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    TURBINE BLADE TIP SHROUD AND MID-SPAN SNUBBER WITH COMPOUND CONTACT ANGLE
    11.
    发明申请
    TURBINE BLADE TIP SHROUD AND MID-SPAN SNUBBER WITH COMPOUND CONTACT ANGLE 审中-公开
    带有复合接触角的涡轮叶片尖头和中等间距的SNUBBER

    公开(公告)号：US20140234110A1

    公开(公告)日：2014-08-21

    申请号：US13772777

    申请日：2013-02-21

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Gayathri PURAM ,  Sheo Narain Giri ,  Harish Bommanakatte

    IPC: F01D5/22

    CPC classification number: F01D5/225

    Abstract: A turbine bucket adapted to be supported on a turbine or rotor wheel includes an airfoil portion extending radially relative to a longitudinal axis of the rotor wheel and having a leading edge, a trailing edge, a pressure side and a suction side. At least one tip shroud extends in opposite circumferential directions, the shroud having a first hard face adapted to engage a mating second hard face on a shroud extending circumferentially from an adjacent bucket. The first hard face defined by a surface portion that varies circumferentially with an increasing radius as measured from the longitudinal axis of the rotor wheel.

    Abstract translation: 适于被支撑在涡轮机或转子轮上的涡轮机叶片包括相对于转子轮的纵向轴线径向延伸并具有前缘，后缘，压力侧和吸力侧的翼型部分。 至少一个尖端护罩在相反的圆周方向上延伸，所述护罩具有第一硬表面，所述第一硬表面适于接合从邻近的桶周向延伸的护罩上的配合的第二硬表面。 由表面部分限定的第一硬表面，其从转子轮的纵向轴线测量的沿半径变化的周向变化。

    TURBINE SHROUD ARRANGEMENT FOR A TURBINE SYSTEM AND METHOD OF CONTROLLING A TURBINE SHROUD ARRANGEMENT
    12.
    发明申请
    TURBINE SHROUD ARRANGEMENT FOR A TURBINE SYSTEM AND METHOD OF CONTROLLING A TURBINE SHROUD ARRANGEMENT 审中-公开
    涡轮机系统的涡轮风力发电机组和控制涡轮机风力发电机组的方法

    公开(公告)号：US20140140807A1

    公开(公告)日：2014-05-22

    申请号：US13681057

    申请日：2012-11-19

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Krishna Kishore Gumpina ,  Harish Bommanakatte ,  Sheo Narain Giri ,  Sanjeev Kumar Jha

    IPC: F01D25/24

    CPC classification number: F01D5/225 ,  F05D2300/5021 ,  F05D2300/505

    Abstract: A turbine shroud arrangement for a turbine system includes a first region of a tip shroud, the first region disposed in close proximity to an adjacent tip shroud. Also included is a second region of the tip shroud, the second region disposed in close proximity to the adjacent tip shroud, the second region comprising a temperature sensitive material configured to engage the second region and the adjacent tip shroud in contact over a first operating condition of the turbine system and configured to provide a second region gap over a second operating condition of the turbine system.

    Abstract translation: 用于涡轮机系统的涡轮机护罩装置包括尖端护罩的第一区域，第一区域设置成紧邻相邻的末梢护罩。 还包括尖端护罩的第二区域，第二区域设置成紧邻相邻的顶部护罩，第二区域包括温度敏感材料，其被配置为在第一操作条件下接合第二区域和相邻的尖端护罩接触 并且构造成在所述涡轮机系统的第二操作状态上提供第二区域间隙。

    Turbine blade tip shroud and mid-span snubber with compound contact angle
    13.
    发明授权
    Turbine blade tip shroud and mid-span snubber with compound contact angle 有权

    公开(公告)号：US10465531B2

    公开(公告)日：2019-11-05

    申请号：US13772777

    申请日：2013-02-21

    Applicant: General Electric Company

    Inventor： Gayathri Puram ,  Sheo Narain Giri ,  Harish Bommanakatte

    IPC: F01D5/22

    Abstract: A turbine bucket adapted to be supported on a turbine or rotor wheel includes an airfoil portion extending radially relative to a longitudinal axis of the rotor wheel and having a leading edge, a trailing edge, a pressure side and a suction side. At least one tip shroud extends in opposite circumferential directions, the shroud having a first hard face adapted to engage a mating second hard face on a shroud extending circumferentially from an adjacent bucket. The first hard face defined by a surface portion that varies circumferentially with an increasing radius as measured from the longitudinal axis of the rotor wheel.

    TURBINE BUCKET INCLUDING COOLING PASSAGE WITH TURN
    17.
    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。

    Turbine bucket base having serpentine cooling passage with leading edge cooling
    18.
    发明授权
    Turbine bucket base having serpentine cooling passage with leading edge cooling 有权

    公开(公告)号：US09670784B2

    公开(公告)日：2017-06-06

    申请号：US14061193

    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

    CPC classification number: F01D5/187 ,  F01D5/186 ,  Y02E20/16 ,  Y02T50/672 ,  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 including: a casing having at least one exhaust aperture on an outer surface of the casing; and a core within the casing, the core having: a serpentine cooling passage; and at least one outlet passage fluidly connected with the serpentine cooling passage and the exhaust aperture, wherein the at least one outlet passage permits flow of a coolant from the serpentine cooling passage to the at least one exhaust aperture on the outer surface of the casing; and an airfoil connected with the base at a first end of the airfoil, the airfoil including: 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.

    Turbine bucket having serpentine core
    20.
    发明授权
    Turbine bucket having serpentine core 有权
    涡轮桶具有蛇形核心

    公开(公告)号：US09528379B2

    公开(公告)日：2016-12-27

    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: F01D5/14 ,  F01D5/18 ,  B22C9/10 ,  B22C9/24

    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。

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