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    Airfoil cooling circuits
    32.
    发明授权
    Airfoil cooling circuits 有权

    公开(公告)号：US10808551B2

    公开(公告)日：2020-10-20

    申请号：US16397180

    申请日：2019-04-29

    Applicant: United Technologies Corporation

    Inventor： Eric A. Hudson ,  Tracy A. Propheter-Hinckley ,  San Quach ,  Matthew A. Devore

    IPC: B22C9/10 ,  B22C9/24 ,  F01D5/18

    Abstract: An airfoil includes leading and trailing edges; first and second sides extending from the leading edge to the trailing edge, each side having an exterior surface; a core passage located between the first and second sides and the leading and trailing edges; and a wall structure located between the core passage and the exterior surface of the first side. The wall structure includes a plurality of cooling fluid inlets communicating with the core passage for receiving cooling fluid from the core passage, a plurality of cooling fluid outlets on the exterior surface of the first side for expelling cooling fluid and forming a cooling film along the exterior surface of the first side, and a plurality of cooling passages communicating with the plurality of cooling fluid inlets and the plurality of cooling fluid outlets. At least a portion of one cooling passage extends between adjacent cooling fluid outlets.

    Component core with shaped edges
    34.
    发明授权
    Component core with shaped edges 有权

    公开(公告)号：US10677069B2

    公开(公告)日：2020-06-09

    申请号：US16199825

    申请日：2018-11-26

    Applicant: United Technologies Corporation

    Inventor： Matthew A. Devore ,  Matthew S. Gleiner ,  Douglas C. Jenne

    IPC: F01D5/18 ,  F01D9/04 ,  F01D11/08 ,  F01D25/12 ,  B22C9/10

    Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a plurality of blade outer air seals and a plurality of airfoils, at least one of seals and airfoils including at least one cooling passage. The cooling passage includes a first wall and an opposed second wall bounding the cooling passage, a surface contour of the first wall having a plurality of first surface features and a surface contour of the second wall having a plurality of second surface features. The first surface features and the second surface features are arranged such that a width of the cooling passage varies along a length of the cooling passage defined by the first surface features and the second surface features. The first surface features have a first profile, and the second surface features have a second, different profile. A casting core for forming cooling passages in an aircraft component is also disclosed.

    Internal cooling cavity with trip strips
    35.
    发明授权
    Internal cooling cavity with trip strips 有权

    公开(公告)号：US10605094B2

    公开(公告)日：2020-03-31

    申请号：US14602035

    申请日：2015-01-21

    Applicant: United Technologies Corporation

    Inventor： San Quach ,  Atul Kohli ,  Matthew A. Devore ,  Steven Bruce Gautschi

    IPC: F01D5/18

    Abstract: An airfoil is provided. The airfoil may comprise a cross over, an impingement chamber in fluid communication with the cross over, and a first trip strip disposed on a first surface of the impingement chamber. A cooling system is also provided. The cooling system may comprise an impingement chamber, a first trip strip on a first surface of the impingement chamber, and a second trip strip on a second surface of the impingement chamber. An internally cooled engine part is further provided. The internally cooled part may comprise a cross over and an impingement chamber in fluid communication with the cross over. The cross over may be configured to direct air towards a first surface of the impingement chamber. A first trip strip may be disposed on the first surface of the impingement chamber.

    COMPONENT CORE WITH SHAPED EDGES
    36.
    发明申请
    COMPONENT CORE WITH SHAPED EDGES 审中-公开

    公开(公告)号：US20200024963A1

    公开(公告)日：2020-01-23

    申请号：US16199825

    申请日：2018-11-26

    Applicant: United Technologies Corporation

    Inventor： Matthew A. Devore ,  Matthew S. Gleiner ,  Douglas C. Jenne

    IPC: F01D5/18 ,  F01D9/04 ,  F01D11/08 ,  F01D25/12

    Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a plurality of blade outer air seals and a plurality of airfoils, at least one of seals and airfoils including at least one cooling passage. The cooling passage includes a first wall and an opposed second wall bounding the cooling passage, a surface contour of the first wall having a plurality of first surface features and a surface contour of the second wall having a plurality of second surface features. The first surface features and the second surface features are arranged such that a width of the cooling passage varies along a length of the cooling passage defined by the first surface features and the second surface features. The first surface features have a first profile, and the second surface features have a second, different profile. A casting core for forming cooling passages in an aircraft component is also disclosed.

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