中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

45 records (took 0.01 seconds)

    GAS TURBINE ENGINE AIRFOIL WITH LEADING EDGE TRENCH AND IMPINGEMENT COOLING
    2.
    发明申请
    GAS TURBINE ENGINE AIRFOIL WITH LEADING EDGE TRENCH AND IMPINGEMENT COOLING 审中-公开
    气体涡轮发动机气动翼片，带有边缘倾斜和冲击冷却

    公开(公告)号：WO2015112225A3

    公开(公告)日：2015-09-24

    申请号：PCT/US2014064018

    申请日：2014-11-05

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SLAVENS THOMAS N ,  SNYDER BROOKS E

    IPC: F01D5/18

    CPC classification number: F01D5/187 ,  F01D5/18 ,  F01D5/186 ,  F01D9/02 ,  F01D25/12 ,  F05D2220/32 ,  F05D2230/31 ,  F05D2260/20 ,  F05D2260/201 ,  F05D2260/202 ,  Y02T50/673 ,  Y02T50/676

    Abstract: A gas turbine engine airfoil includes an airfoil structure including an exterior surface that is provided by an exterior wall that has a leading edge. A radially extending interior wall within the airfoil structure separates first and second radial cooling passages. The first cooling passage is arranged near the leading edge. A radially extending trench is in the leading edge. An impingement hole is provided in the interior wall and is configured to direct a cooling fluid from the second cooling passage to the first cooling passage and onto the exterior wall at the leading edge.

    Abstract translation: 燃气涡轮发动机翼型件包括翼型结构，其包括由具有前缘的外壁提供的外表面。 翼型结构内的径向延伸的内壁分隔第一和第二径向冷却通道。 第一个冷却通道设置在前缘附近。 径向延伸的沟槽位于前缘。 冲击孔设置在内壁中并且构造成将冷却流体从第二冷却通道引导到第一冷却通道并且在前缘处引导到外壁上。

    GAS TURBINE ENGINE TURBINE BLADE TIP COOLING
    4.
    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。

    CENTRIFUGAL AIRFOIL COOLING MODULATION
    5.
    发明申请
    CENTRIFUGAL AIRFOIL COOLING MODULATION 审中-公开
    离心式空气冷却调节

    公开(公告)号：WO2015112268A2

    公开(公告)日：2015-07-30

    申请号：PCT/US2014069128

    申请日：2014-12-08

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： THORNTON LANE ,  SLAVENS THOMAS N

    IPC: F01D5/18

    CPC classification number: F01D5/186 ,  F01D5/187 ,  F01D5/28 ,  F02C3/04 ,  F02C7/12 ,  F05D2220/32 ,  F05D2240/303 ,  F05D2240/304 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2300/175 ,  F05D2300/505 ,  Y02T50/676

    Abstract: In one example embodiment, a blade includes an attachment region, an airfoil extending from the attachment region, and a blade cooling arrangement. The blade cooling arrangement includes at least a first feed passage disposed through the attachment region, which is connected to a first cooling passage disposed in the airfoil. A passively actuated first coolant valve is disposed in or proximate the first feed passage. A plurality of such blades can be disposed in a turbine section of an engine.

    Abstract translation: 在一个示例性实施例中，叶片包括附接区域，从连接区域延伸的翼型件和叶片冷却装置。 叶片冷却装置包括至少一个穿过安装区域设置的第一进料通道，其连接到设置在翼型件中的第一冷却通道。 被动地驱动的第一冷却剂阀设置在第一进料通道中或其附近。 多个这样的叶片可以设置在发动机的涡轮机部分中。

Patent Agency Ranking