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    GAS TURBINE ENGINE COOLING HOLE WITH CIRCULAR EXIT GEOMETRY
    1.
    发明申请
    GAS TURBINE ENGINE COOLING HOLE WITH CIRCULAR EXIT GEOMETRY 审中-公开

    公开(公告)号：WO2014109801A3

    公开(公告)日：2014-07-17

    申请号：PCT/US2013/061101

    申请日：2013-09-22

    Applicant: UNITED TECHNOLOGIES CORPORATION ,  MCBRIEN, John ,  SPANGLER, Brandon, W. ,  DEVORE, Matthew, A.

    Inventor： MCBRIEN, John ,  SPANGLER, Brandon, W. ,  DEVORE, Matthew, A.

    IPC: F01D5/18 ,  F01D25/12 ,  F02C7/18 ,  F04D29/58

    Abstract: A gas turbine engine component includes a structure having an exterior surface. A cooling hole extends from a cooling passage to the exterior surface to provide an exit area on the exterior surface that is substantially circular in shape. A gas turbine engine includes a compressor section and a turbine section. A combustor is provided between the compressor and turbine sections. A component in at least one of the compressor and turbine sections has an exterior surface. A film cooling hole extends from a cooling passage to the exterior surface to provide an exit area that is substantially circular in shape. A method of machining a film cooling hole includes providing a component having an internal cooling passage and an exterior surface, machining a film cooling hole from the exterior surface to the internal cooling passage to provide a substantially circular exit area on the exterior surface.

    AIRFOIL HAVING DEAD-END TIP FLAG CAVITY AND CORRESPONDING CORE ASSEMBLY
    6.
    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.

    REGENERATING AN ADDITIVELY MANUFACTURED COMPONENT TO CURE DEFECTS AND ALTER MICROSTRUCTURE
    9.
    发明公开
    REGENERATING AN ADDITIVELY MANUFACTURED COMPONENT TO CURE DEFECTS AND ALTER MICROSTRUCTURE 审中-公开
    制造的附加部件再生改正缺陷及修订组织结构

    公开(公告)号：EP2986760A2

    公开(公告)日：2016-02-24

    申请号：EP14813859.7

    申请日：2014-04-17

    Applicant: United Technologies Corporation

    Inventor： MCBRIEN, John ,  CASTLE, Lea, Kennard ,  SPANGLER, Brandon, W. ,  XU, JinQuan

    IPC: C30B15/02 ,  C30B15/00

    Abstract: A method of forming a metal single crystal turbine component (10) with internal passageways includes forming a polycrystalline turbine blade with internal passageways by additive manufacturing and filling the passageways with a core ceramic slurry. The ceramic slurry is then treated to harden the core (20) and the turbine component is encased in a ceramic shell which is treated to form a ceramic mold. The turbine component in the mold is then melted and directionally solidified in the form of a single crystal. The outer shell and inner ceramic core are then removed to form a finished single crystal turbine component with internal passageways.

    Abstract translation: 形成具有内部通道的金属单晶涡轮机部件（10）的方法包括通过加成制造形成具有内部通道的多晶涡轮叶片和与核心陶瓷浆料填充所述通道。 然后将陶瓷浆液进行处理以硬化该处理，以形成一个陶瓷铸型的芯（20）和所述涡轮机部件是在陶瓷壳包裹全部。 然后在模具中的涡轮机部件被熔化并在一个单一的晶体形式定向凝固。 外壳体和内陶瓷芯然后被去除，以形成具有内部通道成品单晶涡轮机部件。

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