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    AIRFOIL PLATFORM RIM SEAL ASSEMBLY
    12.
    发明公开
    AIRFOIL PLATFORM RIM SEAL ASSEMBLY 审中-公开
    SCHAUFELPLATTFORMKANTENDICHTUNGSANORDNUNG

    公开(公告)号：EP3020929A1

    公开(公告)日：2016-05-18

    申请号：EP15194006.1

    申请日：2015-11-11

    Applicant: United Technologies Corporation

    Inventor： AGGARWALA, Andrew S. ,  BERGMAN, Russell J. ,  BOEKE, Mark A. ,  LANA, Kyle C. ,  SNYDER, Daniel A.

    IPC: F01D11/00 ,  F01D11/02

    CPC classification number: F01D11/006 ,  F01D5/22 ,  F01D11/001 ,  F01D11/02

    Abstract: An airfoil stage of a turbine engine (20) includes an upstream airfoil assembly (62), a downstream airfoil assembly (64) in rotational relationship to the upstream airfoil assembly (62) and a rim seal assembly (118) integrated therebetween. The rim seal assembly (118) may include a sloped downstream portion (94) of a platform (70) of the upstream airfoil assembly (62), an upstream segment (110) of a platform (76) of the downstream airfoil assembly (64) and a nub (120) that projects radially outward from the upstream segment (110). The downstream portion (94) and the upstream segment (110) are spaced from one-another defining a cooling cavity (114) therebetween for the flow of cooling air. The portion (94) and segment (110) overlap axially such that the nub (120) is axially aligned to the downstream portion (94) to reduce a core airflow (73) into the cooling cavity (114).

    Abstract translation: 涡轮发动机（20）的翼型段包括上游翼型组件（62），与上游翼型组件（62）成旋转关系的下游翼型组件（64）和与它们之间形成的边缘密封组件（118）。 轮缘密封组件（118）可以包括上游翼型组件（62）的平台（70）的倾斜下游部分（94），下游翼型组件（64）的平台（76）的上游段（110） ）和从上游段（110）径向向外突出的突出部（120）。 下游部分（94）和上游段（110）在其间限定冷却空腔（114）之间的间隔开，以使冷却空气流动。 部分（94）和段（110）轴向重叠，使得凸块（120）与下游部分（94）轴向对齐，以将芯气流（73）减少到冷却腔（114）中。

    AIRCRAFT COMPONENT QUALIFICATION SYSTEM AND PROCESS
    14.
    发明公开
    AIRCRAFT COMPONENT QUALIFICATION SYSTEM AND PROCESS 审中-公开

    公开(公告)号：EP3591172A1

    公开(公告)日：2020-01-08

    申请号：EP19183852.3

    申请日：2019-07-02

    Applicant: United Technologies Corporation

    Inventor： SNYDER, Daniel A. ,  YUDICHAK, David J. ,  HEINEMANN, Kurt R. ,  BOWES, Perry ,  SELIN, Evan

    IPC: F01D21/00 ,  F01D25/00 ,  F02C9/00 ,  G01M15/14

    Abstract: A qualification system for gas turbine engine components (174) includes a computer system configured to receive a set of measured parameters for each gas turbine engine component (174) in a plurality of substantially identical gas turbine engine components (174), and determine a variation model based on the set of measured parameters. The computer system includes at least one simulated engine model configured to determine a predicted operation of each gas turbine engine component (174) in the plurality of substantially identical gas turbine engine components (174), a correlation system configured to correlate variations in the set of parameters for each of the gas turbine engine components (174) with a set of the predicted operations of each gas turbine engine (10), thereby generating a predictive model based on the variations. The computer system also includes a qualification module configured to generate a qualification formula based on the predictive model. The qualification formula is configured to receive a set of measured parameters of an as-manufactured gas turbine engine component (174) and determine when the as manufactured gas turbine engine component (174) is qualified for inclusion in at least one engine.

    AIRFOIL SUPPORT AND COOLING SCHEME
    17.
    发明公开
    AIRFOIL SUPPORT AND COOLING SCHEME 审中-公开
    AIRFOIL支持和冷却方案

    公开(公告)号：EP3048255A1

    公开(公告)日：2016-07-27

    申请号：EP16152777.5

    申请日：2016-01-26

    Applicant: United Technologies Corporation

    Inventor： SPANGLER, Brandon W. ,  OTERO, Edwin ,  SNYDER, Daniel A. ,  TARASKEVICH, Jaimie ,  WU, Di ,  SCHWEITZER, Jaimie

    IPC: F01D5/18

    CPC classification number: F01D5/187 ,  F01D5/147 ,  F02C3/04 ,  F02C7/18 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2260/22141 ,  Y02T50/676

    Abstract: In various embodiments, an airfoil (270; 370) used as a turbine blade for a turbine wheel in a gas turbine engine (120) is provided. The airfoil (270; 370) may comprise a root (274), a tip (272), and a body. The root (274) may have a first area. The tip (272) may have a second area. The body may have a chord (278) bounded by the root (274) and the tip (272). The body may also define a cooling chamber (276). The cooling chamber (276) may have a first rib (280) substantially perpendicular to the chord (278). The cooling chamber (276) may also have a second rib (282) extending partially between the root (274) and the tip (272).

    Abstract translation: 在各种实施例中，提供了用作燃气涡轮发动机（120）中的涡轮叶轮的涡轮叶片的翼型件（270; 370）。 翼型件（270; 370）可以包括根部（274），尖端（272）和主体。 根部（274）可以具有第一区域。 尖端（272）可以具有第二区域。 身体可以具有由根部（274）和尖端（272）限定的弦（278）。 主体也可限定冷却室（276）。 冷却室（276）可以具有基本垂直于翼弦（278）的第一肋（280）。 冷却室（276）还可以具有部分地在根部（274）和尖端（272）之间延伸的第二肋（282）。

    BLADE ELEMENT CROSS-TIES
    18.
    发明公开
    BLADE ELEMENT CROSS-TIES 审中-公开
    SCHAUFELELEMENT MIT QUERSTREBE

    公开(公告)号：EP2942484A1

    公开(公告)日：2015-11-11

    申请号：EP15166907.4

    申请日：2015-05-08

    Applicant: United Technologies Corporation

    Inventor： SNYDER, Daniel A. ,  THORNTON, Lane ,  SIMPSON, Alex J.

    IPC: F01D5/16 ,  F01D5/18

    Abstract: The invention concerns a blade element for a gas turbine engine and methods of manufacturing said blade elements.
    In one embodiment, a blade element 100 includes a first inner surface 108 of the blade element, wherein the first inner surface 108 is associated with a first outer blade surface 106 of the blade element, and a second inner surface 109 of the blade element, wherein the second inner surface 109 is associated with a second outer blade surface 107 of the blade element and wherein the second inner surface 109 is opposite from the first inner surface 108. The blade element 100 also includes a cross-tie 130 1 configured to connect the first inner surface 108 to the second inner surface 109, wherein the cross-tie 130 1 is positioned along a trailing edge 110 of the blade element 100 and the cross-tie 130 1 is configured to reduce vibration mode effects of the blade element 100.

    Abstract translation: 本发明涉及一种用于燃气涡轮发动机的叶片元件和制造所述叶片元件的方法。 在一个实施例中，叶片元件100包括叶片元件的第一内表面108，其中第一内表面108与叶片元件的第一外叶片表面106和叶片元件的第二内表面109相关联， 其中第二内表面109与叶片元件的第二外叶片表面107相关联，并且其中第二内表面109与第一内表面108相对。刀片元件100还包括跨接线130 1， 第一内表面108到第二内表面109，其中交叉连接130 1沿着叶片元件100的后缘110定位，并且交叉连接130 1被配置为减小叶片元件100的振动模式效应 。

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