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    QUAD-TAB U-WASHER
    13.
    发明公开
    QUAD-TAB U-WASHER 审中-公开
    U-SCHEIBE MIT VIER LASCHEN

    公开(公告)号：EP3088677A1

    公开(公告)日：2016-11-02

    申请号：EP16163970.3

    申请日：2016-04-06

    Applicant: United Technologies Corporation

    Inventor： MAX, Seth A. ,  PORTER, Steven D.

    IPC: F01D9/06 ,  F01D25/16 ,  F16B43/00 ,  F16B39/00

    CPC classification number: F01D25/243 ,  F01D9/00 ,  F01D9/02 ,  F01D25/00 ,  F01D25/125 ,  F01D25/162 ,  F01D25/246 ,  F05D2220/32 ,  F05D2250/75 ,  F05D2260/31 ,  F16B39/101 ,  F16B39/108 ,  F16B39/24 ,  F16B43/00

    Abstract: A washer 46 includes a first lobe 78 comprising a first hole 96, a second lobe 80 comprising a second hole 100, a third lobe 82 comprising a third hole 104, and a fourth lobe 84 comprising a fourth hole 108. A first leg 86 extends from the first lobe 78 to the second lobe 80, and a second leg 88 extends between the third lobe 82 and the fourth lobe 84, wherein the second leg 88 is parallel to the first leg 86. A third leg 90 extends from the first lobe 78 to the third lobe 82 and spaces the first leg 86 from the second leg 88 such that the second lobe 80 is disposed opposite the fourth lobe 84.

    Abstract translation: 垫圈46包括包括第一孔96的第一凸角78，包括第二孔100的第二凸角80，包括第三孔104的第三凸起82和包括第四孔108的第四凸起84.第一支腿86延伸 从第一凸角78到第二凸角80，并且第二腿部88在第三凸起部分82和第四凸起部分84之间延伸，其中第二腿部88平行于第一腿部86.第三腿部90从第一凸起部延伸 78到第三凸角82，并且将第一腿部86与第二腿部88隔开，使得第二凸角80与第四凸起部84相对设置。

    GAS TURBINE ENGINE VANE RING ARRANGEMENT
    15.
    发明公开
    GAS TURBINE ENGINE VANE RING ARRANGEMENT 审中-公开
    SCHAUFELRINGANORDNUNG EINES GASTURBINENMOTORS

    公开(公告)号：EP3027855A2

    公开(公告)日：2016-06-08

    申请号：EP14832509.5

    申请日：2014-06-19

    Applicant: United Technologies Corporation

    Inventor： OLS, John T. ,  PORTER, Steven D.

    IPC: F01D9/04 ,  F01D11/00

    Abstract: A vane pack for a gas turbine engine includes an annular arrangement of vanes. A ring is secured around the vanes and extends proud of an axial end of the vanes.

    Abstract translation: 用于燃气涡轮发动机的叶片组包括叶片的环形排列。 一个环被固定在叶片周围并且延伸到叶片的轴向端部。

    AERODYNAMIC COMPONENT FOR A GAS TURBINE ENGINE
    16.
    发明公开
    AERODYNAMIC COMPONENT FOR A GAS TURBINE ENGINE 审中-公开

    公开(公告)号：EP3712392A1

    公开(公告)日：2020-09-23

    申请号：EP20163663.6

    申请日：2020-03-17

    Applicant: United Technologies Corporation

    Inventor： PORTER, Steven D. ,  SOBANSKI, Jon E.

    IPC: F01D25/14 ,  F23R3/00

    Abstract: An aerodynamic component (501, 801) of a gas turbine engine (20) is provided and is fittable to a shell (510, 810) having a shell shape (512, 812). The aerodynamic component includes a body (520, 820) having a component shape (522, 822) initially deviating from the shell shape prior to an assembly operation in which the aerodynamic component is to be fit to the shell. Deviation of the component shape from the shell shape aids in an establishment of a final desired shape (530, 830) of the aerodynamic component following the assembly operation.

    ELECTROSTATIC FLAME CONTROL TECHNOLOGY
    19.
    发明公开
    ELECTROSTATIC FLAME CONTROL TECHNOLOGY 审中-公开

    公开(公告)号：EP3587921A2

    公开(公告)日：2020-01-01

    申请号：EP19183017.3

    申请日：2019-06-27

    Applicant: United Technologies Corporation

    Inventor： PORTER, Steven D. ,  SOBANSKI, Jon E.

    IPC: F23D11/32 ,  F02C7/22 ,  F23C99/00 ,  F23R3/28

    Abstract: A method (600) of controlling fuel injection into a combustor (56) of a gas turbine engine (20) including: applying a first electrical charge (212) to fuel (72) such that the fuel becomes a charged fuel (720); and applying a second electrical charge (214) to a component (250) of the combustor, wherein the first electrical charge is applied to the fuel at a first frequency and the second electrical charge is applied to the component at a second frequency such that at least one of a selected tone, a selected screech, and a selected noise is produced by spraying the charged fuel through the component and into a combustion chamber (54) of the combustor from a fuel nozzle (78).

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