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    AIRFOIL WITH BAFFLE SHOWERHEAD AND COOLING PASSAGE NETWORK HAVING AFT INLET
    91.
    发明申请
    AIRFOIL WITH BAFFLE SHOWERHEAD AND COOLING PASSAGE NETWORK HAVING AFT INLET 审中-公开

    公开(公告)号：US20200332713A1

    公开(公告)日：2020-10-22

    申请号：US16667941

    申请日：2019-10-30

    Applicant: United Technologies Corporation

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

    IPC: F02C7/12 ,  F01D9/02 ,  F01D9/06

    Abstract: An airfoil has a leading end, a trailing end, and first and second sides that join the leading end and the trailing end. A rib extends from the first side to the second side and partitions an internal core cavity into a forward cavity and an aft cavity. A baffle is disposed in the forward cavity and has a showerhead array of impingement orifices adjacent the leading end of the airfoil wall. A cooling passage network is embedded in the airfoil wall between inner and outer portions of the airfoil wall. The cooling passage network has an inlet orifice through the inner portion of the airfoil wall, an array of pedestals, and at least one outlet orifice through the outer portion. The inlet orifice opens to the forward cavity at a location aft of the showerhead array of impingement orifices.

    AIRFOIL WITH COOLING PASSAGE NETWORK HAVING ARCED LEADING EDGE
    92.
    发明申请
    AIRFOIL WITH COOLING PASSAGE NETWORK HAVING ARCED LEADING EDGE 审中-公开

    公开(公告)号：US20200332665A1

    公开(公告)日：2020-10-22

    申请号：US16594328

    申请日：2019-10-07

    Applicant: United Technologies Corporation

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

    IPC: F01D5/18

    Abstract: An airfoil includes an airfoil section that has an airfoil wall that defines an arced leading end, a trailing end, and first and second sides that join the arced leading end and the trailing end. The first and second sides span in a longitudinal direction between first and second ends. The airfoil wall circumscribes an internal core cavity. There is an arced rib in the internal core cavity. A cooling passage network is embedded in the airfoil wall between inner and outer portions of the airfoil wall. The cooling passage network has a trailing edge and an arced leading edge.

    AIRFOIL WITH COOLING PASSAGE CIRCUIT THROUGH PLATFORMS AND AIRFOIL SECTION
    93.
    发明申请
    AIRFOIL WITH COOLING PASSAGE CIRCUIT THROUGH PLATFORMS AND AIRFOIL SECTION 审中-公开

    公开(公告)号：US20200332661A1

    公开(公告)日：2020-10-22

    申请号：US16594125

    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 includes a cooling passage circuit that has a first plenum, a skincore passage, a first connector passage, a second plenum, and a second connector passage. The first plenum is in a first platform and extends adjacent a first side, a trailing end, and a second side of and airfoil section. The skincore passage is embedded in the first side of the airfoil section and extends longitudinally. The first connector passage is longitudinally spaced from an internal core cavity in the airfoil section so as to extend around the cavity. The first connector passage connects the first plenum with the skincore passage. The second plenum is in the second platform and extends adjacent the first side, the trailing end, and the second side of the airfoil section. The second connector passage connects the skincore passage with the second plenum.

    Gaspath component including minicore plenums
    94.
    发明授权
    Gaspath component including minicore plenums 有权

    公开(公告)号：US10808571B2

    公开(公告)日：2020-10-20

    申请号：US15629812

    申请日：2017-06-22

    Applicant: United Technologies Corporation

    Inventor： Tracy A. Propheter-Hinckley ,  Matthew A. Devore ,  Renee J. Behlman

    IPC: F01D5/08 ,  F01D25/12 ,  F01D5/18 ,  F01D5/14

    Abstract: A turbine engine component includes a wall extending from a leading edge to a trailing edge. The wall includes a hot side facing a gaspath when the gaspath component is in an installed state, and a cold side opposite the hot side. At least one minicore cooling circuit is disposed between the hot side and the cold side within the wall. At least one cooling fluid inlet connects the minicore cooling circuit to a coolant source. At least one film cooling hole connects the minicore cooling circuit to the hot side surface. The minicore cooling circuit includes an edge plenum having a thickness normal to the hot side surface that is larger than a thickness of the majority of the minicore cooling circuit normal to the hot side surface. The edge plenum is a portion of the at least one minicore cooling circuit most proximate to one of the leading edge and the trailing edge.

    Impingement cooling baffle
    96.
    发明授权
    Impingement cooling baffle 有权

    公开(公告)号：US10781715B2

    公开(公告)日：2020-09-22

    申请号：US14976069

    申请日：2015-12-21

    Applicant: United Technologies Corporation

    Inventor： Tracy A. Propheter-Hinckley

    IPC: F01D25/12 ,  F01D9/06 ,  F01D9/02 ,  F01D5/18 ,  F02C3/04

    Abstract: A component for a gas turbine engine includes a first component end, a second component end and a cavity extending from the first component end to the second component end. A baffle assembly is located in the cavity including a first baffle portion inserted into the cavity and a second baffle portion inserted into the cavity. The first baffle portion overlaps the second baffle portion. A vane for a gas turbine engine includes an outer platform, an inner platform and an airfoil portion extending. A core extends through the airfoil portion. A baffle is positioned in the core and is offset from the core wall. The baffle includes a first baffle portion inserted into the core and a second baffle portion inserted into the core. One of the first baffle portion or the second baffle portion overlaps the other of the first baffle portion or the second baffle portion.

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