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    Systems for preventing wear on turbine blade tip shrouds
    83.
    发明授权
    Systems for preventing wear on turbine blade tip shrouds 有权
    用于防止涡轮叶片尖端罩磨损的系统

    公开(公告)号：US07771171B2

    公开(公告)日：2010-08-10

    申请号：US11638818

    申请日：2006-12-14

    Applicant: Patrick Mohr ,  Daniel Nowak ,  Emilio Fernandez ,  Michael Arnett ,  David Williams ,  Carlos Collado

    Inventor： Patrick Mohr ,  Daniel Nowak ,  Emilio Fernandez ,  Michael Arnett ,  David Williams ,  Carlos Collado

    IPC: F01D5/22

    CPC classification number: F01D5/225 ,  F05C2201/0463 ,  F05D2300/506

    Abstract: A system in a turbine engine for preventing wear on a tip shroud of a turbine blade that includes a pocket formed in a contact surface of the tip shroud and a plug that fits within the pocket and has a durable outer surface. The durable outer surface may include a cobalt-based hardfacing powder. The pocket may be machined out of the contact surface, and the plug may include a plug of predetermined size that fits snugly into the pocket. In some embodiments, the durable outer surface may substantially align with the contact surface after the plug is fitted into the pocket. In other embodiments, the durable outer surface may remain slightly raised from the contact surface after the plug has been fitted into the pocket.

    Abstract translation: 一种涡轮发动机中的系统，用于防止涡轮机叶片的尖端护罩上的磨损，该系统包括形成在尖端护罩的接触表面中的凹穴和装配在口袋内并且具有耐用的外表面的塞子。 耐用的外表面可以包括钴基硬化粉末。 口袋可以从接触表面加工出来，并且塞子可以包括预先规定尺寸的塞子，该栓塞紧贴地配合到口袋中。 在一些实施例中，在将塞子装配到口袋中之后，耐用的外表面可以与接触表面大致对准。 在其他实施例中，在插头已经装配到口袋中之后，耐用的外表面可以保持从接触表面稍微升高。

    Leakage seal for gas path of gas turbine
    84.
    发明授权
    Leakage seal for gas path of gas turbine 有权
    燃气轮机气路泄漏密封

    公开(公告)号：US07389991B2

    公开(公告)日：2008-06-24

    申请号：US11236243

    申请日：2005-09-27

    Applicant: Vincent T. Riggi, Jr. ,  Ronald A. Riggi

    Inventor： Vincent T. Riggi, Jr. ,  Ronald A. Riggi

    IPC: F16J15/16

    CPC classification number: F16J15/3288 ,  F01D11/00 ,  F05C2201/0463 ,  F05C2201/0466 ,  F05D2250/71 ,  F05D2300/601 ,  F16J15/3284

    Abstract: A leakage seal for use in a gas path between two relatively rotatable members of a gas turbine comprises a foil layer and a cloth layer. The foil layer has two expansive surfaces, a single one of which is covered by the cloth layer. The leakage seal has a proximal end, a distal end, and a generally flat region between the proximal and distal ends. The proximal end is attached to an associated one of the turbine members. The distal end diverges from the generally flat region so as to define a curved hook, along which the cloth portion is wrapped over the foil layer, when the distal end is viewed in cross-section.

    Abstract translation: 用于燃气轮机的两个相对旋转的构件之间的气体路径中的泄漏密封件包括箔层和布层。 箔层具有两个膨胀表面，其中一个被布层覆盖。 泄漏密封件具有近端，远端以及近端和远端之间的大致平坦的区域。 近端附接到相关联的一个涡轮机构件。 远端从大体上平坦的区域分开，以限定弯曲的钩子，当横截面看到远端时，布料部分沿着该部分被卷绕在箔层上。

    Leakage seal for gas path of gas turbine
    86.
    发明申请
    Leakage seal for gas path of gas turbine 有权
    燃气轮机气路泄漏密封

    公开(公告)号：US20070069478A1

    公开(公告)日：2007-03-29

    申请号：US11236243

    申请日：2005-09-27

    Applicant: Vincent Riggi ,  Ronald Riggi

    Inventor： Vincent Riggi ,  Ronald Riggi

    IPC: F16J15/00

    CPC classification number: F16J15/3288 ,  F01D11/00 ,  F05C2201/0463 ,  F05C2201/0466 ,  F05D2250/71 ,  F05D2300/601 ,  F16J15/3284

    Abstract: A leakage seal for use in a gas path between two relatively rotatable members of a gas turbine comprises a foil layer and a cloth layer. The foil layer has two expansive surfaces, a single one of which is covered by the cloth layer. The leakage seal has a proximal end, a distal end, and a generally flat region between the proximal and distal ends. The proximal end is attached to an associated one of the turbine members. The distal end diverges from the generally flat region so as to define a curved hook, along which the cloth portion is wrapped over the foil layer, when the distal end is viewed in cross-section.

    Abstract translation: 用于燃气轮机的两个相对旋转的构件之间的气体路径中的泄漏密封件包括箔层和布层。 箔层具有两个膨胀表面，其中一个被布层覆盖。 泄漏密封件具有近端，远端以及近端和远端之间的大致平坦的区域。 近端附接到相关联的一个涡轮机构件。 远端从大体上平坦的区域分开，以限定弯曲的钩子，当横截面看到远端时，布料部分沿着该部分被卷绕在箔层上。

    Turbine blade capable of inhibiting reaction
    87.
    发明申请
    Turbine blade capable of inhibiting reaction 有权
    能够抑制反应的涡轮叶片

    公开(公告)号：US20070026256A1

    公开(公告)日：2007-02-01

    申请号：US10558648

    申请日：2004-02-25

    Applicant: Yasuhiro Aoki ,  Akihiro Sato

    Inventor： Yasuhiro Aoki ,  Akihiro Sato

    IPC: B32B15/00 ,  B32B15/20 ,  B32B15/01

    CPC classification number: C23C10/02 ,  F01D5/288 ,  F05C2201/0463 ,  F05D2300/132 ,  Y02T50/671 ,  Y10T428/12847 ,  Y10T428/12861 ,  Y10T428/1291 ,  Y10T428/12931 ,  Y10T428/12944

    Abstract: A reaction control turbine blade is formed by applying a reaction control material to the surface of an Ni-base superalloy before applying aluminum diffusion coating to the Ni-base superalloy. The reaction control material is Co, Cr or Ru, or an alloy of which main component is selected from a group consisting of Co, Cr, Ru. Thereby, it is possible to enhance the oxidation resistance of the Ni-base superalloy, and to control formation of a secondary reaction zone.

    Abstract translation: 在向Ni基超级合金施加铝扩散涂层之前，通过将反应控制材料施加到Ni基超级合金的表面上来形成反应控制涡轮叶片。 反应控制材料是Co，Cr或Ru，或者主要成分选自Co，Cr，Ru的合金。 由此，可以提高Ni基超合金的抗氧化性，并且可以控制二次反应区的形成。

    Rotating blade body
    89.
    发明申请
    Rotating blade body 有权
    旋转刀体

    公开(公告)号：US20060177312A1

    公开(公告)日：2006-08-10

    申请号：US11340510

    申请日：2006-01-27

    Applicant: Yasuoki Tomita ,  Kouji Watanabe ,  Masamitsu Okuzono ,  Masaki Ono

    Inventor： Yasuoki Tomita ,  Kouji Watanabe ,  Masamitsu Okuzono ,  Masaki Ono

    IPC: F01D11/00

    CPC classification number: F01D5/081 ,  F01D5/22 ,  F01D11/008 ,  F05C2201/0463 ,  F05C2201/0466 ,  F05D2250/29 ,  F05D2260/20 ,  Y02T50/671 ,  Y02T50/676 ,  Y10S416/50

    Abstract: A rotating blade body is provided that can restrain vibrations of rotating blades effectively. The rotating blade body comprises rotor disc, a plurality of rotating blades being assembled so as to extend from the outer circumference of the rotor disc in a radial pattern, and sealing pins extending along the direction of the rotating shaft in the gaps between the platforms of the rotating blades being adjacent in circumferential direction. The sealing pins have a through-hole made therein, penetrating axially from one end surface to the other end surface.

    Abstract translation: 提供了可以有效地抑制旋转叶片的振动的旋转叶片体。 旋转叶片主体包括转子盘，多个旋转叶片组装成以径向图案从转子盘的外圆周延伸，以及沿着旋转轴的方向在第二平台之间的间隙中延伸的密封销 旋转叶片在圆周方向上相邻。 密封销具有形成在其中的通孔，其从一个端面轴向穿透到另一端面。

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