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    STATIONARY AIRFOILS CONFIGURED TO FORM IMPROVED SLIP JOINTS IN BI-CAST TURBINE ENGINE COMPONENTS AND THE TURBINE ENGINE COMPONENTS INCLUDING THE SAME
    2.
    发明申请
    STATIONARY AIRFOILS CONFIGURED TO FORM IMPROVED SLIP JOINTS IN BI-CAST TURBINE ENGINE COMPONENTS AND THE TURBINE ENGINE COMPONENTS INCLUDING THE SAME 有权
    配置用于形成改进的双缸涡轮发动机部件中的滑动接头和包括其的涡轮发动机部件的固定式空气

    公开(公告)号：US20150159495A1

    公开(公告)日：2015-06-11

    申请号：US14099218

    申请日：2013-12-06

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Harry Lester Kington ,  Shezan Kanjiyani ,  Natalie Wali ,  John Gintert ,  Bradley R. Tucker

    IPC: F01D9/04

    CPC classification number: F01D9/042 ,  B22C9/04 ,  B22C9/22 ,  F01D9/041 ,  F01D25/26 ,  F05D2230/21 ,  F05D2300/50212

    Abstract: Stationary airfoils configured to form an improved slip joint in bi-cast turbine engine components and the turbine engine components including the same are provided. The stationary airfoil for a bi-cast turbine engine component comprises a leading edge and a trailing edge interconnected by a pressure sidewall and a suction sidewall. An end portion is shaped with a pair of opposing flanges to form a slip joint with a shroud ring in the bi-cast turbine engine component and to define an interlocking feature. The slip joint permits radial movement of the stationary airfoil relative to the shroud ring due to thermal differential expansion and contraction.

    Abstract translation: 提供了构造成在双流型涡轮发动机部件中形成改进的滑动关节的固定翼型件以及包括其的涡轮发动机部件。 用于双流型涡轮发动机部件的固定翼片包括通过压力侧壁和吸力侧壁互连的前缘和后缘。 端部形成有一对相对的凸缘，以在双流型涡轮发动机部件中形成具有护罩环的滑动接头并且限定互锁特征。 滑动接头允许固定翼型件相对于护罩环由于热差膨胀和收缩而径向移动。

    Gas turbine engine dual-wall hot section structure
    4.
    发明授权
    Gas turbine engine dual-wall hot section structure 有权

    公开(公告)号：US10775044B2

    公开(公告)日：2020-09-15

    申请号：US16172383

    申请日：2018-10-26

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Rodolphe Dudebout ,  Atul Verma ,  Sunil James ,  Hamdullah Ozogul ,  John Gintert

    IPC: F23R3/00

    Abstract: A hot section part of a turbine engine configured to be exposed to hot gases includes a first wall, a second wall, a plurality of pedestals, a plurality of impingement cooling holes, and a plurality of effusion cooling passages. The walls are spaced apart to form an intervening cavity, and each pedestal extends through the intervening cavity. The impingement cooling holes extend through the second wall to admit a flow of cooling air into the intervening cavity. Each effusion cooling passage is associated with a different one of the plurality of pedestals and is disposed at a predetermined angle relative to its associated principal axis. A portion of the flow of cooling air admitted to the intervening cavity is directed through at least a portion of each of the plurality of pedestals and onto the first wall inner surface.

    GAS TURBINE ENGINE DUAL-WALL HOT SECTION STRUCTURE
    5.
    发明申请
    GAS TURBINE ENGINE DUAL-WALL HOT SECTION STRUCTURE 审中-公开

    公开(公告)号：US20200132304A1

    公开(公告)日：2020-04-30

    申请号：US16172383

    申请日：2018-10-26

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Rodolphe Dudebout ,  Atul Verma ,  Sunil James ,  Hamdullah Ozogul ,  John Gintert

    IPC: F23R3/00 ,  F02C7/18

    Abstract: A hot section part of a turbine engine configured to be exposed to hot gases includes a first wall, a second wall, a plurality of pedestals, a plurality of impingement cooling holes, and a plurality of effusion cooling passages. The walls are spaced apart to form an intervening cavity, and each pedestal extends through the intervening cavity. The impingement cooling holes extend through the second wall to admit a flow of cooling air into the intervening cavity. Each effusion cooling passage is associated with a different one of the plurality of pedestals and is disposed at a predetermined angle relative to its associated principal axis. A portion of the flow of cooling air admitted to the intervening cavity is directed through at least a portion of each of the plurality of pedestals and onto the first wall inner surface.

    TURBINE SECTIONS OF GAS TURBINE ENGINES WITH DUAL USE OF COOLING AIR
    6.
    发明申请
    TURBINE SECTIONS OF GAS TURBINE ENGINES WITH DUAL USE OF COOLING AIR 有权
    具有双重冷却空气使用的涡轮发动机涡轮段

    公开(公告)号：US20150275763A1

    公开(公告)日：2015-10-01

    申请号：US14227924

    申请日：2014-03-27

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Shezan Kanjiyani ,  John Gintert ,  Rajiv Rana ,  Lorenzo Crosatti ,  Bradley Reed Tucker ,  Ed Zurmehly

    IPC: F02C7/18 ,  F02C3/10

    CPC classification number: F02C7/18 ,  F01D5/187 ,  F01D11/08 ,  F01D25/12 ,  F01D25/14 ,  F02C3/10 ,  F05D2240/81 ,  F05D2260/201 ,  F05D2260/205 ,  Y02T50/673 ,  Y02T50/676

    Abstract: A turbine section includes a stator assembly having an inner diameter end wall, an outer diameter end wall, and a stator vane; a turbine rotor assembly including a rotor blade extending into the mainstream gas flow path; a housing including an annular shroud that circumscribes the rotor blade and at least partially defines the mainstream hot gas flow path; a first baffle arranged to define a first cavity with the outer diameter end wall of the stator assembly; a second baffle; and a third baffle arranged to define a second cavity with the second baffle and a third cavity with the shroud. The first cavity is fluidly coupled to the second cavity and the second cavity is fluidly coupled to the third cavity such that cooling air flows from the first cavity to the second cavity and from the second cavity to the third cavity.

    Abstract translation: 涡轮部分包括具有内径端壁，外径端壁和定子叶片的定子组件; 涡轮转子组件，其包括延伸到主流气流路径中的转子叶片; 壳体，其包括环绕所述转子叶片并且至少部分地限定所述主流热气体流动路径的环形护罩; 第一挡板，布置成限定具有定子组件的外径端壁的第一腔; 第二挡板 以及第三挡板，其布置成限定具有第二挡板的第二空腔和具有护罩的第三空腔。 第一腔体流体地联接到第二腔体，而第二腔室流体耦合到第三空腔，使得冷却空气从第一空腔流到第二空腔，并从第二腔体流到第三空腔。

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