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    DAMPER SEAL INSTALLATION FEATURES
    3.
    发明公开
    DAMPER SEAL INSTALLATION FEATURES 审中-公开
    防潮密封安装特点

    公开(公告)号：EP3181945A1

    公开(公告)日：2017-06-21

    申请号：EP16202769.2

    申请日：2016-12-07

    Applicant: United Technologies Corporation

    Inventor： NIEZELSKI, David A. ,  WINN, Joshua D. ,  BEATTIE, Jeffrey S.

    IPC: F16F15/04 ,  F01D5/26 ,  F01D5/30

    CPC classification number: F01D5/22 ,  F01D5/26 ,  F01D5/30 ,  F01D5/3007 ,  F01D11/006 ,  F05D2240/30 ,  F05D2240/55 ,  F05D2240/57 ,  F05D2260/96 ,  F16F15/04 ,  Y02T50/673

    Abstract: Aspects of the disclosure are directed to a damper (334) configured to be located in a cavity (346) formed between first and second bases (322a,322b) configured to seat respective first and second airfoils, the damper (334) having a first face and a second face, where an aspect ratio between the first face and the second face ensures that the damper (334) is installed in the cavity (346) in accordance with a predetermined orientation.

    Abstract translation: 本公开的多个方面涉及一种阻尼器（334），该阻尼器被配置为位于在第一基部和第二基部（322a，322b）之间形成的空腔（346）中，该第一基部和第二基部构造成使相应的第一翼型件和第二翼型件安置， 正面和第二面，其中第一面和第二面之间的高宽比确保阻尼器（334）根据预定取向安装在空腔（346）中。

    AIRFOIL HAVING DEAD-END TIP FLAG CAVITY AND CORRESPONDING CORE ASSEMBLY
    5.
    发明公开
    AIRFOIL HAVING DEAD-END TIP FLAG CAVITY AND CORRESPONDING CORE ASSEMBLY 审中-公开

    公开(公告)号：EP3693546A1

    公开(公告)日：2020-08-12

    申请号：EP20156368.1

    申请日：2020-02-10

    Applicant: United Technologies Corporation

    Inventor： NIEZELSKI, David A. ,  JENNINGS, Timothy J. ,  TELLER, Bret M. ,  MCBRIEN, John ,  SLAVENS, Thomas N.

    IPC: F01D5/18 ,  F01D5/20

    Abstract: Airfoils for gas turbine engines are described. The airfoils (320) include an airfoil body extending between a platform (348) and a tip (322), the airfoil body having a leading edge (322), a trailing edge (324), a pressure side (326), and a suction side (328), a serpentine cavity formed within the airfoil body and having an up-pass serpentine cavity (340), a down-pass serpentine cavity (342), and a trailing edge cavity (344), and a dead-end tip flag cavity (338) extending in a direction between the leading edge and the trailing edge, the dead-end tip flag cavity arranged between the serpentine cavity and the tip, wherein the dead-end tip flag cavity ends at a dead-end wall (366) located at a position between the leading edge and the trailing edge of the airfoil body. A corresponding core assembly for the formation of the airfoil is also provided.

    GAS TURBINE ENGINE BLADE, CORRESPONDING GAS TURBINE ENGINE AND METHOD FOR A GAS TURBINE ENGINE BLADE
    7.
    发明公开
    GAS TURBINE ENGINE BLADE, CORRESPONDING GAS TURBINE ENGINE AND METHOD FOR A GAS TURBINE ENGINE BLADE 审中-公开
    燃气轮机发动机叶片，相应的燃气涡轮发动机及用于燃气涡轮发动机叶片的方法

    公开(公告)号：EP3296511A2

    公开(公告)日：2018-03-21

    申请号：EP17187494.4

    申请日：2017-08-23

    Applicant: United Technologies Corporation

    Inventor： JENNINGS, Timothy J. ,  NIEZELSKI, David A. ,  AUXIER, James Tilsley

    IPC: F01D5/18

    CPC classification number: F01D5/187 ,  F01D5/186 ,  F01D11/08 ,  F02C3/04 ,  F05D2220/32 ,  F05D2240/307 ,  F05D2260/202 ,  Y02T50/676

    Abstract: A gas turbine engine (20) blade (64) includes a platform (68) that has an inner side (68A) and an outer side (68B), a root (70) that extends outwardly from the inner side (68A), and an airfoil (72) that extends outwardly from a base (72A) at the outer side (68B) to a tip end (72B). The airfoil (72) includes a leading edge and a trailing edge and a first side wall (72C) and a second side wall (72D). The first side wall (72C) and the second side wall (72D) join the leading edge and the trailing edge and at least partially define one or more cavities (74) in the airfoil (72). The airfoil (72) has a span from the base (72A) to the tip end (72B), with the base (72A) being at 0% of the span and the tip end (72B) being at 100% of the span. The first side wall (72C) includes an axial row (76) of cooling holes (78) at 90% or greater of the span.

    Abstract translation: 燃气涡轮发动机（20）叶片（64）包括具有内侧（68A）和外侧（68B），从内侧（68A）向外延伸的根部（70）的平台（68），以及 在外侧（68B）处从基部（72A）向外延伸至尖端（72B）的翼型件（72）。 翼型件（72）包括前缘和后缘以及第一侧壁（72C）和第二侧壁（72D）。 第一侧壁（72C）和第二侧壁（72D）连接前缘和后缘并且至少部分地限定翼型件（72）中的一个或多个空腔（74）。 翼型件72具有从基座72A到尖端72B的跨度，其中基座72A占跨距的0％并且末端72B处于跨距的100％。 第一侧壁（72C）包括在跨度的90％或更大处的轴向排（76）的冷却孔（78）。

    INSTALLATION FAULT TOLERANT DAMPER
    8.
    发明公开
    INSTALLATION FAULT TOLERANT DAMPER 审中-公开
    安装L TER TER TER。

    公开(公告)号：EP3098387A1

    公开(公告)日：2016-11-30

    申请号：EP16171273.2

    申请日：2016-05-25

    Applicant: United Technologies Corporation

    Inventor： WINN, Joshua Daniel ,  NIEZELSKI, David A.

    IPC: F01D5/22 ,  F01D11/00

    CPC classification number: F01D5/28 ,  F01D5/147 ,  F01D5/22 ,  F01D11/006 ,  F05D2300/17

    Abstract: The present disclosure provides systems for preventing improper installation of a damper seal (340). In various embodiments, an airfoil assembly (200) may comprise a platform (212), an airfoil (210; 410) extending from the platform (212), and a platform tab (314). The airfoil (210; 410) may comprise a gaspath face (317) and a non-gaspath face (319). The non-gaspath face (319) may at least partially define a cavity (316). The airfoil (210; 410) may comprise a pressure side and a suction side (318). The platform tab (314) may be located adjacent to the suction side (318) of the airfoil (210; 410). The platform tab (314) may extend from the platform (212) in the opposite direction as the airfoil (210; 410) and may be configured to prevent a damper seal tab (342) from being inserted radially inwards of the platform tab (314).

    Abstract translation: 本公开提供了用于防止阻尼密封件（340）的不正确安装的系统。 在各种实施例中，翼型组件（200）可以包括平台（212），从平台（212）延伸的翼型件（210; 410）和平台接头（314）。 机翼（210; 410）可以包括气路面（317）和非气道面（319）。 非气道面（319）可以至少部分地限定空腔（316）。 翼型件（210; 410）可以包括压力侧和吸力侧（318）。 平台突片（314）可以位于与翼型件（210; 410）的吸力侧（318）相邻的位置。 平台突片（314）可以从平台（212）沿与翼型件（210; 410）相反的方向延伸，并且可以构造成防止阻尼器密封片（342）径向向内插入平台突片（314） ）。

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