2.
    发明专利
    未知

    公开(公告)号:DE602005008311D1

    公开(公告)日:2008-09-04

    申请号:DE602005008311

    申请日:2005-05-27

    Abstract: A rotor blade (14) is provided that includes a root (20) and a hollow airfoil (22). The hollow airfoil (22) has a cavity defined by a suction side wall (38), a pressure side wall (36), a leading edge (32), a trailing edge (34), a base (28), and a tip (30). An internal passage configuration (40) is disposed within the cavity. The configuration includes a passage (50) disposed adjacent the leading edge (32), and an axially extending passage (52) disposed adjacent the tip (30). The first passage (50) is connected to the second passage (52). The second passage (52) includes an opening disposed at the trailing edge (34) of the airfoil. A conduit (42) is disposed within the root (20) that is operable to permit airflow through the root (20) and into the leading edge passage (50), wherein the conduit (42) provides the primary path into the leading edge passage (42).

    IMPROVED COOLING FOR A TURBINE AIRFOIL TRAILING EDGE
    4.
    发明申请
    IMPROVED COOLING FOR A TURBINE AIRFOIL TRAILING EDGE 审中-公开
    改进的冷却涡轮机空运货物边缘

    公开(公告)号:WO2014007889A2

    公开(公告)日:2014-01-09

    申请号:PCT/US2013034220

    申请日:2013-03-28

    Abstract: An assembly for a gas turbine engine includes a first platform and an airfoil extending from the first platform. The airfoil includes a first fillet, pressure side biased discharge openings, and a first center cooling discharge opening. A pressure side wall of the airfoil and the first platform form an acute angle at the trailing edge. The first fillet is formed around a perimeter of the airfoil where the airfoil extends from the first platform. The pressure side biased cooling discharge openings are along the trailing edge outside of the first fillet. Each pressure side biased cooling discharge opening extends from the trailing edge along the pressure side wall. The first center cooling discharge opening extends along the trailing edge into the first fillet and is centrally located between the pressure side wall and the suction side wall.

    Abstract translation: 一种用于燃气涡轮发动机的组件包括第一平台和从第一平台延伸的翼型件。 翼型件包括第一圆角,压力侧偏压排出口和第一中心冷却排出口。 翼型件的压力侧壁和第一平台在后缘处形成锐角。 第一圆角围绕机翼的周边形成,其中翼型件从第一平台延伸。 压力侧偏压的冷却排出口沿着第一圆角外侧的后缘。 每个压力侧偏压的冷却排放口从后缘沿压力侧壁延伸。 第一中心冷却排出口沿着后缘延伸​​到第一圆角中并且位于压力侧壁和吸力侧壁之间的中心。

    TAPERED THERMAL BARRIER COATING ON CONVEX AND CONCAVE TRAILING EDGE SURFACES
    5.
    发明申请
    TAPERED THERMAL BARRIER COATING ON CONVEX AND CONCAVE TRAILING EDGE SURFACES 审中-公开
    锥形热障涂层和凹凸边缘表面

    公开(公告)号:WO2014143360A3

    公开(公告)日:2014-11-06

    申请号:PCT/US2013078179

    申请日:2013-12-30

    Inventor: LEVINE JEFFREY R

    Abstract: A turbine engine component has an airfoil portion having a pressure side, a suction side, and a trailing edge. The trailing edge has a center discharge cooling circuit, which center discharge cooling circuit has an exit defined by a concave surface on the pressure side of the airfoil portion and a convex surface on the suction side of the airfoil portion. The airfoil portion has a thermal barrier coating on the pressure side and the suction side. The thermal barrier coating on the convex surface tapers to zero in thickness at a point spaced from the trailing edge so as to leave an uncoated portion on the convex surface.

    Abstract translation: 涡轮发动机部件具有具有压力侧,吸力侧和后缘的翼型部。 后缘具有中心排出冷却回路,中心排出冷却回路具有由翼型部的压力侧的凹面界定的出口和翼型部的吸入侧的凸面。 翼型部分在压力侧和吸力侧具有热障涂层。 凸表面上的热障涂层在与后缘间隔开的位置处的厚度变薄到零,以便在凸面上留下未涂覆的部分。

    TAPERED THERMAL COATING FOR AIRFOIL
    6.
    发明申请
    TAPERED THERMAL COATING FOR AIRFOIL 审中-公开
    用于气流的热转印热涂层

    公开(公告)号:WO2013172903A3

    公开(公告)日:2014-01-09

    申请号:PCT/US2013027232

    申请日:2013-02-22

    CPC classification number: F01D5/188 Y02T50/676

    Abstract: An airfoil comprises pressure and suction surfaces extending axially from a leading edge to a trailing edge and radially from a root section to a tip section, the root section and the tip section defining a span therebetween. A thermal coating extends from the root section of the airfoil toward the tip section of the airfoil. A relative coating thickness of the thermal coating decreases by at least thirty percent at full span in the tip section, as compared to minimum span in the root section.

    Abstract translation: 翼型件包括从前缘到后缘轴向延伸的压力和抽吸表面,并且从根部到尖端部分径向延伸,根部和末端部分限定了它们之间的跨度。 热涂层从翼型的根部朝向翼型的末端部分延伸。 与根部中的最小跨度相比,热涂层的相对涂层厚度在末端部分的全跨度处降低至少30%。

    TAPERED THERMAL BARRIER COATING ON CONVEX AND CONCAVE TRAILING EDGE SURFACES
    9.
    发明公开
    TAPERED THERMAL BARRIER COATING ON CONVEX AND CONCAVE TRAILING EDGE SURFACES 审中-公开
    康奈尔·肯尼亚·肯尼亚·弗朗西斯科

    公开(公告)号:EP2956623A4

    公开(公告)日:2016-03-16

    申请号:EP13877747

    申请日:2013-12-30

    Inventor: LEVINE JEFFREY R

    Abstract: A turbine engine component has an airfoil portion having a pressure side, a suction side, and a trailing edge. The trailing edge has a center discharge cooling circuit, which center discharge cooling circuit has an exit defined by a concave surface on the pressure side of the airfoil portion and a convex surface on the suction side of the airfoil portion. The airfoil portion has a thermal barrier coating on the pressure side and the suction side. The thermal barrier coating on the convex surface tapers to zero in thickness at a point spaced from the trailing edge so as to leave an uncoated portion on the convex surface.

    Abstract translation: 涡轮发动机部件具有具有压力侧,吸力侧和后缘的翼型部。 后缘具有中心排出冷却回路,其中心排出冷却回路具有由翼型部的压力侧的凹面界定的出口和翼型部的吸入侧的凸面。 翼型部分在压力侧和吸力侧具有热障涂层。 凸表面上的隔热涂层在与后缘间隔开的位置处的厚度变薄到零,以便在凸面上留下未涂覆的部分。

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