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    Turbine blade with tip vortex control and tip shelf
    1.
    发明授权
    Turbine blade with tip vortex control and tip shelf 有权

    公开(公告)号：US10801325B2

    公开(公告)日：2020-10-13

    申请号：US15469715

    申请日：2017-03-27

    Applicant: United Technologies Corporation

    Inventor： Dominic J. Mongillo ,  Scott D. Lewis ,  Jeffrey T. Morton

    IPC: F01D5/18 ,  F01D5/14 ,  F01D5/20

    Abstract: A blade for a gas turbine engine includes an airfoil which includes pressure and suction side surfaces joined at leading and trailing edges to provide an exterior airfoil surface. The airfoil extends from a 0% span position to a 100% span position at a tip. A mean chamber line is provided at the tip and extends from the leading edge to the trailing edge. The mean chamber line has a leading edge tangent line at the leading edge at the tip and a trailing edge tangent line at the trailing edge at the tip. The leading edge tangent line and the trailing edge tangent line intersect to provide a total camber angle in a range of −35° to 35°. The pressure side includes a tip shelf.

    Woven skin cores for turbine airfoils
    2.
    发明授权
    Woven skin cores for turbine airfoils 有权

    公开(公告)号：US10731477B2

    公开(公告)日：2020-08-04

    申请号：US15700990

    申请日：2017-09-11

    Applicant: United Technologies Corporation

    Inventor： San Quach ,  Jeffrey T. Morton

    IPC: F01D5/18

    Abstract: An airfoil includes an airfoil body having a pressure side and a suction side that each radially extend between a first radial boundary end and a second radial boundary end and each axially extend between a leading edge and a trailing edge. The airfoil body defines a plurality of first skin core passages disposed proximate the suction side and radially extend from the first radial boundary end towards the second radial boundary end, and a plurality of second skin core passages that radially extend toward the second radial boundary end and circumferentially extend towards the suction side proximate the second radial boundary end.

    TURBINE BLADE WITH TIP VORTEX CONTROL AND TIP SHELF
    3.
    发明申请
    TURBINE BLADE WITH TIP VORTEX CONTROL AND TIP SHELF 审中-公开

    公开(公告)号：US20180274368A1

    公开(公告)日：2018-09-27

    申请号：US15469715

    申请日：2017-03-27

    Applicant: United Technologies Corporation

    Inventor： Dominic J. Mongillo ,  Scott D. Lewis ,  Jeffrey T. Morton

    IPC: F01D5/14 ,  F01D5/18 ,  F01D5/20

    Abstract: A blade for a gas turbine engine includes an airfoil which includes pressure and suction side surfaces joined at leading and trailing edges to provide an exterior airfoil surface. The airfoil extends from a 0% span position to a 100% span position at a tip. A mean chamber line is provided at the tip and extends from the leading edge to the trailing edge. The mean chamber line has a leading edge tangent line at the leading edge at the tip and a trailing edge tangent line at the trailing edge at the tip. The leading edge tangent line and the trailing edge tangent line intersect to provide a total camber angle in a range of −35° to 35°. The pressure side includes a tip shelf.

    IMPINGEMENT COOLING ARRANGEMENT FOR AIRFOILS
    7.
    发明申请
    IMPINGEMENT COOLING ARRANGEMENT FOR AIRFOILS 审中-公开

    公开(公告)号：US20190211689A1

    公开(公告)日：2019-07-11

    申请号：US15866557

    申请日：2018-01-10

    Applicant: United Technologies Corporation

    Inventor： Jason Shenny ,  Jeffrey T. Morton ,  Alberto A. Mateo ,  San Quach ,  Gregory Anselmi

    IPC: F01D5/18 ,  F04D29/32 ,  F04D29/58

    CPC classification number: F01D5/186 ,  F01D5/187 ,  F04D29/324 ,  F04D29/582 ,  F05D2220/32 ,  F05D2240/303 ,  F05D2260/201 ,  F05D2260/202

    Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section that has an internal wall and an external wall. The external wall defines pressure and suction sides that extends in a chordwise direction between a leading edge and a trailing edge, a first impingement cavity and a second impingement cavity bounded by the external wall at a leading edge region that defines the leading edge, a first feeding cavity separated from the first impingement cavity and from the second impingement cavity by the internal wall, and a first crossover passage within the internal wall that connects the first impingement cavity and the first feeding cavity. The first crossover passage defines a first passage axis that intersects a surface of the first impingement cavity. A second crossover passage within the internal wall connects to the second impingement cavity. The second crossover passage defines a second passage axis that intersects a surface of the second impingement cavity.

    Internally cooled engine components
    8.
    发明授权
    Internally cooled engine components 有权

    公开(公告)号：US10344607B2

    公开(公告)日：2019-07-09

    申请号：US15416900

    申请日：2017-01-26

    Applicant: United Technologies Corporation

    Inventor： Jeffrey T. Morton ,  San Quach

    IPC: F01D9/06 ,  F01D5/18

    Abstract: A component of a gas turbine engine is provided. The component may include an external surface with a skin cavity adjacent the external surface. The skin cavity may be defined by a hot-side surface and a cool-side surface with the hot-side surface between the cool-side surface and the external surface. A flat portion may be disposed on the hot-side surface and may, for example, define a wall-thickness check region. A protrusion may be disposed on the cool-side surface opposite the flat portion on the hot-side surface. The hot-side surface and the cool-side surface may tend to increase a heat transfer coefficient along the flat portion of the hot-side surface, which may also define a wall thickness check region.

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