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    SELF-COOLED ORIFICE STRUCTURE
    82.
    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。

    SELF-COOLED ORIFICE STRUCTURE
    83.
    发明申请
    SELF-COOLED ORIFICE STRUCTURE 有权
    自冷式结构

    公开(公告)号：US20160003477A1

    公开(公告)日：2016-01-07

    申请号：US14790970

    申请日：2015-07-02

    Applicant: United Technologies Corporation

    Inventor： Tracy A. Propheter-Hinckley ,  Dominic J. Mongillo ,  Joel H. Wagner ,  Mark F. Zelesky ,  Stanislav Kostka ,  Timothy S. Snyder

    IPC: F23R3/06 ,  F23R3/00

    CPC classification number: F23R3/06 ,  F23R3/002 ,  F23R3/005 ,  F23R2900/00019 ,  F23R2900/03042 ,  F23R2900/03044 ,  Y02T50/675

    Abstract: A self-cooled orifice structure that may be for a combustor of a gas turbine engine, and may further be a dilution hole structure, includes a hot side panel, a cold side panel spaced from the hot side panel, and a continuous inner wall extending between the hot and cold side panels and defining an orifice having a centerline and communicating axially through the hot and cold side panels. A plurality of end walls of the structure are in a cooling cavity that is defined in-part by the hot and cold side panels and the inner wall. Each end wall extends between and are engaged to the hot and cold side panels and are circumferentially spaced from the next adjacent end wall. A plurality of inlet apertures extend through the cold side panel and are in fluid communication with the cavity, and each one of the plurality of inlet apertures are proximate to a first side of a respective one of the plurality of end walls. A plurality of outlet apertures extend through the hot side panel and are in fluid communication with the cavity, and each one of the plurality of outlet apertures are associated with an opposite second side of a respective one of the plurality of end walls.

    Abstract translation: 可以用于燃气涡轮发动机的燃烧器的自冷却孔结构，并且还可以是稀释孔结构，包括热侧板，与热侧板间隔开的冷侧板，以及连续的内壁，其延伸 在热和冷侧板之间并且限定具有中心线并且轴向地通过热和冷侧板的孔口。 该结构的多个端壁位于由冷热侧板和内壁部分限定的冷却腔中。 每个端壁在热侧面板和冷侧面板之间延伸并与之接合，并与下一个相邻的端壁沿圆周间隔开。 多个入口孔延伸穿过冷侧面板并且与空腔流体连通，并且多个入口孔中的每一个靠近多个端壁中的相应一个的第一侧。 多个出口孔延伸穿过热侧面板并且与空腔流体连通，并且多个出口孔中的每一个与多个端壁中的相应一个端壁的相对的第二侧相关联。

    Airfoil with baffle having flange ring affixed to platform
    84.
    发明授权
    Airfoil with baffle having flange ring affixed to platform 有权

    公开(公告)号：US11702941B2

    公开(公告)日：2023-07-18

    申请号：US16532638

    申请日：2019-08-06

    Applicant: United Technologies Corporation

    Inventor： Scott A. Kovach ,  Tracy A. Propheter-Hinckley

    IPC: F01D5/18 ,  F01D9/06

    CPC classification number: F01D5/189 ,  F01D9/065 ,  F05D2220/32 ,  F05D2240/301 ,  F05D2260/201

    Abstract: An airfoil includes an airfoil section that has an airfoil wall that defines leading and trailing ends and first and second sides that join the leading and trailing ends. The first and second sides span in a longitudinal direction between first and second ends. The airfoil wall circumscribes an internal core cavity. A platform is attached with the first end of the airfoil wall. The platform includes an opening that opens into the internal core cavity and a land region that circumscribes the opening. A baffle is formed of a tube and an attachment portion. The tube extends in the internal core cavity and the attachment portion has a flange ring that is affixed to the platform at the land region.

    Airfoil with cooling passage network having arced leading edge
    85.
    发明授权
    Airfoil with cooling passage network having arced leading edge 有权

    公开(公告)号：US11377964B2

    公开(公告)日：2022-07-05

    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.

    Minicore cooling passage network having trip strips
    86.
    发明授权
    Minicore cooling passage network having trip strips 有权

    公开(公告)号：US11339718B2

    公开(公告)日：2022-05-24

    申请号：US16594146

    申请日：2019-10-07

    Applicant: United Technologies Corporation

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

    IPC: F02C7/00 ,  F02C7/12 ,  F02C3/04

    Abstract: A gas turbine engine article includes an article wall that defines leading and trailing ends and first and second sides that join the leading and trailing ends. The article wall defines a cavity. A cooling passage network is embedded in the article wall between inner and outer portions of the article wall. The cooling passage network has an inlet orifice through the inner portion of the article wall to receive cooling air from the cavity, a plurality of sub-passages that extend axially from the at least one inlet orifice, at least one outlet orifice through the outer portion of the airfoil wall, and trip strips for mixing cooling air in the cooling passage network.

    Chordal seal
    88.
    发明授权
    Chordal seal 有权

    公开(公告)号：US10968777B2

    公开(公告)日：2021-04-06

    申请号：US16393205

    申请日：2019-04-24

    Applicant: United Technologies Corporation

    Inventor： Tracy A. Propheter-Hinckley ,  Kyle J. Brevick

    IPC: F01D25/24 ,  F01D11/00 ,  F01D9/00 ,  F01D9/02 ,  F01D9/04

    Abstract: A vane for a gas turbine engine includes at least one airfoil. A first platform has a first rail located at a first end of the airfoil. A second platform has a second rail located at a second end of the airfoil. A first chordal seal is located on an axially aft surface of the first rail. A second chordal seal is located on an aft surface of the second rail and has a second radius of curvature at least partially truncated by an outer edge of the second rail.

    AIRFOIL HAVING IMPINGEMENT LEADING EDGE
    89.
    发明申请
    AIRFOIL HAVING IMPINGEMENT LEADING EDGE 有权

    公开(公告)号：US20210079793A1

    公开(公告)日：2021-03-18

    申请号：US16552450

    申请日：2019-08-27

    Applicant: United Technologies Corporation

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

    IPC: F01D5/18 ,  F01D5/14

    Abstract: Airfoils for a gas turbine engines and gas turbine engines are described. The airfoils include an airfoil body extending in a radial direction from a first end to a second end, and axially from a leading edge to a trailing edge. A radially extending leading edge channel is formed in the leading edge of the airfoil body, having first and second channel walls that join at a channel base. A first leading edge impingement cavity is located within the airfoil body proximate the leading edge and is defined, in part, by the first channel wall. A leading edge feed cavity is arranged aft of the first leading edge impingement cavity to supply air into the first leading edge impingement cavity. A first leading edge impingement hole is formed in the first channel wall and angled toward a portion of the second channel wall.

    Modulated combustor bypass
    90.
    发明授权
    Modulated combustor bypass 有权

    公开(公告)号：US10830438B2

    公开(公告)日：2020-11-10

    申请号：US15782423

    申请日：2017-10-12

    Applicant: United Technologies Corporation

    Inventor： Anton G. Banks ,  Tracy A. Propheter-Hinckley

    IPC: F02C6/08 ,  F23R3/26 ,  F02C9/18 ,  F23R3/02 ,  F01D17/10 ,  F02C9/22 ,  F01D17/16 ,  F04D27/02 ,  F23R3/04 ,  F23R3/10 ,  F02C7/18

    Abstract: A combustor section of a gas turbine engine includes a combustor having a combustor inlet, and a combustor bypass passage having a passage inlet located upstream of the combustor inlet. The combustor bypass passage is configured to divert a selected bypass airflow around the combustor. A combustor bypass valve is located at the combustor bypass passage to control the selected bypass airflow along the combustor bypass passage. A method of operating a gas turbine engine, includes urging a core airflow from a compressor section toward a combustor section, flowing a first portion of the core airflow into the combustor section via a combustor inlet, and flowing a second portion of the core airflow into a combustor bypass passage via a combustor bypass valve, thereby bypassing the combustor with the second portion of the core airflow.

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