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    DIRT SEPARATOR FOR INTERNALLY COOLED COMPONENTS
    21.
    发明申请
    DIRT SEPARATOR FOR INTERNALLY COOLED COMPONENTS 审中-公开

    公开(公告)号：US20190218940A1

    公开(公告)日：2019-07-18

    申请号：US15873475

    申请日：2018-01-17

    Applicant: United Technologies Corporation

    Inventor： Tracy A. Propheter-Hinckley ,  Joel H. Wagner

    IPC: F01D25/32 ,  F01D5/18

    Abstract: Aspects of the disclosure are directed to a gas turbine engine internally cooled component airfoil having a peripheral wall having an external surface comprising a suction surface and a pressure surface laterally spaced from the suction surface, the surfaces extending chordwisely from a leading edge to a trailing edge and radially from a proximate end to a distal end. The gas turbine engine internally cooled component airfoil may include a cooling system having at least one or more passages bounded in part by the peripheral wall, where at least a first of the one or more passages includes a first passage pressure side surface that includes an interior protrusion including a first sloped surface extending to a peak of the interior protrusion and a second sloped surface extending from the peak substantially in the direction of the pressure side surface. The slope of the second sloped surface may be greater than the slope of the first sloped surface and a first cooling hole extends from the second sloped surface through the interior protrusion to vent the first of the one or more passages to the pressure side surface.

    GAS TURBINE ENGINE COMPONENT COOLING CIRCUIT
    23.
    发明申请
    GAS TURBINE ENGINE COMPONENT COOLING CIRCUIT 审中-公开

    公开(公告)号：US20190017390A1

    公开(公告)日：2019-01-17

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

    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.

    AIRFOIL COOLING CIRCUITS
    28.
    发明申请
    AIRFOIL COOLING CIRCUITS 审中-公开

    公开(公告)号：US20180128115A1

    公开(公告)日：2018-05-10

    申请号：US15866134

    申请日：2018-01-09

    Applicant: United Technologies Corporation

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

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

    CPC classification number: F01D5/187 ,  B22C9/10 ,  B22C9/108 ,  B22C9/24 ,  F01D5/186 ,  F05D2230/211 ,  F05D2260/204 ,  F05D2260/2212

    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.

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