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    ARTICLE HAVING COOLING PASSAGE NETWORK WITH INTER-ROW SUB-PASSAGES
    13.
    发明申请
    ARTICLE HAVING COOLING PASSAGE NETWORK WITH INTER-ROW SUB-PASSAGES 审中-公开

    公开(公告)号：US20200149412A1

    公开(公告)日：2020-05-14

    申请号：US16594224

    申请日：2019-10-07

    Applicant: United Technologies Corporation

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

    IPC: F01D5/18 ,  F01D5/08

    Abstract: A gas turbine engine article includes a cooling passage network embedded in an article wall between inner and outer portions of the article wall. The network has an inlet orifice through the inner portion to receive cooling air from a cavity, a sub-passage region that includes an array of pedestals, and at least one outlet orifice through the outer portion. The array of pedestals includes first pedestals arranged in a first row and second pedestals arranged in a second, adjacent row. The first pedestals and the second pedestals define inter-row sub-passages there between. Each of the inter-row sub-passages has an inlet mouth, an outlet mouth, and a compound channel connecting the inlet mouth and the outlet mouth. The compound channel includes a first channel length over which the inter-row sub-passage has a constant cross-section and a second channel length over which the inter-row sub-passage has a non-constant cross-section.

    AIRFOIL COOLING CIRCUITS
    16.
    发明申请
    AIRFOIL COOLING CIRCUITS 审中-公开

    公开(公告)号：US20200024970A1

    公开(公告)日：2020-01-23

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

    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 IMPROVED COOLING SCHEME
    17.
    发明申请
    AIRFOIL HAVING IMPROVED COOLING SCHEME 审中-公开

    公开(公告)号：US20190338652A1

    公开(公告)日：2019-11-07

    申请号：US15968865

    申请日：2018-05-02

    Applicant: United Technologies Corporation

    Inventor： Timothy J. Jennings ,  Tracy A. Propheter-Hinckley ,  Kyle C. Lana

    IPC: F01D5/18

    Abstract: Airfoils for gas turbine engines are provided. The airfoils include an airfoil body extending between leading and trailing edges in an axial direction, between pressure and suction sides in a circumferential direction, and between a root and tip in a radial direction, a first shielding sidewall cavity located adjacent one of the pressure and suction sides proximate the root of the airfoil body and extending radially toward the tip, a second shielding sidewall cavity located adjacent the other of the pressure and suction sides proximate the root of the airfoil body and extending radially toward the tip, and a shielded sidewall cavity located between the first shielding sidewall cavity and the second shielding sidewall cavity, wherein the shielded sidewall cavity is not adjacent either of the pressure or suction sides proximate the root and transitions to be proximate at least one of the pressure and suction sides proximate the tip.

    AIRFOIL HAVING IMPROVED LEADING EDGE COOLING SCHEME AND DAMAGE RESISTANCE
    18.
    发明申请
    AIRFOIL HAVING IMPROVED LEADING EDGE COOLING SCHEME AND DAMAGE RESISTANCE 审中-公开

    公开(公告)号：US20190338648A1

    公开(公告)日：2019-11-07

    申请号：US15972429

    申请日：2018-05-07

    Applicant: United Technologies Corporation

    Inventor： Timothy J. Jennings ,  Tracy A. Propheter-Hinckley ,  Kyle C. Lana

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

    Abstract: Airfoils for gas turbine engines are provided. The airfoils include an airfoil body extending between a leading edge and a trailing edge in an axial direction, between a pressure side and a suction side in a circumferential direction, and between a root and a tip in a radial direction, a first transitioning leading edge cavity located proximate the leading edge proximate the root of the airfoil body and transitioning axially toward the trailing edge as the first transitioning leading edge cavity extends radially toward the tip, and a second transitioning leading edge cavity located aft of the first transitioning leading edge cavity proximate the root of the airfoil body and transitioning axially toward the leading edge as the second transitioning leading edge cavity extends radially toward the tip. The second transitioning leading edge cavity includes an impingement sub-cavity and a film sub-cavity along the leading edge and proximate the tip.

    AIRFOILS, CORES, AND METHODS OF MANUFACTURE FOR FORMING AIRFOILS HAVING FLUIDLY CONNECTED PLATFORM COOLING CIRCUITS
    19.
    发明申请
    AIRFOILS, CORES, AND METHODS OF MANUFACTURE FOR FORMING AIRFOILS HAVING FLUIDLY CONNECTED PLATFORM COOLING CIRCUITS 审中-公开

    公开(公告)号：US20190316471A1

    公开(公告)日：2019-10-17

    申请号：US15954857

    申请日：2018-04-17

    Applicant: United Technologies Corporation

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

    IPC: F01D5/18 ,  B22D25/02 ,  B22C9/10 ,  B22C9/24

    Abstract: Methods for manufacturing airfoils of gas turbine engines are provided. The methods include forming a main body core, the main body core including a feed cavity core portion, the main body core configured to form at least a part of an airfoil including an airfoil body, a platform, and an attachment element, forming a platform circuit core having a platform core extension, wherein the platform circuit core is configured to form a cooling circuit in the platform, wherein at least one of the feed cavity core portion and the platform core extension comprises a notch, assembling the platform circuit core to the main body core such that the platform core extension engages with the feed cavity core portion at the notch, casting an airfoil using the assembled platform circuit core and main body core, and removing a platform core extension element that is formed at the location of the notch.

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