,  San Quach

    IPC: F01D9/06 ,  F01D5/18

    Abstract: A component of a gas turbine engine is provided. The component may include an external surface with a skin cavity adjacent the external surface. The skin cavity may be defined by a hot-side surface and a cool-side surface with the hot-side surface between the cool-side surface and the external surface. A flat portion may be disposed on the hot-side surface and may, for example, define a wall-thickness check region. A protrusion may be disposed on the cool-side surface opposite the flat portion on the hot-side surface. The hot-side surface and the cool-side surface may tend to increase a heat transfer coefficient along the flat portion of the hot-side surface, which may also define a wall thickness check region.

    Gas turbine engine component cooling circuit
    114.
    发明授权
    Gas turbine engine component cooling circuit 有权

    公开(公告)号：US10301947B2

    公开(公告)日：2019-05-28

    申请号：US15997943

    申请日：2018-06-05

    Applicant: United Technologies Corporation

    Inventor： Tracy A. Propheter-Hinckley ,  Steven Bruce Gautschi ,  San Quach

    IPC: B22C9/10 ,  F01D5/18 ,  B22C9/04 ,  F28F7/00 ,  B23P15/02

    Abstract: A method of manufacturing a component for a gas turbine engine according to an exemplary aspect of the present disclosure includes forming the component with a first manufacturing technique to include a first cavity and a second cavity, and a microcircuit in fluid communication with the first cavity, the component including an outer wall and a ribbed portion or a bulged portion extending from the outer wall. The exemplary method includes forming a plunged hole with a second manufacturing technique different from the first manufacturing technique to intersect at least a portion of the microcircuit and extend into the ribbed portion or the bulged portion.

    PANEL SURFACE POCKETS FOR COATING RETENTION
    119.
    发明申请
    PANEL SURFACE POCKETS FOR COATING RETENTION 审中-公开

    公开(公告)号：US20180283688A1

    公开(公告)日：2018-10-04

    申请号：US15477518

    申请日：2017-04-03

    Applicant: United Technologies Corporation

    Inventor： San Quach ,  Andreas Sadil ,  Donald W. Peters

    IPC: F23R3/00 ,  F01D25/30

    CPC classification number: F23R3/002 ,  F01D25/145 ,  F01D25/30 ,  F05D2220/32 ,  F05D2230/90 ,  F05D2240/35 ,  F05D2300/611 ,  Y02T50/675

    Abstract: A coated panel for a gas turbine engine includes a panel having a panel inner surface and a pocket formed in the panel inner surface, the pocket having a pocket depth. A coating is applied to the pocket such that a coating edge is disposed within the pocket to enhance coating retention to the panel. A gas turbine engine includes a turbine, a combustor to supply hot combustion gases to the turbine along a gas path, and one or more coated panels located along the gas path. The one or more panels includes a panel having a panel inner surface, and a pocket formed in the panel inner surface, the pocket having a pocket depth. A coating is applied to the pocket such that a coating edge is located within the pocket to enhance coating retention to the panel.

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