中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

14 records (took 0.02 seconds)

    COOLED TURBINE BLADE
    3.
    发明申请
    COOLED TURBINE BLADE 审中-公开
    冷却涡轮叶片

    公开(公告)号：WO1995026459A1

    公开(公告)日：1995-10-05

    申请号：PCT/US1995003573

    申请日：1995-03-21

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： UNITED TECHNOLOGIES CORPORATION ,  ZELESKY, Mark, F.

    IPC: F01D05/18

    CPC classification number: F01D5/187

    Abstract: Turbine blade (10) has a plurality of trailing edge discharge openings (28) discharging cooling air. The blade trailing edge has an increasing thickness "E" toward the tip end (16). Discharge openings with the shortened pressure wall "L" have lesser distances "L" toward the tip end.

    Abstract translation: 涡轮叶片（10）具有排出冷却空气的多个后缘排放口（28）。 叶片后缘朝向顶端（16）具有增加的厚度“E”。 具有缩短的压力壁“L”的排出开口具有较小的距离“L”朝向末端。

    COOLING HOLE WITH THERMO-MECHANICAL FATIGUE RESISTANCE
    6.
    发明申请
    COOLING HOLE WITH THERMO-MECHANICAL FATIGUE RESISTANCE 审中-公开
    具有热机械疲劳电阻的冷却孔

    公开(公告)号：WO2013165502A2

    公开(公告)日：2013-11-07

    申请号：PCT/US2013/025680

    申请日：2013-02-12

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： KOHLI, Atul ,  GLEINER, Matthew, S. ,  ZELESKY, Mark, F. ,  XU, JinQuan

    IPC: F02C7/18 ,  F01D25/12 ,  F02K3/00 ,  F01D5/08

    CPC classification number: F23R3/06 ,  F01D5/186 ,  F01D9/065 ,  F05D2240/81 ,  F05D2260/202 ,  F23R2900/03042 ,  Y02T50/676

    Abstract: A gas turbine engine includes a wall having first and second wall surfaces and a cooling hole extending through the wall. The cooling hole includes an inlet located at the first wall surface, an outlet located at the second wall surface, a metering section extending downstream from the inlet and a diffusing section extending from the metering section to the outlet. The diffusing section includes a first lobe diverging longitudinally and laterally from the metering section, a second lobe diverging longitudinally and laterally from the metering section, an upstream end located at the outlet, a trailing edge located at the outlet opposite the upstream end and generally opposite first and second sidewalls. Each sidewall has an edge extending along the outlet between the upstream end and the trailing edge. Each edge diverges laterally from the upstream end and converges laterally before reaching the trailing edge.

    Abstract translation: 燃气涡轮发动机包括具有第一和第二壁表面的壁和延伸穿过壁的冷却孔。 冷却孔包括位于第一壁表面的入口，位于第二壁表面处的出口，从入口下游延伸的计量部分和从计量部分延伸到出口的扩散部分。 扩散部分包括从计量部分纵向和横向分叉的第一凸角，从计量部分纵向和横向分开的第二凸角，位于出口处的上游端，位于与上游端相对的出口处的后缘， 第一和第二侧壁。 每个侧壁具有沿着上游端和后缘之间的出口延伸的边缘。 每个边缘从上游端横向分开，并在到达后缘之前横向会聚。

    GAS TURBINE ENGINE COMPONENT WITH MULTI-LOBED COOLING HOLE
    9.
    发明申请
    GAS TURBINE ENGINE COMPONENT WITH MULTI-LOBED COOLING HOLE 审中-公开
    具有多孔冷却孔的气体涡轮发动机部件

    公开(公告)号：WO2013123121A1

    公开(公告)日：2013-08-22

    申请号：PCT/US2013/026041

    申请日：2013-02-14

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： GLEINER, Matthew, S. ,  ZELESKY, Mark, F. ,  KOHLI, Atul

    IPC: F02C7/12 ,  F01D5/18 ,  F01D25/12 ,  F02C9/00

    CPC classification number: F01D5/187 ,  F01D5/186 ,  F01D9/065 ,  F01D25/12 ,  F05D2240/81 ,  F05D2250/21 ,  F05D2250/232 ,  F05D2260/202 ,  F23R2900/03042 ,  Y02T50/676 ,  Y10T29/49234

    Abstract: A component for a gas turbine engine includes a wall and a cooling hole extending through the wall. The wall has a first surface and a second surface. The cooling hole includes a metering section extending downstream from an inlet in the first surface of the wall and a diffusion section extending from the metering section to an outlet in the second surface of the wall. The diffusion section includes a first plurality of lobes diverging longitudinally and laterally from the metering section on a first side of a centerline axis of the cooling hole and a second plurality of lobes diverging longitudinally and laterally from the metering section on a second side of the centerline axis.

    Abstract translation: 用于燃气涡轮发动机的部件包括壁和延伸穿过壁的冷却孔。 该壁具有第一表面和第二表面。 冷却孔包括从壁的第一表面中的入口的下游延伸的计量部分和从计量部分延伸到壁的第二表面中的出口的扩散部分。 扩散部分包括在冷却孔的中心线轴线的第一侧上从计量部分纵向和横向分叉的第一多个凸角，以及在中心线的第二侧上从计量部分纵向和横向地分散的第二多个凸角 轴。

    TRI-LOBED COOLING HOLE AND METHOD OF MANUFACTURE
    10.
    发明申请
    TRI-LOBED COOLING HOLE AND METHOD OF MANUFACTURE 审中-公开
    三轴冷却孔及其制造方法

    公开(公告)号：WO2013122906A1

    公开(公告)日：2013-08-22

    申请号：PCT/US2013/025686

    申请日：2013-02-12

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： ZELESKY, Mark, F. ,  KOHLI, Atul ,  LEWIS, Scott, D.

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

    CPC classification number: F23R3/06 ,  F01D5/186 ,  F01D9/065 ,  F05D2240/81 ,  F05D2260/202 ,  F23R2900/03041 ,  F23R2900/03042 ,  Y02T50/673 ,  Y02T50/676

    Abstract: A gas turbine engine component includes first and second wall surfaces, an inlet located at the first wall surface, an outlet located at the second wall surface and a diffusing section positioned between the inlet and the outlet. The diffusing section includes a first lobe, a second lobe adjacent the first lobe and a third lobe adjacent the second lobe. The first lobe and the second lobe meet at a first ridge and the second lobe and the third lobe meet at a second ridge.

    Abstract translation: 燃气涡轮发动机部件包括第一和第二壁表面，位于第一壁表面处的入口，位于第二壁表面处的出口和位于入口和出口之间的扩散部分。 扩散部分包括第一凸角，与第一凸角相邻的第二凸角和与第二凸角相邻的第三凸角。 第一个小叶和第二个小叶在第一个山脊相交，第二个叶和第三个叶在第二个山脊相遇。

Patent Agency Ranking