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    ROTATING TURBINE COMPONENT WITH PREFERENTIAL HOLE ALIGNMENT
    1.
    发明申请
    ROTATING TURBINE COMPONENT WITH PREFERENTIAL HOLE ALIGNMENT 有权
    旋转涡轮组件与优选孔对齐

    公开(公告)号：US20150226069A1

    公开(公告)日：2015-08-13

    申请号：US14418626

    申请日：2013-07-30

    Applicant: General Electric Company

    Inventor： Shawn Michael Pearson ,  Steven Robert Brassfield ,  Stephen Mark Molter ,  Mark Edward Stegemiller ,  Nicholas Ertel ,  Vanessa Camarillo

    IPC: F01D5/18 ,  B23P15/04

    CPC classification number: F01D5/185 ,  B23P15/04 ,  F01D5/147 ,  F01D5/187 ,  F05D2250/14 ,  Y10T29/49316 ,  Y10T29/49321

    Abstract: A turbine airfoil includes: a concave pressure sidewall and a convex suction sidewall joined together at a leading edge and a trailing edge, and extending between a root and a tip; an internal rib extending between the pressure sidewall and the suction sidewall; and a crossover hole formed in the rib, the crossover hole having a noncircular cross-sectional shape with a major axis defining a maximum dimension of the cross-sectional shape; wherein the major axis of the crossover hole lies in plane with the rib and is non-parallel to an imaginary curvilinear lateral centerline which defines a locus of points lying halfway between the pressure and suction sidewalls. The orientation of the crossover holes minimizes stress concentration caused by the presence of the crossover holes.

    Abstract translation: 涡轮机翼片包括：在前缘和后缘处连接在一起并且在根部和尖端之间延伸的凹形压力侧壁和凸形抽吸侧壁; 在所述压力侧壁和所述吸力侧壁之间延伸的内部肋; 以及形成在所述肋中的交叉孔，所述交叉孔具有非圆形横截面形状，所述横截面形状具有限定所述横截面形状的最大尺寸的长轴; 其中所述交叉孔的长轴位于与所述肋的平面中，并且不平行于限定位于所述压力和抽吸侧壁之间的中心位置的虚拟曲线横向中心线。 交叉孔的方向最小化由交叉孔的存在引起的应力集中。

    METHODS AND APPARATUS FOR SEALING A GAS TURBINE ENGINE ROTOR ASSEMBLY
    2.
    发明申请
    METHODS AND APPARATUS FOR SEALING A GAS TURBINE ENGINE ROTOR ASSEMBLY 有权
    密封涡轮发动机转子总成的方法和装置

    公开(公告)号：US20150167480A1

    公开(公告)日：2015-06-18

    申请号：US14407867

    申请日：2013-06-14

    Applicant: General Electric Company

    Inventor： Shawn Michael Pearson ,  Steven Robert Brassfield ,  Mark Edward Stegemiller ,  Jonathan Filipa ,  Daniel Lee Durstock

    IPC: F01D5/30 ,  F01D11/00

    CPC classification number: F01D5/30 ,  F01D5/22 ,  F01D5/3015 ,  F01D11/00 ,  F01D11/006 ,  F05D2240/57 ,  Y10T29/49321

    Abstract: A rotor assembly for use in a gas turbine engine having an axis of rotation includes a plurality of rotor blades. Each rotor blade includes a platform extending between opposing side faces, a shank extending radially inward from the platform, and a slot at least partially defined in each of the opposing side faces. A sealing member is configured to be inserted into each slot of a first rotor blade of the plurality of rotor blades such that at least a portion of each sealing member extends beyond one of the opposing side faces. A second rotor blade of the plurality of rotor blades is coupled adjacent the first rotor blade such that at least a portion of one sealing member is inserted into a corresponding second slot on the second rotor blade.

    Abstract translation: 用于具有旋转轴线的燃气涡轮发动机中的转子组件包括多个转子叶片。 每个转子叶片包括在相对侧面之间延伸的平台，从平台径向向内延伸的杆，以及至少部分限定在每个相对侧面中的狭槽。 密封构件被配置为插入到多个转子叶片中的第一转子叶片的每个槽中，使得每个密封构件的至少一部分延伸超过相对侧面之一。 多个转子叶片中的第二转子叶片与第一转子叶片相邻地连接，使得一个密封构件的至少一部分插入到第二转子叶片上相应的第二槽中。

    TURBINE AIRFOIL WITH CAST PLATFORM COOLING CIRCUIT
    4.
    发明申请
    TURBINE AIRFOIL WITH CAST PLATFORM COOLING CIRCUIT 审中-公开
    具有铸铁平台冷却电路的涡轮机空气

    公开(公告)号：US20150152735A1

    公开(公告)日：2015-06-04

    申请号：US14406018

    申请日：2013-06-17

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Stephen Mark Molter ,  Mark Edward Stegemiller ,  Shawn Michael Pearson ,  Steven Robert Brassfield

    IPC: F01D5/18 ,  B23P15/02 ,  F01D5/20

    CPC classification number: F01D5/186 ,  B23P15/02 ,  F01D5/187 ,  F01D5/20 ,  F01D5/225 ,  F01D9/041 ,  F05D2220/32 ,  F05D2230/10 ,  F05D2230/21 ,  F05D2240/81 ,  F05D2260/202 ,  Y10T29/49341

    Abstract: A turbine airfoil apparatus includes: an airfoil including a concave pressure sidewall and a convex suction sidewall joined together at a leading edge and a trailing edge; an endwall projecting laterally outwardly from the airfoil at one spanwise end thereof, the endwall having an outer surface facing the airfoil and an opposing inner surface; a plenum defined within the endwall between the inner and outer surfaces wherein the plenum is forked in plan view, with at least two branches, each branch having a throat disposed at its upstream end; and at least one film cooling hole passing through the outer surface and communicating with the plenum.

    Abstract translation: 涡轮机翼型装置包括：在前缘和后缘处连接在一起的包括凹压侧壁和凸吸吸侧壁的翼型件; 所述端壁在所述翼型件的一个翼展端处从所述翼型件横向向外突出，所述端壁具有面向所述翼型件的外表面和相对的内表面; 限定在内表面和外表面之间的端壁内的气室，其中气室在平面图中分叉，至少两个分支，每个分支具有设置在其上游端的喉部; 以及至少一个通过外表面并与气室连通的薄膜冷却孔。

    TURBINE AIRFOIL WITH LOCAL WALL THICKNESS CONTROL
    9.
    发明申请
    TURBINE AIRFOIL WITH LOCAL WALL THICKNESS CONTROL 有权
    具有局部壁厚控制的涡轮机空气

    公开(公告)号：US20150152734A1

    公开(公告)日：2015-06-04

    申请号：US14396062

    申请日：2013-04-23

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Christopher Michael Ceglio ,  Randall Charles Bauer ,  Stephen Mark Molter ,  Mark Edward Stegemiller

    IPC: F01D5/18

    CPC classification number: F01D5/186 ,  F01D5/187 ,  F05D2250/292 ,  F05D2260/202

    Abstract: A turbine airfoil for a gas turbine engine including an outer peripheral wall having an external surface, the outer peripheral wall enclosing an interior space and including a concave pressure sidewall and a convex suction sidewall joined together at a leading edge and at a trailing edge; wherein the outer peripheral wall has a varying wall thickness which incorporates a locally-thickened wall portion; and a film cooling hole having a shaped diffuser exit passing through the outer peripheral wall within the locally-thickened wall portion.

    Abstract translation: 一种用于燃气涡轮发动机的涡轮机翼片，其包括具有外表面的外周壁，所述外周壁包围内部空间，并且包括在前缘和后缘处连接在一起的凹形压力侧壁和凸形抽吸侧壁; 其中所述外周壁具有变化的壁厚，其包含局部增厚的壁部分; 以及膜冷却孔，其具有穿过局部加厚的壁部分中的外周壁的成形扩散器出口。

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