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    STAGGERED CROSSOVERS FOR AIRFOILS
    32.
    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。

    AIRFOIL PLATFORM IMPINGEMENT COOLING HOLES
    33.
    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。

    OBLONG PURGE HOLES
    37.
    发明申请
    OBLONG PURGE HOLES 审中-公开

    公开(公告)号：US20180347379A1

    公开(公告)日：2018-12-06

    申请号：US15613923

    申请日：2017-06-05

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Scott D. Lewis

    IPC: F01D5/20 ,  F01D5/14 ,  F01D5/18

    Abstract: A turbine blade may comprise a pressure side wall and a suction side wall opposite the pressure side wall. A tip wall may extend between the pressure side wall and the suction side wall and may comprise a first opening. A first dimension of the first opening may be greater than a second dimension of the first opening. The first dimension may be oriented in a direction extending from a leading edge of the turbine blade toward a trailing edge of the turbine blade.

    Showerhead hole scheme apparatus and system
    39.
    发明授权
    Showerhead hole scheme apparatus and system 有权

    公开(公告)号：US10041356B2

    公开(公告)日：2018-08-07

    申请号：US14733686

    申请日：2015-06-08

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Scott D. Lewis

    IPC: F01D9/04 ,  F01D5/18 ,  F01D25/12

    Abstract: The gas turbine component showerhead cooling hole layouts described herein include minimal lateral cooling hole exit diffusion on the middle showerhead cooling hole rows and interior facing sides of outer rows. In this way, rows of cooling holes may be placed close together. Stated another way, the outer showerhead cooling hole rows substantially only include lateral cooling hole exit diffusion in the direction away from the other rows to again allow the rows to be placed close together.

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