中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

7 records (took 0.028 seconds)

    GAS TURBINE ENGINE COMPONENT COOLING WITH RESUPPLY OF COOLING PASSAGE
    1.
    发明申请
    GAS TURBINE ENGINE COMPONENT COOLING WITH RESUPPLY OF COOLING PASSAGE 审中-公开
    气体涡轮发动机组件冷却与冷却通气

    公开(公告)号：WO2015006026A1

    公开(公告)日：2015-01-15

    申请号：PCT/US2014/042732

    申请日：2014-06-17

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： SPANGLER, Brandon W. ,  MONGILLO JR., Dominic J.

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

    CPC classification number: F01D5/187 ,  F01D9/041 ,  F01D11/08 ,  F01D25/12 ,  F05D2220/32 ,  F05D2230/00 ,  F05D2230/21 ,  F05D2240/81 ,  F05D2260/202 ,  F05D2260/204 ,  F05D2260/205 ,  Y02T50/676

    Abstract: A gas turbine engine component includes a structure having a wall that provides an exterior surface. A first cooling passage is arranged adjacent to and interiorly of the wall. A second cooling passage is arranged in the wall and provides a first fluid flow direction. A resupply channel is arranged in the wall and is fluidly interconnected to the second cooling passage. A resupply hole fluidly interconnects the first cooling passage and the resupply channel. The resupply channel is transverse relative to the second cooling passage to provide a second fluid flow direction that extends from the resupply hole to the second cooling passage.

    Abstract translation: 燃气涡轮发动机部件包括具有提供外表面的壁的结构。 第一冷却通道布置成与壁的内部和内部相邻。 第二冷却通道布置在壁中并提供第一流体流动方向。 补给通道布置在壁中并且流体地互连到第二冷却通道。 补给孔流体地互连第一冷却通道和补给通道。 补给通道相对于第二冷却通道是横向的，以提供从补给孔延伸到第二冷却通道的第二流体流动方向。

    GAS TURBINE ENGINE SERPENTINE COOLING PASSAGE
    2.
    发明申请
    GAS TURBINE ENGINE SERPENTINE COOLING PASSAGE 审中-公开
    燃气涡轮发动机SERPENTINE冷却通风

    公开(公告)号：WO2014042955A1

    公开(公告)日：2014-03-20

    申请号：PCT/US2013/058282

    申请日：2013-09-05

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： PEREZ, Rafel A. ,  PIETRASZKIEWICZ, Edward F. ,  LEVINE, Jeffrey R. ,  MONGILLO JR., Dominic J.

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

    CPC classification number: F01D5/188 ,  F01D5/187 ,  F05D2250/183 ,  F05D2250/185 ,  F05D2260/2212 ,  F05D2260/22141 ,  F05D2270/17 ,  Y02T50/673 ,  Y02T50/676

    Abstract: A gas turbine engine component includes a structure having a cooling passage providing upstream and downstream portions separated from one another by an inner wall and fluidly connected by a bend. The downstream portion includes an outer wall opposite the inner wall to provide a downstream region extending between the inner and outer walls. A turbulence promoter extends from the outer wall adjacent to the bend in the downstream portion. The turbulence promoter is absent from a stagnation region adjoining the inner wall adjacent to the bend in the downstream portion

    Abstract translation: 燃气涡轮发动机部件包括具有冷却通道的结构，该冷却通道提供通过内壁彼此分离并通过弯曲部流体连接的上游和下游部分。 下游部分包括与内壁相对的外壁，以提供在内壁和外壁之间延伸的下游区域。 湍流促进剂从与下游部分中的弯曲部相邻的外壁延伸。 在与下游部分中的弯曲部相邻的内壁的停滞区域中不存在湍流促进剂

    GAS TURBINE ENGINE SERPENTINE COOLING PASSAGE
    4.
    发明公开
    GAS TURBINE ENGINE SERPENTINE COOLING PASSAGE 审中-公开
    燃气涡轮发动机SERPENTINE COOLING PASSAGE

    公开(公告)号：EP2895694A1

    公开(公告)日：2015-07-22

    申请号：EP13836460.9

    申请日：2013-09-05

    Applicant: United Technologies Corporation

    Inventor： PEREZ, Rafel A. ,  PIETRASZKIEWICZ, Edward F. ,  LEVINE, Jeffrey R. ,  MONGILLO JR., Dominic J.

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

    CPC classification number: F01D5/188 ,  F01D5/187 ,  F05D2250/183 ,  F05D2250/185 ,  F05D2260/2212 ,  F05D2260/22141 ,  F05D2270/17 ,  Y02T50/673 ,  Y02T50/676

    Abstract: A gas turbine engine component includes a structure having a cooling passage providing upstream and downstream portions separated from one another by an inner wall and fluidly connected by a bend. The downstream portion includes an outer wall opposite the inner wall to provide a downstream region extending between the inner and outer walls. A turbulence promoter extends from the outer wall adjacent to the bend in the downstream portion. The turbulence promoter is absent from a stagnation region adjoining the inner wall adjacent to the bend in the downstream portion

    Abstract translation: 燃气涡轮发动机部件包括具有冷却通道的结构，所述冷却通道提供通过内壁彼此分开并通过弯曲流体连接的上游部分和下游部分。 下游部分包括与内壁相对的外壁，以提供在内壁和外壁之间延伸的下游区域。 湍流促进剂从靠近下游部分弯曲处的外壁延伸。 邻近邻近下游部分弯曲处的内壁的停滞区中不存在湍流促进剂

    GAS TURBINE ENGINE COMPONENT COOLING WITH RESUPPLY OF COOLING PASSAGE
    6.
    发明公开
    GAS TURBINE ENGINE COMPONENT COOLING WITH RESUPPLY OF COOLING PASSAGE 审中-公开
    KÜHLUNGVON GASTURBINENMOTORKOMPONENTEN MITKÜHLKANALRÜCKFÜHRUNG

    公开(公告)号：EP3019704A1

    公开(公告)日：2016-05-18

    申请号：EP14823573.2

    申请日：2014-06-17

    Applicant: United Technologies Corporation

    Inventor： SPANGLER, Brandon W. ,  MONGILLO JR., Dominic J.

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

    CPC classification number: F01D5/187 ,  F01D9/041 ,  F01D11/08 ,  F01D25/12 ,  F05D2220/32 ,  F05D2230/00 ,  F05D2230/21 ,  F05D2240/81 ,  F05D2260/202 ,  F05D2260/204 ,  F05D2260/205 ,  Y02T50/676

    Abstract: A gas turbine engine component includes a structure having a wall that provides an exterior surface. A first cooling passage is arranged adjacent to and interiorly of the wall. A second cooling passage is arranged in the wall and provides a first fluid flow direction. A resupply channel is arranged in the wall and is fluidly interconnected to the second cooling passage. A resupply hole fluidly interconnects the first cooling passage and the resupply channel. The resupply channel is transverse relative to the second cooling passage to provide a second fluid flow direction that extends from the resupply hole to the second cooling passage.

    Abstract translation: 燃气涡轮发动机部件包括具有提供外表面的壁的结构。 第一冷却通道布置成与壁的内部和内部相邻。 第二冷却通道布置在壁中并提供第一流体流动方向。 补给通道布置在壁中并且流体地互连到第二冷却通道。 再补充孔将第一冷却通道和补给通道流体地相互连接。 补给通道相对于第二冷却通道是横向的，以提供从补给孔延伸到第二冷却通道的第二流体流动方向。

Patent Agency Ranking