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    ROTATING TURBINE COMPONENT WITH PREFERENTIAL HOLE ALIGNMENT
    11.
    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
    12.
    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 BLADE
    13.
    发明申请
    TURBINE BLADE 有权

    公开(公告)号：US20210270139A1

    公开(公告)日：2021-09-02

    申请号：US17324660

    申请日：2021-05-19

    Applicant: General Electric Company

    Inventor： Matthew Lee Krumanaker ,  Weston Nolan Dooley ,  Steven Robert Brassfield

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

    Abstract: An airfoil for a gas turbine engine can include an outer surface defining a pressure side and a suction side extending axially between a leading edge and a trailing edge and extending radially between a first end and a second end to define a span-wise direction, and a cooling circuit located within the airfoil. The cooling circuit can include a cooling air inlet passage, a radially extending supply passage, an upstream supply passage fluidly coupling the cooling air inlet passage and the supply passage, and a near wall cooling mesh extending along a portion of the outer surface.

    Engine component with cooling hole
    16.
    发明授权
    Engine component with cooling hole 有权

    公开(公告)号：US10648342B2

    公开(公告)日：2020-05-12

    申请号：US15844684

    申请日：2017-12-18

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Zachary Daniel Webster ,  Aaron Ezekiel Smith ,  Steven Robert Brassfield

    IPC: F01D5/18 ,  F01D5/14 ,  F23R3/00

    Abstract: An apparatus and method an airfoil for a turbine engine, the airfoil comprising an outer wall defining an interior bound by a pressure side and a suction side extending axially between a leading edge and a trailing edge defining a chord-wise direction and extending radially between a root and a tip defining a span-wise direction. The airfoil further includes at least one cooling hole including a diffusing section and fluidly coupling an exterior of the engine component to an exterior of the engine component.

    TURBINE BLADE
    18.
    发明申请
    TURBINE BLADE 审中-公开

    公开(公告)号：US20200024969A1

    公开(公告)日：2020-01-23

    申请号：US16214411

    申请日：2018-12-10

    Applicant: General Electric Company

    Inventor： Matthew Lee Krumanaker ,  Weston Nolan Dooley ,  Steven Robert Brassfield

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

    Abstract: An airfoil comprises one or more internal cooling circuits. The cooling circuit can further comprise a near wall cooling mesh, fluidly coupling a supply passage to a mesh plenum. The mesh plenum can be disposed adjacent to the external surface of the airfoil having a plurality of film holes extending between the mesh plenum and the external surface of the airfoil. The mesh plenum can further comprise a cross-sectional area sized to facilitate machining of the film holes without damage to the interior of the airfoil.

    ENGINE COMPONENT WITH COOLING HOLE
    19.
    发明申请
    ENGINE COMPONENT WITH COOLING HOLE 审中-公开

    公开(公告)号：US20190257206A1

    公开(公告)日：2019-08-22

    申请号：US15898703

    申请日：2018-02-19

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Zachary Daniel Webster ,  Gregory Terrence Garay ,  Steven Robert Brassfield

    IPC: F01D5/18

    Abstract: An apparatus and method an engine component for a turbine engine comprising an outer wall bounding an interior and defining a pressure side and an opposing suction side, with both sides extending between a leading edge and a trailing edge to define a chord-wise direction, and extending between a root and a tip to define a span-wise direction, at least one cooling passage located within the interior, at least one cooling hole having an inlet fluidly coupled to the cooling passage and an outlet located along the outer wall.

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