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    FULL RING CURVIC SEAL
    12.
    发明申请
    FULL RING CURVIC SEAL 审中-公开
    全环CURVIC密封

    公开(公告)号：US20160010458A1

    公开(公告)日：2016-01-14

    申请号：US14772849

    申请日：2014-03-10

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Scott D. Virkler

    IPC: F01D5/02 ,  F01D11/00 ,  F16D1/02

    CPC classification number: F01D5/026 ,  F01D5/02 ,  F01D11/003 ,  F01D11/005 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2240/60 ,  F05D2260/37 ,  F16D1/02 ,  F16J15/062

    Abstract: A shaft coupling between a first shaft and a second shaft includes a seal assembly to minimize leakage. The seal assembly includes a ring press fit against an inner surface of the first shaft and a clearance fit with an inner surface of the second shaft. A seal is supported between the ring and the inner surface of the second shaft.

    Abstract translation: 第一轴和第二轴之间的联轴器包括密封组件以最小化泄漏。 所述密封组件包括与所述第一轴的内表面相配合的环压配合和与所述第二轴的内表面的间隙配合。 密封件支撑在环和第二轴的内表面之间。

    Split vernier ring for turbine rotor stack assembly
    13.
    发明授权
    Split vernier ring for turbine rotor stack assembly 有权

    公开(公告)号：US11021958B2

    公开(公告)日：2021-06-01

    申请号：US16176894

    申请日：2018-10-31

    Applicant: United Technologies Corporation

    Inventor： Christopher M. Juh ,  Scott D. Virkler

    IPC: F01D5/02 ,  F01D5/06

    Abstract: A power turbine rotor assembly including a rotor shaft. The assembly also includes a rotor stack surrounding the rotor shaft. The assembly further includes a nut axially retaining the rotor stack. The assembly yet further includes a Vernier ring engaged with the nut and the rotor shaft, the Vernier ring having an inner ring, a plurality of inner tabs extending radially inward from the inner ring, and a plurality of outer tabs extending radially outward from the inner ring, the Vernier ring formed of at least two ring segments.

    Turbine blade damper seal
    14.
    发明授权
    Turbine blade damper seal 有权

    公开(公告)号：US10907482B2

    公开(公告)日：2021-02-02

    申请号：US16126482

    申请日：2018-09-10

    Applicant: United Technologies Corporation

    Inventor： Daniel A. Snyder ,  Jaimie Schweitzer ,  Jonathan Perry Sandoval ,  Edwin Otero ,  Kyle C. Lana ,  Scott D. Virkler

    IPC: F01D5/30 ,  F01D5/22 ,  F01D11/00

    Abstract: An example turbine includes a turbine disk and a turbine blade. The turbine disk includes a plurality of lugs and a plurality of slots. Each of the plurality of lugs is located between two of the plurality of slots. Each of the plurality of lugs includes a tab that extends radially outwardly from an end of the lug. The tab has a first section having an upper surface and a second section having an upper surface. The upper surface of the first section is inclined greater than the upper surface of the second section, and the upper surface of the first section of the tab defines a contour. The turbine blade includes a root received in one of the plurality of slots and a platform, and the platform has a lower surface defining a contour. When the turbine blade is received in one of the plurality of slots, the lower surface of the platform is located above a portion of the upper surface of the first section of the tab, and the contour of the upper surface of the first section of the tab matches the contour of the lower surface of the platform.

    DOUBLE SNAPPED COVER PLATE FOR ROTOR DISK
    18.
    发明申请
    DOUBLE SNAPPED COVER PLATE FOR ROTOR DISK 审中-公开
    用于转盘的双重安装盖板

    公开(公告)号：US20150369061A1

    公开(公告)日：2015-12-24

    申请号：US14764021

    申请日：2013-01-30

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Jonathan Perry Sandoval ,  Raymond S. Hummel ,  Scott D. Virkler

    IPC: F01D5/30 ,  F02C3/04

    CPC classification number: F01D5/3015 ,  F01D5/082 ,  F01D11/001 ,  F02C3/04 ,  F02C7/28 ,  F04D29/321 ,  F05D2260/30 ,  F05D2260/36 ,  Y02T50/676

    Abstract: According to an exemplary embodiment of this disclosure, among other possible things a gas turbine engine includes a compressor section, a combustor in fluid communication with the compressor section, a turbine section in fluid communication with the combustor section, a plurality of turbine disks in at least one of the compressor section and the turbine sections, at least one cover plate corresponding to at least one of the turbine disks, each of the cover plates includes, at least two snaps connected via a webbing portion, and a bore region radially inward of the at least two snaps and connected to at least one of the at least two snaps via the webbing portion.

    Abstract translation: 根据本公开的示例性实施例，除了其它可能的情况之外，燃气涡轮发动机包括压缩机部分，与压缩机部分流体连通的燃烧器，与燃烧器部分流体连通的涡轮机部分，处于 压缩机部分和涡轮机部分中的至少一个，至少一个与至少一个涡轮盘对应的盖板，每个盖板包括经由织带部分连接的至少两个卡扣和径向向内 所述至少两个卡扣并且经由所述织带部分连接到所述至少两个卡扣中的至少一个卡扣。

    HYDROSTATIC SEAL WITH ASYMMETRIC BEAMS FOR ANTI-TIPPING
    19.
    发明申请
    HYDROSTATIC SEAL WITH ASYMMETRIC BEAMS FOR ANTI-TIPPING 审中-公开

    公开(公告)号：US20200165930A1

    公开(公告)日：2020-05-28

    申请号：US16202868

    申请日：2018-11-28

    Applicant: United Technologies Corporation

    Inventor： Michael G. McCaffrey ,  Scott D. Virkler

    IPC: F01D11/02 ,  F01D11/16 ,  F01D11/00

    Abstract: A hydrostatic advanced low leakage seal configured to be disposed between relatively rotatable components. The seal includes a base. The seal also includes a shoe extending circumferentially. The seal further includes a first beam operatively coupling the shoe to the base, the first beam having a first thickness. The seal yet further includes a second beam operatively coupling the shoe to the base, the second beam having at least a portion thereof with a second thickness that is less than the first thickness.

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