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    AIRFOIL HAVING FORWARD FLOWING SERPENTINE FLOW
    21.
    发明申请
    AIRFOIL HAVING FORWARD FLOWING SERPENTINE FLOW 审中-公开

    公开(公告)号：US20190048728A1

    公开(公告)日：2019-02-14

    申请号：US15671328

    申请日：2017-08-08

    Applicant: United Technologies Corporation

    Inventor： Carey Clum ,  Dominic J. Mongillo, JR.

    IPC: F01D5/18 ,  F01D5/14

    Abstract: Airfoils including an airfoil body having leading and trailing edges and root and tip regions, wherein an aftward direction is from the leading edge toward the trailing edge and a radially outward direction is from root to tip, a forward-flowing serpentine flow path formed within the airfoil body defined by a first serpentine cavity, a second serpentine cavity, and a third serpentine cavity, wherein the first serpentine cavity is aftward of the second serpentine cavity, and the second serpentine cavity is aftward of the third serpentine cavity, a tip flag cavity extending aftward from proximate the leading edge to the trailing edge along the tip region, and at least one shielding cavity located between a portion of the forward-flowing serpentine flow path and an external surface of the airfoil body.

    SEAL ARRANGEMENT FOR TURBINE ENGINE COMPONENT
    22.
    发明申请
    SEAL ARRANGEMENT FOR TURBINE ENGINE COMPONENT 审中-公开
    涡轮发动机部件的密封安装

    公开(公告)号：US20160326898A1

    公开(公告)日：2016-11-10

    申请号：US14704278

    申请日：2015-05-05

    Applicant: United Technologies Corporation

    Inventor： Dominic J. Mongillo, JR. ,  Brandon W. Spangler ,  Lane Thornton

    IPC: F01D11/00

    CPC classification number: F01D11/006 ,  F01D11/005 ,  F01D25/246 ,  F05D2240/11 ,  F05D2240/57 ,  F05D2250/182 ,  Y02T50/672

    Abstract: A component for a gas turbine engine according to an example of the present disclosure includes, among other things, a body including a cold side surface adjacent to a mate face. A plurality of ridges extends from the cold side surface. A seal member abuts the plurality of ridges to define a plurality of cooling passages. The seal member is configured to move between a first position and a second position relative to the plurality of ridges. Each of the plurality of cooling passages includes a first inlet defined at the first position and a second, different inlet defined at the second position. A method of sealing between adjacent components of a gas turbine engine is also disclosed.

    Abstract translation: 根据本公开的示例的用于燃气涡轮发动机的部件包括包括邻近配合面的冷侧表面的主体。 多个脊从冷侧表面延伸。 密封构件邻接多个脊以限定多个冷却通道。 密封构件被构造成相对于多个脊在第一位置和第二位置之间移动。 多个冷却通道中的每一个包括限定在第一位置处的第一入口和限定在第二位置处的第二不同入口。 还公开了一种在燃气涡轮发动机的相邻部件之间的密封方法。

    SELF-COOLED ORIFICE STRUCTURE
    25.
    发明申请
    SELF-COOLED ORIFICE STRUCTURE 有权
    自冷式结构

    公开(公告)号：US20160025006A1

    公开(公告)日：2016-01-28

    申请号：US14807602

    申请日：2015-07-23

    Applicant: United Technologies Corporation

    Inventor： Tracy A. Propheter-Hinckley ,  Dominic J. Mongillo, JR. ,  Mark F. Zelesky

    IPC: F02C7/08

    CPC classification number: F02C7/08 ,  F02C7/18 ,  F02C7/264 ,  F23R3/002 ,  F23R3/06 ,  F23R2900/03045 ,  Y02T50/675

    Abstract: A self-cooled orifice structure, that may be for a combustor of a gas turbine engine includes a hot side panel, a cold side panel spaced from the hot side panel, and a continuous first wall extending axially between the hot and cold side panels and spaced radially outward from a centerline. The structure may further include a first plurality of helical vanes projecting laterally, radially, inward from the first wall for flowing cooling air in a spiraling fashion through the cold side panel, then through the hot side panel.

    Abstract translation: 可以用于燃气涡轮发动机的燃烧器的自冷式孔结构包括热侧板，与热侧板间隔开的冷侧板，以及在热侧板和冷侧板之间轴向延伸的连续第一壁，以及 与中心线径向向外间隔开。 该结构还可以包括从第一壁横向，径向向内突出的第一多个螺旋叶片，用于使冷却空气以螺旋方式流过冷侧面板，然后通过热侧面板。

    GAS TURBINE ENGINE COMPONENTS HAVING INTERLACED TRIP STRIP ARRAYS
    29.
    发明申请
    GAS TURBINE ENGINE COMPONENTS HAVING INTERLACED TRIP STRIP ARRAYS 审中-公开

    公开(公告)号：US20200240275A1

    公开(公告)日：2020-07-30

    申请号：US16261745

    申请日：2019-01-30

    Applicant: United Technologies Corporation

    Inventor： Dominic J. Mongillo, JR.

    IPC: F01D5/18 ,  F01D11/08

    Abstract: Components for gas turbine engines are described. The components include a component body defining an internal cavity and an interlaced trip strip array arranged within the internal cavity. The interlaced trip strip array includes a chevron trip strip having an apex, a first ligament extending from the apex in a first direction, and second ligament extending from the apex in a second direction that is different from the first direction to form a chevron shape and a skew trip strip arranged proximate to the chevron trip strip, wherein the skew trip strip has a leading end and a trailing end. The skew trip strip of the array is positioned adjacent to and not contacting the chevron trip strip such that a gap is formed between one of the first ligament and the second ligament and the skew trip strip.

    SEAL ASSEMBLY WITH SHIELD FOR GAS TURBINE ENGINES
    30.
    发明申请
    SEAL ASSEMBLY WITH SHIELD FOR GAS TURBINE ENGINES 审中-公开

    公开(公告)号：US20190323373A1

    公开(公告)日：2019-10-24

    申请号：US15957053

    申请日：2018-04-19

    Applicant: United Technologies Corporation

    Inventor： Winston Gregory Smiddy ,  Paul M. Lutjen ,  Dominic J. Mongillo, JR.

    IPC: F01D11/08 ,  F01D9/06 ,  F01D11/00 ,  F01D9/02

    Abstract: A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a seal having an elongated seal body extending between a seal face that faces toward a gas path and a backside face opposite the seal face, and the seal face extending circumferentially between first and second mate faces. The seal body defines an internal cavity that extends circumferentially from a first opening along the first mate face to a second opening along the second mate face, and the backside face extends between the first and second openings. A shield includes a shield body that spans between the first and second openings such that the backside face is situated between the internal cavity and the shield body.

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