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    AIRFOIL WITH WALL THAT TAPERS IN THICKNESS
    211.
    发明申请
    AIRFOIL WITH WALL THAT TAPERS IN THICKNESS 审中-公开

    公开(公告)号：US20200332662A1

    公开(公告)日：2020-10-22

    申请号：US16594353

    申请日：2019-10-07

    Applicant: United Technologies Corporation

    Inventor： Allan N. Arisi ,  Tracy A. Propheter-Hinckley

    IPC: F01D5/18 ,  F01D25/12 ,  F02C7/18

    Abstract: An airfoil section has an airfoil wall that defines a leading end, a trailing end, and first and second sides that join the leading end and the trailing end. The airfoil wall circumscribes an internal core cavity. A skincore passage is embedded in the first side of the airfoil wall between inner and outer portions of the first side of airfoil wall. The skincore passage defines a passage forward edge and a passage aft edge. The first side of the airfoil wall has a portion that tapers in thickness at the passage aft edge. A cooling passage is embedded in the second side of the airfoil wall between inner and outer portions of the second side of airfoil wall. The inner portion of the second side of the airfoil wall includes a protrusion located across the internal core cavity from the portion of the first side that tapers in thickness.

    Airfoil cooling circuits
    213.
    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.

    Airfoil having internal hybrid cooling cavities
    216.
    发明授权
    Airfoil having internal hybrid cooling cavities 有权

    公开(公告)号：US10704398B2

    公开(公告)日：2020-07-07

    申请号：US15723486

    申请日：2017-10-03

    Applicant: United Technologies Corporation

    Inventor： Tracy A. Propheter-Hinckley ,  Carey Clum ,  Timothy J. Jennings

    IPC: F01D5/08 ,  F01D5/18 ,  B22C13/10 ,  F01D9/06 ,  B22C9/24 ,  B22C9/10 ,  B22C9/22

    Abstract: Airfoil bodies having a first core cavity and a second core cavity located within the airfoil body and adjacent the first core cavity, wherein the second core cavity is defined by a first cavity wall, a second cavity wall, a first exterior wall, and a second exterior wall, wherein the first cavity wall is located between the first and second core cavities. The first cavity wall includes a first surface angled toward the first exterior wall and a second surface angled toward the second exterior wall. At least one first cavity impingement hole is formed within the first surface. At least one circuit exit is located in the first exterior wall, the at least one circuit exit arranged to expel air from the second core cavity through the first exterior wall.

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