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    Interior configuration for turbine rotor blade
    2.
    发明授权
    Interior configuration for turbine rotor blade 有权
    涡轮转子叶片的内部结构

    公开(公告)号：US09376922B2

    公开(公告)日：2016-06-28

    申请号：US13737031

    申请日：2013-01-09

    Applicant: General Electric Company

    Inventor： Harish Bommanakatte ,  Jalindar Appa Walunj ,  Anthony Louis Giglio ,  Jason Douglas Herzlinger

    IPC: F01D5/08 ,  F01D5/18

    CPC classification number: F01D5/189 ,  F01D5/187 ,  F05D2240/303 ,  F05D2260/201 ,  Y02T50/672 ,  Y02T50/673 ,  Y02T50/676

    Abstract: An interior cooling configuration formed within an airfoil of a blade of a combustion turbine engine is provided. The interior cooling configuration may include a first flow passage and a second flow passage that have a side-by-side configuration for a segment, and multiple lateral crossover passages extending between and fluidly connecting the first flow passage to the second flow passage. The crossover passages may be staggered.

    Abstract translation: 提供了形成在燃气涡轮发动机的叶片的翼型内的内部冷却构造。 内部冷却构造可以包括具有用于段的并排构造的第一流动通道和第二流动通道，以及在第一流动通道和第二流动通道之间延伸并且将流体连接到第二流动通道的多个横向跨接通道。 交叉通道可能交错。

    Airfoil shape for a turbine rotor blade
    4.
    发明授权
    Airfoil shape for a turbine rotor blade 有权

    公开(公告)号：US10247007B2

    公开(公告)日：2019-04-02

    申请号：US15584443

    申请日：2017-05-02

    Applicant: General Electric Company

    Inventor： Neil Ristau ,  Mehmet Suleyman Ciray ,  Jason Douglas Herzlinger

    IPC: F01D5/14

    Abstract: A turbine rotor blade is provided including an airfoil having an airfoil shape. The airfoil shape having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape.

    TURBINE BUCKET HAVING SERPENTINE CORE
    5.
    发明申请
    TURBINE BUCKET HAVING SERPENTINE CORE 有权
    具有SERPENTINE核心的涡轮鼓

    公开(公告)号：US20150110640A1

    公开(公告)日：2015-04-23

    申请号：US14061363

    申请日：2013-10-23

    Applicant: General Electric Company

    Inventor： Jason Douglas Herzlinger ,  Harish Bommanakatte ,  Anthony Louis Giglio ,  Jacob Charles Perry, II

    IPC: F01D5/18 ,  F01D5/14

    CPC classification number: F01D5/187 ,  B22C9/10 ,  B22C9/103 ,  B22C9/24 ,  F01D5/147 ,  F05D2230/211 ,  F05D2250/185 ,  F05D2250/74 ,  Y02T50/673 ,  Y02T50/676

    Abstract: Various embodiments of the invention include turbine buckets and systems employing such buckets. Various particular embodiments include a turbine bucket having: a base; and an airfoil connected with the base at a first end of the airfoil, the airfoil including: a casing having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side, the casing including an aperture on the leading edge; and a core within the casing, the core having a serpentine shape for supporting the casing and a leading edge passage fluidly connected with the aperture on the leading edge of the casing.

    Abstract translation: 本发明的各种实施例包括涡轮机桶和采用这种铲斗的系统。 各种具体实施例包括涡轮机桶，其具有：基座; 以及在所述翼型件的第一端处与所述基座连接的翼型件，所述翼型件包括：壳体，其具有：吸力侧; 与吸力侧相对的压力侧; 位于压力侧和吸力侧之间的前缘; 以及与所述前缘相对并且跨越所述压力侧和所述吸力侧的后缘，所述壳体在所述前缘上包括孔; 以及壳体内的芯部，芯部具有用于支撑壳体的蛇形形状，以及与壳体前缘上的孔流体连接的前缘通路。

    INTERIOR COOLING CIRCUITS IN TURBINE BLADES
    6.
    发明申请
    INTERIOR COOLING CIRCUITS IN TURBINE BLADES 有权
    涡轮叶片内部冷却电路

    公开(公告)号：US20140271225A1

    公开(公告)日：2014-09-18

    申请号：US13737023

    申请日：2013-01-09

    Applicant: General Electric Company

    Inventor： Jason Douglas Herzlinger ,  Bradley Taylor Boyer ,  Harish Bommanakatte ,  Anthony Louis Giglio

    IPC: F01D5/18

    CPC classification number: F01D5/187 ,  B22C9/10 ,  F05D2230/21 ,  F05D2250/232 ,  Y02T50/676 ,  Y10T29/49341

    Abstract: A rotor blade comprising an airfoil portion and a root portion, and an internal cooling circuit having flow passages in the root portion and the airfoil portion, wherein the internal cooling circuit includes: a first flow passage; and a non-integral plug. The plug may include a plug channel configured to correspond to a desired level of coolant flow through the first cooling passage. The plug may be connected to the rotor blade in a fixed blocking position relative to the first flow passage.

    Abstract translation: 一种包括翼型部分和根部的转子叶片，以及具有根部和翼型部分中的流动通道的内部冷却回路，其中内部冷却回路包括：第一流动通道; 和非整体插头。 塞子可以包括被配置为对应于通过第一冷却通道的期望水平的冷却剂流动的塞通道。 塞子可以相对于第一流动通道以固定的阻塞位置连接到转子叶片。

    TURBINE BLADE AND METHOD FOR ENHANCING LIFE OF THE TURBINE BLADE
    8.
    发明申请
    TURBINE BLADE AND METHOD FOR ENHANCING LIFE OF THE TURBINE BLADE 审中-公开
    涡轮叶片和增加涡轮叶片寿命的方法

    公开(公告)号：US20150204237A1

    公开(公告)日：2015-07-23

    申请号：US14157581

    申请日：2014-01-17

    Applicant: General Electric Company

    Inventor： William Scott Zemitis ,  Ariel Caesar Prepena Jacala ,  Jason Douglas Herzlinger

    IPC: F02C3/04

    CPC classification number: F02C3/04 ,  F01D5/187 ,  F05D2240/304 ,  F05D2260/2212 ,  Y02T50/673 ,  Y02T50/676 ,  Y10T29/49318

    Abstract: A turbine blade comprises a cooling passage defined between a pressure side wall and a suction side wall. A pin is disposed within the cooling passage and includes a first end that is connected to the pressure side wall and a second end that is connected to the suction side wall. A radially oriented fillet having a maximum radius of curvature value is disposed along a periphery of at least one of the first end or the second end within a region of peak steady state stress. An axially oriented fillet having a maximum radius of curvature value is disposed along a periphery of at least one of the first end or second end within a region of peak vibratory stress. The maximum radius of curvature value of the axially oriented fillet is greater than the maximum radius of curvature value of the radially oriented fillet.

    Abstract translation: 涡轮叶片包括限定在压力侧壁和吸力侧壁之间的冷却通道。 销设置在冷却通道内，并且包括连接到压力侧壁的第一端和连接到吸力侧壁的第二端。 具有最大曲率半径值的径向取向的圆角在峰值稳态应力的区域内沿着第一端或第二端中的至少一个的周边设置。 具有最大曲率半径值的轴向取向的圆角沿尖峰振动应力的区域内的第一端或第二端中的至少一个的周边设置。 轴向取向圆角的最大曲率半径值大于径向取向圆角的最大曲率半径值。

    TURBINE BUCKET INCLUDING COOLING PASSAGE WITH TURN
    9.
    发明申请
    TURBINE BUCKET INCLUDING COOLING PASSAGE WITH TURN 有权
    涡轮鼓包括冷却通风

    公开(公告)号：US20150110639A1

    公开(公告)日：2015-04-23

    申请号：US14061158

    申请日：2013-10-23

    Applicant: General Electric Company

    Inventor： Jason Douglas Herzlinger ,  Harish Bommanakatte ,  Anthony Louis Giglio

    IPC: F01D5/18

    CPC classification number: F01D5/18 ,  F01D5/187 ,  F05D2250/185 ,  F05D2250/74 ,  Y02T50/671 ,  Y02T50/673 ,  Y02T50/676

    Abstract: Turbine frequency tuning, fluid dynamic efficiency, and performance can be improved using a particular profile for a turn of a cooling passage in an airfoil. By blending aspects of baseline and bulb contours into a blended turn with a non-uniform profile, mechanical and/or thermal stress can be reduced in the turn and in an airfoil including the turn, particularly on an outflow side of the turn. Stresses on the airfoil can be reduced using a turn profile that is a blend of a baseline profile and a bulb profile and that can be described by the airfoil core profile.

    Abstract translation: 可以使用用于翼型件中的冷却通道的转动的特定轮廓来提高涡轮机频率调节，流体动力学效率和性能。 通过将基准线和灯泡轮廓的方面混合成具有不均匀轮廓的混合转弯，可以在转弯和包括转弯的翼型中特别是在转弯的流出侧上减小机械和/或热应力。 可以使用作为基线轮廓和灯泡轮廓的混合的转弯轮廓来减小翼型的应力，并且可以由翼型芯轮廓描述。

    Airfoil Shape for a Turbine Rotor Blade
    10.
    发明申请
    Airfoil Shape for a Turbine Rotor Blade 审中-公开

    公开(公告)号：US20180320527A1

    公开(公告)日：2018-11-08

    申请号：US15584443

    申请日：2017-05-02

    Applicant: General Electric Company

    Inventor： Neil Ristau ,  Mehmet Suleyman Ciray ,  Jason Douglas Herzlinger

    IPC: F01D5/14 ,  F04D29/38

    CPC classification number: F01D5/141 ,  F01D5/143 ,  F05D2250/74

    Abstract: A turbine rotor blade is provided including an airfoil having an airfoil shape. The airfoil shape having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape.

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