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    STAGGERED CROSSOVERS FOR AIRFOILS
    16.
    发明申请
    STAGGERED CROSSOVERS FOR AIRFOILS 审中-公开

    公开(公告)号：US20160160657A1

    公开(公告)日：2016-06-09

    申请号：US14820786

    申请日：2015-08-07

    Applicant: United Technologies Corporation

    Inventor： Scott D. Lewis ,  Yafet Girma ,  Christopher Corcoran

    IPC: F01D5/18 ,  B22C9/10 ,  F01D25/12 ,  F01D5/14 ,  F01D9/04

    CPC classification number: F01D5/187 ,  B22C9/10 ,  F01D5/147 ,  F01D9/041 ,  F01D25/12 ,  F05D2220/32 ,  F05D2230/21 ,  F05D2230/211 ,  F05D2250/314 ,  F05D2260/201 ,  F05D2260/202 ,  Y02T50/672 ,  Y02T50/673 ,  Y02T50/676

    Abstract: An airfoil according to an exemplary aspect of the present disclosure includes, among other things, an airfoil section having an external wall and an internal wall. The internal wall defines a first reference plane extending in a spanwise direction and through a thickness of the internal wall. A first cavity and a second cavity are separated by the internal wall. A plurality of crossover passages within the internal wall connects the first cavity to the second cavity. Each of the plurality of crossover passages defines a passage axis. The plurality of crossover passages are distributed in the spanwise direction and arranged such that the passage axis of each of the plurality of cooling passages intersects a surface of the second cavity. The plurality of crossover passages include a first set of crossover passages and a second set of crossover passages positioned on opposite sides of the first reference plane. The passage axis of each of the first set of crossover passages is arranged at a first vertical angle relative to a spanwise axis, and the passage axis of each of the second set of crossover passages is arranged at a second, different vertical angle relative to the spanwise axis. A casting core for an airfoil is also disclosed.

    Abstract translation: 根据本公开的示例性方面的翼型件尤其包括具有外壁和内壁的翼型部分。 内壁限定在翼展方向上延伸并穿过内壁的厚度的第一参考平面。 第一腔和第二腔由内壁分开。 内壁内的多个交叉通道将第一腔连接到第二腔。 多个交叉通道中的每一个限定通道轴线。 多个交叉通道沿翼展方向分布，并且布置成使得多个冷却通道中的每一个的通道轴线与第二腔体的表面相交。 多个交叉通道包括第一组交叉通道和位于第一参考平面的相对侧上的第二组交叉通道。 第一组交叉通道中的每一个的通道轴线相对于翼展方向轴线以第一垂直角度布置，并且第二组交叉通道中的每一个的通道轴线相对于第二组交叉通道布置成第二不同的垂直角度 翼展轴。 还公开了一种用于翼型的铸芯。

    ROTOR BLADE WITH L-SHAPED FEATHER SEAL
    17.
    发明申请
    ROTOR BLADE WITH L-SHAPED FEATHER SEAL 审中-公开
    带有L形羽毛密封的转子刀片

    公开(公告)号：US20160061048A1

    公开(公告)日：2016-03-03

    申请号：US14779841

    申请日：2014-03-24

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Christopher Corcoran ,  Anthony P. Cherolis

    IPC: F01D11/00 ,  F01D5/14 ,  F01D15/12 ,  F01D5/02

    CPC classification number: F01D11/008 ,  F01D5/02 ,  F01D5/147 ,  F01D11/006 ,  F01D15/12 ,  F05D2220/30 ,  F05D2240/30 ,  F05D2240/55 ,  F05D2250/71 ,  F05D2250/75 ,  F05D2260/97

    Abstract: A turbine engine assembly arranged relative to an axis includes a rotor blade and a feather seal with an L-shaped geometry. The rotor blade includes an airfoil and a base. The airfoil extends axially between an upstream leading edge and a downstream trailing edge, and radially out from the base. The base includes a neck and a pocket. The neck extends axially to a downstream surface. The pocket extends laterally into the neck. The feather seal extends laterally into the pocket, and includes a down stream leg that extends substantially along the downstream surface.

    Abstract translation: 相对于轴线布置的涡轮发动机组件包括转子叶片和具有L形几何形状的羽毛密封件。 转子叶片包括翼型件和底座。 翼型件在上游前缘和下游后缘之间轴向延伸，并从底座径向延伸。 底座包括一个颈部和一个口袋。 颈部轴向延伸到下游表面。 口袋横向延伸到颈部。 羽毛密封件横向延伸到袋中，并且包括基本上沿着下游表面延伸的下游腿。

    AIRFOIL PLATFORM IMPINGEMENT COOLING HOLES
    18.
    发明申请
    AIRFOIL PLATFORM IMPINGEMENT COOLING HOLES 审中-公开
    AIRFOIL平台打击球

    公开(公告)号：US20160017720A1

    公开(公告)日：2016-01-21

    申请号：US14802459

    申请日：2015-07-17

    Applicant: United Technologies Corporation

    Inventor： Scott D. Lewis ,  Christopher Corcoran

    IPC: F01D5/18

    CPC classification number: F01D5/187 ,  F01D5/186 ,  F05D2240/81 ,  F05D2260/201 ,  Y02T50/676

    Abstract: An airfoil structure for a gas turbine engine includes an airfoil which includes a leading edge and a trailing edge. A platform is located adjacent a first end of the airfoil and includes a core passage that extends through the platform, a mate-face for engaging an adjacent airfoil structure and a set of impingement cooling holes in communication with the core passage that extend through the mate-face adjacent the trialing edge of the airfoil.

    Abstract translation: 用于燃气涡轮发动机的翼型结构包括包括前缘和后缘的翼型件。 平台位于翼型件的第一端附近并且包括延伸穿过平台的芯通道，用于接合相邻翼型结构的配合面和与芯通道连通的一组冲击冷却孔，所述冲击冷却孔延伸穿过配合 表面相邻翼型的试验边缘。

    DAMPER PIN
    19.
    发明申请
    DAMPER PIN 审中-公开
    阻尼针

    公开(公告)号：US20140112792A1

    公开(公告)日：2014-04-24

    申请号：US14143828

    申请日：2013-12-30

    Applicant: United Technologies Corporation

    Inventor： Seth J. Thomen ,  Christopher Corcoran

    IPC: F01D5/22 ,  F01D11/00

    CPC classification number: F01D5/22 ,  F01D11/006 ,  F01D11/008 ,  F05D2250/25 ,  Y10S416/50

    Abstract: A damper pin for coupling platforms of adjacent turbine blades includes a first flat longitudinal end region, a second flat longitudinal end region and a reduced cross sectional area. The reduced cross sectional area is separated from the first flat longitudinal end region by a first main body region and the reduced cross sectional area is separated from the second flat longitudinal end region by a second main body region. The cross sectional area of the reduced cross sectional area is less than the cross sectional area of each of the first and second main body regions.

    Abstract translation: 用于联接相邻涡轮机叶片的平台的减震器销包括第一平坦纵向端部区域，第二平坦纵向端部区域和减小的横截面面积。 减小的横截面积由第一主体区域与第一平坦纵向端部区域分离，并且减小的横截面面积与第二平坦纵向端部区域通过第二主体区域分离。 横截面积减小的截面积小于第一和第二主体区域的横截面面积。

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