中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

8 records (took 0.026 seconds)

    THREADED FULL RING INNER AIR-SEAL
    1.
    发明申请
    THREADED FULL RING INNER AIR-SEAL 审中-公开
    螺纹内圈空气密封

    公开(公告)号：WO2014058505A2

    公开(公告)日：2014-04-17

    申请号：PCT/US2013051584

    申请日：2013-07-23

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： HAGAN BENJAMIN F ,  CAPRARIO JOSEPH T

    IPC: F01D11/08 ,  F01D5/20 ,  F02C7/28

    CPC classification number: F01D11/001 ,  F01D9/065 ,  F01D11/02 ,  F05D2240/11

    Abstract: A disclosed vane assembly includes a vane section formed of a plurality of circumferentially spaced fixed vanes. The vanes extend radially outward from an inner platform and hooked into case. The inner platform includes a mount rail extending radially inwardly from the inner platform. An air seal is attached to the inner platform of the vane section and includes a ring extending circumferentially about the axis. The disclosed air seal includes a plurality of tabs that receive lugs disposed on the mount rail. A ring nut is secured to the air seal and engaged to the mount rail for securing the vane section to the air seal.

    Abstract translation: 公开的叶片组件包括由多个周向间隔开的固定叶片形成的叶片部分。 叶片从内平台径向向外延伸并钩入壳体。 内平台包括从内平台径向向内延伸的安装轨道。 空气密封件附接到叶片部分的内平台，并且包括围绕轴线周向延伸的环。 所公开的空气密封件包括接纳设置在安装轨道上的凸耳的多个凸片。 环形螺母被固定到空气密封件并且接合到安装轨道以将叶片部分固定到空气密封件。

    COOLING SYSTEM FOR A TURBINE VANE
    2.
    发明专利
    COOLING SYSTEM FOR A TURBINE VANE 未知

    公开(公告)号：SG11201404364TA

    公开(公告)日：2014-10-30

    申请号：SG11201404364T

    申请日：2013-03-25

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： PAPPLE MICHAEL ,  ENNACER MOHAMMED ,  DABBS THURMAN CARLO ,  LUTJEN PAUL M ,  CAPRARIO JOSEPH T ,  BERGMAN RUSSELL J ,  GREGG SHAWN J

    IPC: F01D25/08 ,  F01D5/18 ,  F01D9/06 ,  F02C7/12

    Abstract: A cooling system for a gas turbine engine includes a first plenum, a first cooling flow passageway, and a second cooling flow passageway. The first cooling flow passageway is in fluid communication with the first plenum and with a first airfoil cooling channel within an airfoil of the stator vane. The first airfoil cooling channel is for cooling a leading edge of the airfoil. The second cooling flow passageway is in fluid communication with the first plenum and with a platform cooling channel within an outer diameter platform of the stator vane. The first cooling flow passageway and the second cooling flow passageway are disposed within a mounting hook. The first cooling flow passageway and the second cooling flow passageway are not in fluid communication with each other.

    COOLING SYSTEM FOR A TURBINE VANE
    3.
    发明公开
    COOLING SYSTEM FOR A TURBINE VANE 审中-公开
    KÜHLSYSTEMFÜREINE TURBINENSCHAUFEL

    公开(公告)号：EP2834498A4

    公开(公告)日：2016-07-06

    申请号：EP13772338

    申请日：2013-03-25

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： BERGMAN RUSSELL J ,  GREGG SHAWN J ,  PAPPLE MICHAEL ,  LUTJEN PAUL M ,  CAPRARIO JOSEPH T ,  ENNACER MOHAMMED ,  DABBS THURMAN CARLO

    IPC: F02C7/12 ,  F01D5/18 ,  F01D25/08 ,  F01D25/14 ,  F01D25/24

    CPC classification number: F01D25/246 ,  F01D25/14 ,  F05D2240/81

    Abstract: A cooling system for a gas turbine engine includes a first plenum, a first cooling flow passageway, and a second cooling flow passageway. The first cooling flow passageway is in fluid communication with the first plenum and with a first airfoil cooling channel within an airfoil of the stator vane. The first airfoil cooling channel is for cooling a leading edge of the airfoil. The second cooling flow passageway is in fluid communication with the first plenum and with a platform cooling channel within an outer diameter platform of the stator vane. The first cooling flow passageway and the second cooling flow passageway are disposed within a mounting hook. The first cooling flow passageway and the second cooling flow passageway are not in fluid communication with each other.

    Abstract translation: 用于燃气涡轮发动机的冷却系统包括第一增压室，第一冷却流通道和第二冷却流通道。 第一冷却流通道与第一增压室流体连通，并且与定子叶片的翼型内的第一翼型冷却通道形成流体连通。 第一翼型冷却通道用于冷却翼型件的前缘。 第二冷却流通道与第一集气室流体连通，并且在定子叶片的外径平台内具有平台冷却通道。 第一冷却流通道和第二冷却流通道设置在安装钩内。 第一冷却流路和第二冷却流路不相互流体连通。

    THREADED FULL RING INNER AIR-SEAL
    5.
    发明公开
    THREADED FULL RING INNER AIR-SEAL 有权
    VOLLGEWINDERINGFÜREINE LUFTINNENDICHTUNG

    公开(公告)号：EP2885507A4

    公开(公告)日：2015-10-07

    申请号：EP13845065

    申请日：2013-07-23

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： HAGAN BENJAMIN F ,  CAPRARIO JOSEPH T

    IPC: F01D11/08 ,  F01D5/20 ,  F01D11/02 ,  F02C7/28

    CPC classification number: F01D11/001 ,  F01D9/065 ,  F01D11/02 ,  F05D2240/11

    Abstract: A disclosed vane assembly includes a vane section formed of a plurality of circumferentially spaced fixed vanes. The vanes extend radially outward from an inner platform and hooked into case. The inner platform includes a mount rail extending radially inwardly from the inner platform. An air seal is attached to the inner platform of the vane section and includes a ring extending circumferentially about the axis. The disclosed air seal includes a plurality of tabs that receive lugs disposed on the mount rail. A ring nut is secured to the air seal and engaged to the mount rail for securing the vane section to the air seal.

    Abstract translation: 公开的叶片组件包括由多个周向间隔开的固定叶片形成的叶片部分。 叶片从内平台径向向外延伸并钩在壳体内。 内平台包括从内平台径向向内延伸的安装轨道。 空气密封件附接到叶片部分的内平台，并且包括围绕轴线周向延伸的环。 所公开的空气密封件包括接收设置在安装轨道上的凸耳的多个凸片。 环形螺母固定到空气密封件上并与安装轨道接合，用于将叶片部分固定到空气密封。

    GAS TURBINE ENGINE INCLUDING A PRE-DIFFUSER HEAT EXCHANGER
    6.
    发明公开
    GAS TURBINE ENGINE INCLUDING A PRE-DIFFUSER HEAT EXCHANGER 审中-公开
    燃气轮机与VORDIFFUSOR热交换

    公开(公告)号：EP2935833A4

    公开(公告)日：2016-08-03

    申请号：EP13863795

    申请日：2013-12-18

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： CAPRARIO JOSEPH T ,  GREGG SHAWN J ,  HYLAND DAVE J

    IPC: F02C7/12 ,  F01D9/06 ,  F01D25/12 ,  F02K3/00

    CPC classification number: F01D9/065 ,  F05D2260/22141 ,  Y02T50/676

    Abstract: According to an example embodiment, a gas turbine engine assembly includes, among other things, a compressor. A strut near the compressor includes a flow passage through a portion of the strut. The flow passage is configured to direct air from the compressor to another portion of the gas turbine engine. The flow passage has at least one surface feature that at least partially hinders some airflow through the flow passage.

    Abstract translation: 根据示例性实施例，燃气涡轮发动机组件尤其包括压缩机。 压缩机附近的支柱包括通过支柱的一部分的流动通道。 流动通道构造成将空气从压缩机引导到燃气涡轮发动机的另一部分。 流动通道具有至少部分地阻碍通过流动通道的一些气流的至少一个表面特征。

Patent Agency Ranking