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    Baffle with impingement holes
    11.
    发明授权
    Baffle with impingement holes 有权

    公开(公告)号：US11415002B2

    公开(公告)日：2022-08-16

    申请号：US16657135

    申请日：2019-10-18

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Adam P. Generale ,  Lucas Dvorozniak ,  San Quach

    IPC: F01D5/18 ,  F01D25/12

    Abstract: An airfoil includes an vane airfoil, which has a ceramic matrix composite airfoil section including an outer wall that defines an internal cavity. The vane airfoil has an associated temperature profile which defines at least one high temperature area and at least one low temperature area. The vane airfoil includes a first zone which is defined in a first radial extent and corresponds to the high temperature area of the temperature profile and a second zone defined in a second radial extent and corresponds to the low temperature area of the temperature profile. An insert is situated in the internal cavity. The insert includes a first zone defined in a first radial extent that is aligned with the first zone of the vane airfoil. The first zone includes a first plurality of cooling holes which are configured to provide a first cooling density. A second zone is defined in a second radial extent that is aligned with the second zone of the vane airfoil. The second zone includes a second plurality of cooling holes that provide a second cooling density that is lower than the first cooling density such that the high temperature area and the low temperature area are balanced to lower a thermal gradient across the first and second zones of the vane airfoil. An vane airfoil and a method of assembling a ceramic matrix composite vane airfoil are also disclosed.

    TRAILING EDGE INSERT FOR AIRFOIL VANE
    12.
    发明申请
    TRAILING EDGE INSERT FOR AIRFOIL VANE 有权

    公开(公告)号：US20210140322A1

    公开(公告)日：2021-05-13

    申请号：US16679229

    申请日：2019-11-10

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Adam P. Generale ,  Dominic J. Mongillo

    IPC: F01D5/18 ,  F01D25/12

    Abstract: An example airfoil vane according to the present disclosure includes an airfoil section including an outer wall that defines an internal cavity, and an insert situated in the internal cavity. A space is defined between the insert and the airfoil outer wall, the insert including an insert wall. A plurality of standoff features extend from the insert wall into the space and contact the airfoil outer wall at a contact area, whereby the standoff features are configured to block airflow in the space at the contact area and redirect the airflow to gaps between the standoff features. A gas turbine engine with the example airfoil vane and a method of assembling an airfoil vane are also disclosed.

    AIRFOIL WITH METALLIC SHIELD
    13.
    发明申请
    AIRFOIL WITH METALLIC SHIELD 有权

    公开(公告)号：US20210071534A1

    公开(公告)日：2021-03-11

    申请号：US16562557

    申请日：2019-09-06

    Applicant: United Technologies Corporation

    Inventor： Adam P. Generale ,  Howard J. Liles

    IPC: F01D5/14

    Abstract: A gas turbine engine airfoil includes an airfoil section that has an airfoil wall and a rib that are formed of a ceramic matrix composite. The airfoil wall circumscribes an internal cavity for receiving cooling air. The airfoil wall defines leading and trailing ends and first and second sides that join the leading and trailing ends. The rib connects the first and second sides. A metallic shield is disposed in the internal cavity and at least partially encloses the rib to shield the rib from the cooling air.

    Vane platform leading edge recessed pocket with cover
    14.
    发明授权
    Vane platform leading edge recessed pocket with cover 有权

    公开(公告)号：US10822962B2

    公开(公告)日：2020-11-03

    申请号：US16144677

    申请日：2018-09-27

    Applicant: United Technologies Corporation

    Inventor： Ky H. Vu ,  Adam P. Generale

    IPC: F01D5/18 ,  F01D5/30 ,  F01D9/04 ,  F01D9/06

    Abstract: A platform for an airfoil of a gas turbine engine having an axis extending from a front of the gas turbine engine to a rear of the gas turbine engine. The platform includes a leading edge configured to face towards the front of the gas turbine engine. The platform further includes a trailing edge opposite the leading edge. The platform further includes a radially outer surface that defines a pocket for receiving a cooling airflow. The platform further includes a cover coupled to the radially outer surface to at least partially enclose the pocket and defining a plurality of air inlet holes configured to port at least a portion of the cooling airflow into the pocket.

    VANE PLATFORM LEADING EDGE RECESSED POCKET WITH COVER
    17.
    发明申请
    VANE PLATFORM LEADING EDGE RECESSED POCKET WITH COVER 审中-公开

    公开(公告)号：US20200102838A1

    公开(公告)日：2020-04-02

    申请号：US16144677

    申请日：2018-09-27

    Applicant: United Technologies Corporation

    Inventor： KY H. VU ,  Adam P. Generale

    IPC: F01D5/18 ,  F01D9/04 ,  F01D5/30

    Abstract: A platform for an airfoil of a gas turbine engine having an axis extending from a front of the gas turbine engine to a rear of the gas turbine engine. The platform includes a leading edge configured to face towards the front of the gas turbine engine. The platform further includes a trailing edge opposite the leading edge. The platform further includes a radially outer surface that defines a pocket for receiving a cooling airflow. The platform further includes a cover coupled to the radially outer surface to at least partially enclose the pocket and defining a plurality of air inlet holes configured to port at least a portion of the cooling airflow into the pocket.

    VANE AIR INLET WITH FILLET
    18.
    发明申请
    VANE AIR INLET WITH FILLET 审中-公开

    公开(公告)号：US20190178091A1

    公开(公告)日：2019-06-13

    申请号：US15837784

    申请日：2017-12-11

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Ky H. Vu ,  Adam P. Generale ,  Brandon L. Howard

    IPC: F01D5/18 ,  F01D9/04

    Abstract: A vane for a gas turbine engine may comprise a vane platform and an airfoil extending radially from the vane platform. The airfoil may comprise an inlet defined, at least partially, by an internal surface of the airfoil. The internal surface may comprise a convex curve proximate the inlet. A transition between an external surface of the airfoil and a surface of the vane platform may comprise a concave curve. A radius of curvature of the convex curve of the internal surface may be concentric to a radius of curvature of the concave curve of the transition.

    Components for gas turbine engines
    20.
    发明授权
    Components for gas turbine engines 有权

    公开(公告)号：US11371360B2

    公开(公告)日：2022-06-28

    申请号：US16432214

    申请日：2019-06-05

    Applicant: United Technologies Corporation

    Inventor： Adam P. Generale ,  Dominic J. Mongillo

    IPC: F01D5/18

    Abstract: Component for gas turbine engines are described. The components include an airfoil body having leading and trailing edges and pressure and suction sides. The airfoil has a leading edge cavity located proximate the leading edge defined between the leading edge and a separator rib and between the pressure side and the suction side. An insert member is installed within the leading edge cavity. The insert member has one or more metering flow apertures at an aft end and one or more impingement apertures at a forward end and at least one axially extending rib along an exterior surface thereof. At least one axial extending flow channel passage is defined along the axial extending rib between an exterior of the insert member and an interior of the airfoil body. Air flow through the metering flow apertures flows into the axial extending flow channel passage and flows forward toward the leading edge.

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