中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

5 records (took 0.023 seconds)

    REVERSIBLE BLADE DAMPER
    1.
    发明申请
    REVERSIBLE BLADE DAMPER 审中-公开
    可逆式叶片阻尼器

    公开(公告)号：WO2014107212A3

    公开(公告)日：2014-10-09

    申请号：PCT/US2013065202

    申请日：2013-10-16

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： DONNELL BRANDON S ,  GIRMA YAFET ,  O'DELL GINA C

    IPC: F01D5/22 ,  F01D5/26 ,  F01D11/08

    CPC classification number: F01D5/22 ,  F01D5/26 ,  F01D11/005 ,  F01D11/006 ,  F01D11/008 ,  F05D2260/36

    Abstract: A damper body extends between an axial first end, an opposing axial second end, a first lateral side, and an opposing second lateral side. A first pair of lugs are disposed at the first axial end and a second pair of lugs are disposed at the second axial end. In the first lug pair, a lug has an axially outermost foot which extends laterally beyond a lateral wall. The second lug pair has a lug with an axial outermost point with a foot extending laterally beyond a lateral wall. The foot on the first axial end and the foot on the second axial end are on opposed lateral sides.

    Abstract translation: 阻尼体在轴向第一端，相对的轴向第二端，第一侧面和相对的第二侧面之间延伸。 第一对凸耳设置在第一轴向端部，第二对凸耳设置在第二轴向端。 在第一凸耳对中，凸耳具有横向延伸超过侧壁的轴向最外侧的脚。 第二凸耳对具有带轴向最外点的凸耳，其中一个脚横向延伸超过侧壁。 第一轴向端部的脚和第二轴向端部上的脚在相对的侧面上。

    GAS TURBINE ENGINE TURBINE BLADE TIP COOLING
    2.
    发明申请
    GAS TURBINE ENGINE TURBINE BLADE TIP COOLING 审中-公开
    燃气涡轮发动机涡轮叶片冷却

    公开(公告)号：WO2014137443A3

    公开(公告)日：2014-11-20

    申请号：PCT/US2013075796

    申请日：2013-12-17

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： AUXIER JAMES T ,  O'HEARN JASON L ,  SLAVENS THOMAS N ,  GIRMA YAFET

    IPC: F01D5/18 ,  F01D25/12 ,  F02C7/12 ,  F04D29/58

    CPC classification number: F01D5/186 ,  F01D5/20 ,  F01D11/08 ,  F05D2240/307 ,  Y02T50/676

    Abstract: An airfoil for a gas turbine engine includes pressure and suction walls spaced apart from one another and joined at leading and trailing edges to provide an airfoil having an exterior surface that extends in a radial direction to a tip. A camber line at the tip extends from the leading edge to the trailing edge. Pressure and suction side shelves are arranged in the exterior surface on opposing sides of the camber line respectively in the pressure and suction side walls. A plateau is proud of and separates the pressure and suction side shelves. The plateau is arranged along the camber line and extends to the leading edge.

    Abstract translation: 用于燃气涡轮发动机的翼型件包括彼此间隔开并在前缘和后缘处连接的压力和吸力壁，以提供具有沿径向方向延伸到尖端的外表面的翼型件。 尖端的弧形线从前缘延伸到后缘。 压力和吸力侧搁架分别设置在压力和吸力侧壁的外倾线的相对侧的外表面上。 高原为压力和吸力侧货架感到自豪和分离。 高原沿着弧线布置并延伸到前缘。

Patent Agency Ranking