中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

255 records (took 0.016 seconds)

    VARIABLE AREA VANE ARRANGEMENT FOR A TURBINE ENGINE
    252.
    发明申请
    VARIABLE AREA VANE ARRANGEMENT FOR A TURBINE ENGINE 审中-公开
    用于涡轮发动机的可变区域风扇装置

    公开(公告)号：US20150361822A1

    公开(公告)日：2015-12-17

    申请号：US14762302

    申请日：2013-01-21

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Michael G. McCaffrey ,  Raymond Surace ,  Tracy A. Propheter-Hinckley

    IPC: F01D17/16

    CPC classification number: F01D17/162 ,  F01D5/145 ,  F01D5/187

    Abstract: An adjustable stator vane for a turbine engine includes a shaft, a flange and a stator vane body that pivots about a variable vane axis. The stator vane body extends axially between a first end and a second end. The stator vane body includes an airfoil, a cavity, and a body surface located at the first end. The cavity extends axially from an inlet in the body surface and into the airfoil. The shaft extends along the variable vane axis from the first end. The flange extends circumferentially around the inlet and the shaft, and radially from the stator vane body.

    Abstract translation: 用于涡轮发动机的可调节定子叶片包括轴，凸缘和绕可变叶片轴线枢转的定子叶片体。 定子叶片体在第一端和第二端之间轴向延伸。 定子叶片主体包括翼型件，空腔和位于第一端的主体表面。 空腔从体表面的入口轴向延伸到翼型中。 轴从第一端沿着可变叶片轴线延伸。 凸缘围绕入口和轴周向延伸，并且从定子叶片体径向延伸。

    GAS TURBINE ENGINE AIRFOIL COOLING PASSAGE CONFIGURATION
    253.
    发明申请
    GAS TURBINE ENGINE AIRFOIL COOLING PASSAGE CONFIGURATION 审中-公开
    气体涡轮发动机空气冷却通风配置

    公开(公告)号：US20150315929A1

    公开(公告)日：2015-11-05

    申请号：US14696627

    申请日：2015-04-27

    Applicant: United Technologies Corporation

    Inventor： Tracy A. Propheter-Hinckley ,  San Quach

    IPC: F01D25/12

    CPC classification number: F01D25/12 ,  F01D5/187 ,  F05D2220/32 ,  F05D2260/22141 ,  Y02T50/676

    Abstract: An airfoil for a gas turbine engine includes an airfoil body that extends in a radial direction from a support. The airfoil body has pressure and suction side walls joined at leading and trailing edges to provide an exterior airfoil surface. A chord-wise direction extends between the leading and trailing edges and a thickness direction transverse to chord-wise direction and extending between the pressure and suction side walls. Cooling passages extend from the support into the airfoil body. The cooling passages include adjacent passageways in the thickness direction and are separated by a chord-wise wall. One of the adjacent passageways is adjacent to another passageway in the chord-wise direction and is separated by a rib in the thickness direction. The rib is discontinued at a location along the radial direction to provide an opening that fluidly connects one of the adjacent passageways to the other passageway.

    Abstract translation: 用于燃气涡轮发动机的翼型件包括从支撑件沿径向方向延伸的翼型件本体。 翼型体具有在前缘和后缘处连接的压力和吸力侧壁，以提供外部翼面表面。 并列方向在前缘和后缘之间延伸，厚度方向横向于弦向​​并在压力侧和吸力侧壁之间延伸。 冷却通道从支撑件延伸到翼型体中。 冷却通道包括在厚度方向上相邻的通道，并且由一个和弦壁隔开。 相邻通道中的一个沿着并列方向的另一个通道相邻，并且在厚度方向上被肋条隔开。 肋沿着径向方向停止，以提供将相邻通道中的一个流体连接到另一个通道的开口。

    AIRFOIL AND METHOD OF MAKING
    255.
    发明申请
    AIRFOIL AND METHOD OF MAKING 有权
    飞行器及其制造方法

    公开(公告)号：US20140199177A1

    公开(公告)日：2014-07-17

    申请号：US13737200

    申请日：2013-01-09

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Tracy A. Propheter-Hinckley ,  San Quach ,  Matthew A. Devore

    IPC: F01D5/18 ,  B23P15/04

    CPC classification number: F01D5/187 ,  B22C9/10 ,  B22C9/103 ,  F01D5/186 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/205 ,  Y10T29/49337

    Abstract: An airfoil includes leading and trailing edges, a first exterior wall extending from the leading edge to the trailing edge and having inner and outer surfaces, a second exterior wall extending from the leading edge to the trailing edge generally opposite the first exterior wall and having inner and outer surfaces, and cavities within the airfoil. A first cavity extends along the inner surface of the first exterior wall and a first inner wall and has an upstream end and a downstream end, and a feed cavity is located between the first inner wall and the second exterior wall.

    Abstract translation: 机翼包括前缘和后缘，从前缘延伸到后缘并具有内表面和外表面的第一外壁，从前缘延伸到后缘的第二外壁，大体与第一外壁相对，并且具有内 和外表面以及翼型内的空腔。 第一腔沿着第一外壁的内表面延伸并且具有第一内壁并具有上游端和下游端，并且进料腔位于第一内壁和第二外壁之间。

Patent Agency Ranking