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    Variable dual spring blade root support for gas turbines
    2.
    发明授权
    Variable dual spring blade root support for gas turbines 有权

    公开(公告)号：US09909431B2

    公开(公告)日：2018-03-06

    申请号：US14699269

    申请日：2015-04-29

    申请人： Siemens Energy, Inc.

    发明人： Charalambos Polyzopoulos ,  Mohit Gupta ,  Robert Hudson ,  Erica Holden ,  David Myers

    IPC分类号： F01D5/32 ,  F01D5/30

    CPC分类号： F01D5/323 ,  F01D5/3007 ,  F05D2250/183 ,  F05D2250/184 ,  F05D2250/25

    摘要： An adjustable blade root spring device for turbine blade fixation in turbomachinery. The device is designed to be placed in a space in a rotor disk cavity adjacent to a tip of a blade root, where the device applies a radial outward force on the turbine blade to fix the blade position in the rotor disk. The device includes a wave spring with integral end blocks which is compressed by a bolt and a coil spring. When the wave spring is compressed in length, it increases in height and makes contact with the rotor disk and the turbine blade. The force of the wave spring on the turbine blade can be adjusted via the bolt, and the coil spring provides an increased compliance range. The body of the device has an oblong cross-sectional shape, thereby preventing rotation of the device in the space between the blade and the disk.

    DAMPER RING
    7.
    发明申请
    DAMPER RING 审中-公开

    公开(公告)号：US20170321556A1

    公开(公告)日：2017-11-09

    申请号：US15145160

    申请日：2016-05-03

    申请人： Pratt & Whitney Canada Corp.

    发明人： MAKSIM PANKRATOV

    IPC分类号： F01D5/10 ,  F02C3/04

    CPC分类号： F01D5/10 ,  F02C3/04 ,  F05D2220/32 ,  F05D2250/182 ,  F05D2250/183 ,  F05D2250/184

    摘要： A damper ring is mounted in frictional engagement with a radially inwardly facing surface of a circumferential groove defined in a rotary part of a gas turbine engine. Energy dissipation is provided via sliding friction of the ring in the groove. The damper ring has a circumferentially segmented ring body having a non-uniform circumferential stiffness around its circumference including a locally reduced stiffness in a circumferential direction between each pair of circumferentially adjacent ring segments.

    TAPERED LAND THRUST BEARING DEVICE AND TURBOCHARGER PROVIDED WITH THE BEARING DEVICE
    9.
    发明申请
    TAPERED LAND THRUST BEARING DEVICE AND TURBOCHARGER PROVIDED WITH THE BEARING DEVICE 审中-公开
    带有轴承装置的带状陆面轴承装置和涡轮增压器

    公开(公告)号：US20160348721A1

    公开(公告)日：2016-12-01

    申请号：US15113894

    申请日：2014-02-27

    申请人： MITSUBISHI HEAVY INDUSTRIES, LTD.

    发明人： Takaya FUTAE ,  Hideaki NISHIDA

    IPC分类号： F16C33/10 ,  F04D17/10 ,  F01D25/16 ,  F16C17/04 ,  F16C33/12

    CPC分类号： F16C33/107 ,  F01D25/168 ,  F02B39/00 ,  F05D2220/40 ,  F05D2250/182 ,  F05D2250/183 ,  F05D2250/191 ,  F05D2250/292 ,  F05D2250/611 ,  F16C17/045 ,  F16C17/047 ,  F16C33/1075 ,  F16C33/128 ,  F16C2360/24

    摘要： An object is to provide a tapered land thrust bearing device with a land surface having a substantially reduced area without changing the contour shape of the land surface even if the area of the land surface is small, and high mechanical efficiency, as well as a turbocharger provided with the bearing device. A tapered land thrust bearing device includes: a flange portion fitted onto a rotary shaft and including a first thrust portion; and a thrust member including a second thrust portion which is disposed around a through hole and which faces the first thrust portion of the flange portion. The first thrust portion or the second thrust portion includes a plurality of land surfaces each of which is parallel to a plane orthogonal to an axis of the rotary shaft, the land surfaces being disposed at intervals in a circumferential direction of the through hole, a plurality of tapered surfaces each of which is disposed between the plurality of land surfaces, joined via a step to a boundary of the land surface on one side in the circumferential direction of the through hole, and joined continuously to a boundary of the land surface on the other side in the circumferential direction of the through hole, and at least one concave portion disposed on each of the plurality of land surfaces.

    摘要翻译： 本发明的目的是提供一种具有大大减小的面积而具有大幅减小的面积的锥形陆面推力轴承装置，而不改变陆面的轮廓形状，即使陆面的面积小，机械效率高，以及涡轮增压器 设有轴承装置。 锥形陆面推力轴承装置包括：安装在旋转轴上并包括第一推力部分的凸缘部分; 以及推力构件，其包括设置在通孔周围并且与凸缘部的第一推力部相对的第二推力部。 所述第一推力部或所述第二推力部具有与所述旋转轴的轴正交的平面平行的多个台面，所述台面沿所述贯通孔的圆周方向间隔配置， 所述锥形表面设置在所述多个台面表面之间，所述多个台面表面之间经由台阶在所述通孔的圆周方向上的一侧上的所述台面的边界接合，并且连续地连接到所述通孔的所述台面的边界 在通孔的圆周方向上的另一侧，以及设置在多个台面的每一个上的至少一个凹部。

    GAS TURBINE ENGINE WITH SEAL HAVING PROTRUSIONS
    10.
    发明申请
    GAS TURBINE ENGINE WITH SEAL HAVING PROTRUSIONS 审中-公开
    具有密封的气体涡轮发动机

    公开(公告)号：US20160222809A1

    公开(公告)日：2016-08-04

    申请号：US15021945

    申请日：2014-08-21

    申请人： UNITED TECHNOLOGIES CORPORATION

    发明人： Matthew Andrew Hough ,  Christopher Corcoran ,  Jeffrey S. Beattie

    IPC分类号： F01D11/00

    CPC分类号： F01D11/006 ,  F01D5/22 ,  F05D2250/181 ,  F05D2250/182 ,  F05D2250/183 ,  F05D2250/75 ,  F05D2260/22141

    摘要： A gas turbine engine includes a turbine section. The turbine section includes a disk that is rotatable about an axis. A plurality of turbine blades are mounted around a periphery of the disk, and a plurality of seals are arranged between the turbine blades and the periphery of the disk. Each of the seals includes, with respect to the axis, a radially outer surface and a radially inner surface. The radially inner surface includes a plurality of protrusions.

    摘要翻译： 燃气涡轮发动机包括涡轮部分。 涡轮机部分包括可围绕轴线旋转的盘。 多个涡轮机叶片围绕盘的周边安装，并且多个密封件布置在涡轮机叶片与盘周边之间。 每个密封件相对于轴线包括径向外表面和径向内表面。 径向内表面包括多个突起。