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    Seal damper with improved retention
    22.
    发明授权
    Seal damper with improved retention 有权

    公开(公告)号：US10247023B2

    公开(公告)日：2019-04-02

    申请号：US14429089

    申请日：2013-03-14

    Applicant: United Technologies Corporation

    Inventor： Jeffrey S. Beattie ,  Jeffrey Michael Jacques

    IPC: F01D5/22 ,  F01D5/26 ,  F01D11/00

    Abstract: A seal damper system includes a plurality of circumferentially spaced blades that each include a platform and an airfoil that extends radially outwardly from the platform. A pocket is arranged circumferentially intermediate the blades and radially inwardly of the platform. A seal damper is arranged in the pocket. The seal damper includes a base section that extends along an axial dimension from a first axial end to an opposing second axial end. The base section joins a first arm that extends radially inwardly from the first axial end and a second arm that extends radially inwardly from the second axial end. The first arm includes a free end having a pair of spaced apart shoulders.

    AXIAL TRANSFER TUBE
    23.
    发明申请
    AXIAL TRANSFER TUBE 有权
    轴向转管

    公开(公告)号：US20170002671A1

    公开(公告)日：2017-01-05

    申请号：US14790589

    申请日：2015-07-02

    Applicant: United Technologies Corporation

    Inventor： RYAN ALAN WAITE ,  Jeffrey Michael Jacques ,  Benjamin F. Hagan

    IPC: F01D9/06 ,  F01D25/12 ,  F16L9/00 ,  F01D9/02

    CPC classification number: F01D9/065 ,  F01D9/02 ,  F01D9/06 ,  F01D25/12 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2260/20 ,  F16L9/006 ,  Y02T50/675

    Abstract: What is described is a transfer tube for use with an airfoil of a gas turbine engine coupled to a platform. The transfer tube includes a main body having a first end defining an inlet configured to receive a flow of fluid and a second end defining an outlet for the flow of fluid, the main body having a curved section. The transfer tube also includes a first mating face coupled to the first end of the main body. The transfer tube also includes a second mating face coupled to the second end of the main body. At least one of the first mating face or the second mating face is configured to be coupled to a platform body of the outer diameter platform.

    Abstract translation: 所描述的是用于与连接到平台的燃气涡轮发动机的翼型一起使用的传送管。 传送管包括主体，主体具有限定入口的第一端，所述第一端被配置为接收流体流动，第二端限定用于流体流动的出口，主体具有弯曲部分。 传送管还包括联接到主体的第一端的第一配合面。 传送管还包括联接到主体的第二端的第二配合面。 所述第一配合面或所述第二配合面中的至少一个被配置为联接到所述外径平台的平台主体。

    SEAL RING
    25.
    发明申请
    SEAL RING 审中-公开
    密封环

    公开(公告)号：US20160109025A1

    公开(公告)日：2016-04-21

    申请号：US14852918

    申请日：2015-09-14

    Applicant: United Technologies Corporation

    Inventor： Michael G. McCaffrey ,  John R. Farris ,  Theodore W. Hall ,  John J. Korzendorfer ,  Elizabeth F. Vinson ,  Jeffrey Michael Jacques ,  John E. Paul ,  Ross Wilson ,  Edwin Otero ,  Alan W. Stoner

    IPC: F16J15/06 ,  F01D11/02 ,  F16J15/44

    CPC classification number: F16J15/441 ,  F01D11/025 ,  F16J15/442 ,  F16J15/445

    Abstract: A seal ring system is provided. The seal ring system comprises a segment defining a slot, a pedal along the slot, and an opening offset from the slot. A retention fastener may be disposed in the opening. A seal ring system is also provided comprising a first segment defining a first opening, a second segment defining a second opening, and a retention fastener extending through the first and second openings. The retention fastener configured to allow relative radial movement of the first segment and the second segment. A seal is further provided comprising a seal ring having a central axis, a petal extending radially inward with respect to the central axis of the seal ring, and a sealing disk axially proximate the seal ring. The sealing disk may have a seal shoe configured as a primary seal. The petal may extend toward the seal shoe.

    Abstract translation: 提供密封环系统。 密封环系统包括限定槽的段，沿着槽的踏板和与槽相偏离的开口。 保持紧固件可以设置在开口中。 还提供了密封环系统，其包括限定第一开口的第一段，限定第二开口的第二段和延伸穿过第一和第二开口的保持紧固件。 保持紧固件被构造成允许第一段和第二段的相对径向移动。 还提供了一种密封件，其包括具有中心轴线的密封环，相对于密封环的中心轴线径向向内延伸的花瓣，以及轴向邻近密封环的密封盘。 密封盘可以具有被配置为主密封件的密封垫。 花瓣可以朝向密封鞋延伸。

    SEAL DAMPER WITH IMPROVED RETENTION
    27.
    发明申请
    SEAL DAMPER WITH IMPROVED RETENTION 审中-公开
    具有改进保持性的密封阻尼器

    公开(公告)号：US20150226077A1

    公开(公告)日：2015-08-13

    申请号：US14429089

    申请日：2013-03-14

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Jeffrey S. Beattie ,  Jeffrey Michael Jacques

    IPC: F01D11/00 ,  F01D5/22

    CPC classification number: F01D11/006 ,  F01D5/22 ,  F01D5/26 ,  F01D11/008

    Abstract: A seal damper system includes a plurality of circumferentially spaced blades that each include a platform and an air-foil that extends radially outwardly from the platform. A pocket is arranged circumferentially intermediate the blades and radially inwardly of the platform. A seal damper is arranged in the pocket. The seal damper includes a base section that extends along an axial dimension from a first axial end to an opposing second axial end. The base section joins a first arm that extends radially inwardly from the first axial end and a second arm that extends radially inwardly from the second axial end. The first arm includes a free end having a pair of spaced apart shoulders.

    Abstract translation: 密封阻尼器系统包括多个周向间隔开的叶片，每个叶片包括平台和从平台径向向外延伸的空气箔片。 一个口袋沿圆周方向布置在刀片和径向向内的平台上。 密封阻尼器布置在口袋中。 密封阻尼器包括基部，该基部沿轴向尺寸从第一轴向端延伸到相对的第二轴向端。 基部接合从第一轴向端径向向内延伸的第一臂和从第二轴向端径向向内延伸的第二臂。 第一臂包括具有一对间隔开的肩部的自由端。

    TURBINE BLADE ROOT PROFILE
    28.
    发明申请
    TURBINE BLADE ROOT PROFILE 有权
    涡轮叶片轮廓

    公开(公告)号：US20140083114A1

    公开(公告)日：2014-03-27

    申请号：US13626937

    申请日：2012-09-26

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Jeffrey S. Beattie ,  Jeffrey Michael Jacques

    IPC: F01D5/30 ,  F01D5/18

    CPC classification number: F01D5/30 ,  F01D5/18 ,  F01D5/3007

    Abstract: A turbine blade for a gas turbine engine includes an airfoil that extends in a first radial direction from a platform. A root extends from the platform in a second radial direction and has opposing lateral sides that provide a firtree-shaped contour. The contour includes first, second and third lobes on each of the lateral sides and that tapers relative to the radial direction away from the platform. The first, second and third lobes each provide contact surfaces arranged at about 45° relative to the radial direction. A contact plane on each lateral side at an angle of about 11° relative to the radial direction defining a contact point on each of the contact surfaces. The first, second and third lobes each include first, second and third grooves that are substantially aligned with one another along an offset plane spaced a uniform offset distance from the contact plane.

    Abstract translation: 用于燃气涡轮发动机的涡轮机叶片包括从平台沿第一径向方向延伸的翼型件。 根部在第二径向方向上从平台延伸并且具有相对的侧向侧面，该侧面侧面提供保持曲面的轮廓。 轮廓包括在每个侧面上的第一，第二和第三凸角，并且相对于远离平台的径向方向逐渐变细。 第一，第二和第三叶片各自提供相对于径向方向布置成大约45°的接触表面。 在每个侧面上的接触平面相对于径向方向以约11°的角度限定每个接触表面上的接触点。 第一，第二和第三凸耳各自包括第一，第二和第三凹槽，其沿着与接触平面间隔开均匀偏移距离的偏移平面彼此基本对齐。

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