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    Turbine blade tip shroud and mid-span snubber with compound contact angle
    2.
    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 BLADE TIP SHROUD AND MID-SPAN SNUBBER WITH COMPOUND CONTACT ANGLE
    3.
    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
    4.
    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。

    TURBOMACHINE PLASMA SEAL SYSTEM
    5.
    发明申请
    TURBOMACHINE PLASMA SEAL SYSTEM 审中-公开
    涡轮等离子体密封系统

    公开(公告)号：US20140119879A1

    公开(公告)日：2014-05-01

    申请号：US13662978

    申请日：2012-10-29

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Sanjeev Kumar Jha ,  Sheo Narain Giri

    IPC: F01D11/04

    CPC classification number: F01D11/001 ,  F05D2270/172

    Abstract: Various embodiments include a turbomachine with a plasma seal system. The turbomachine can include: a diaphragm section having: an axially facing diaphragm wall; and a discourager seal protruding axially from the axially facing diaphragm wall; a rotor section having: a bucket having an axially facing bucket wall opposing the axially facing diaphragm wall; and a seal member extending from the axially facing bucket wall, wherein the seal member axially overlaps a portion of the discourager seal of the diaphragm section leaving a radial gap between the seal member and the discourager seal; and a plasma generator coupled to the diaphragm section for generating a plasma which reduces the radial gap between the seal member and the discourager seal.

    Abstract translation: 各种实施例包括具有等离子体密封系统的涡轮机。 涡轮机可以包括：隔膜部分，其具有：轴向面对的隔膜壁; 以及从轴向面对的隔膜壁轴向突出的踩踏器密封件; 转子部分具有：具有与轴向面对的隔膜壁相对的轴向面对的铲斗壁的铲斗; 以及密封构件，其从所述轴向相对的铲斗壁延伸，其中所述密封构件与所述隔膜部分的所述挡板密封件的一部分轴向重叠，在所述密封构件和所述挡板密封件之间留有径向间隙; 以及耦合到所述隔膜部分的等离子体发生器，用于产生等离子体，所述等离子体减小了所述密封构件和所述挡板密封件之间的径向间隙。

    EXHAUST PLUME CONTROL STRUCTURE AND POWER GENERATING PLANT INCLUDING SAME
    6.
    发明申请
    EXHAUST PLUME CONTROL STRUCTURE AND POWER GENERATING PLANT INCLUDING SAME 有权

    公开(公告)号：US20210262363A1

    公开(公告)日：2021-08-26

    申请号：US16798506

    申请日：2020-02-24

    Applicant: General Electric Company

    Inventor： Laxmikant Merchant ,  Sheo Narain Giri

    IPC: F01D25/30 ,  F02C6/18 ,  F01K23/10 ,  F02C3/34

    Abstract: An exhaust plume control structure includes a mounting member configured to mount to an exhaust flow source. At least one divider member operatively couples to the mounting member and is positioned in fluid communication with the exhaust flow source. A diverter member operatively couples to the divider member(s) to radially direct an initial exhaust flow from the exhaust plume towards the divider member(s). Each divider member separates the initial exhaust flow into a plurality of exhaust flows. A number of peripherally spaced, radially extending vanes may also separate the exhaust flows into additional exhaust flows. Each of the additional exhaust flows has a slower velocity than the initial exhaust flow. The structure reduces exhaust flow velocity and may provide back pressure to the initial exhaust flow. A power generating plant including the structure is also disclosed.

    Variable cross-section damper pin for a turbine blade
    7.
    发明授权
    Variable cross-section damper pin for a turbine blade 有权

    公开(公告)号：US10584597B2

    公开(公告)日：2020-03-10

    申请号：US14844306

    申请日：2015-09-03

    Applicant: General Electric Company

    Inventor： Spencer A. Kareff ,  Sheo Narain Giri

    IPC: F01D5/26 ,  F01D5/22

    Abstract: A damper pin for damping adjacent turbine blades coupled to a rotor shaft includes an elongated body having a center portion that is disposed between a first end portion and a second end portion. The first end portion, center portion and second end portion at least partially define a generally arcuate top portion of the elongated body. At least a portion of the top portion may be configured to contact with a groove that is defined between the adjacent turbine blades. The first end portion and the second end portion have substantially semi-cylindrical cross sectional shapes and the center portion has a cylindrical cross sectional shape. A bottom portion of the elongated body diverges radially outwardly from the first end portion to the center portion and from the second end portion to the center portion.

    DAMPER PIN FOR A TURBINE BLADE
    9.
    发明申请
    DAMPER PIN FOR A TURBINE BLADE 审中-公开
    涡轮叶片的阻尼器

    公开(公告)号：US20170067351A1

    公开(公告)日：2017-03-09

    申请号：US14844306

    申请日：2015-09-03

    Applicant: General Electric Company

    Inventor： Spencer A. Kareff ,  Sheo Narain Giri

    IPC: F01D5/26 ,  F01D5/22

    CPC classification number: F01D5/26 ,  F01D5/22 ,  F05D2220/30 ,  F05D2240/30 ,  F05D2260/96 ,  Y02T50/671

    Abstract: A damper pin for damping adjacent turbine blades coupled to a rotor shaft includes an elongated body having a center portion that is disposed between a first end portion and a second end portion. The first end portion, center portion and second end portion at least partially define a generally arcuate top portion of the elongated body. At least a portion of the top portion may be configured to contact with a groove that is defined between the adjacent turbine blades. The first end portion and the second end portion have substantially semi-cylindrical cross sectional shapes and the center portion has a cylindrical cross sectional shape. A bottom portion of the elongated body diverges radially outwardly from the first end portion to the center portion and from the second end portion to the center portion.

    Abstract translation: 用于阻尼与转子轴相连接的相邻涡轮叶片的阻尼器销包括细长体，其具有设置在第一端部和第二端部之间的中心部分。 第一端部，中心部分和第二端部部分至少部分地限定细长主体的大致弓形的顶部部分。 顶部的至少一部分可以构造成与限定在相邻涡轮叶片之间的凹槽接触。 第一端部和第二端部具有大致半圆柱形的横截面形状，并且中心部分具有圆柱形横截面形状。 细长体的底部从第一端部向中心部分从第二端部向中心部分径向向外分开。

    TURBINE BUCKET SHROUD ARRANGEMENT AND METHOD OF CONTROLLING TURBINE BUCKET INTERACTION WITH AN ADJACENT TURBINE BUCKET
    10.
    发明申请
    TURBINE BUCKET SHROUD ARRANGEMENT AND METHOD OF CONTROLLING TURBINE BUCKET INTERACTION WITH AN ADJACENT TURBINE BUCKET 审中-公开
    涡轮机油底壳布置方法和控制涡轮机相互作用的方法与相似的涡轮机

    公开(公告)号：US20140140841A1

    公开(公告)日：2014-05-22

    申请号：US13680974

    申请日：2012-11-19

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Krishna Kishore Gumpina ,  Sheo Narain Giri ,  Sanjeev Kumar Jha ,  Mahesh Pasupuleti

    IPC: F01D5/22

    CPC classification number: F01D5/225

    Abstract: A turbine bucket shroud arrangement for a turbine system includes a contact region of a tip shroud, wherein the contact region is in close proximity to an adjacent tip shroud. Also included is a negative thermal expansion material disposed proximate the contact region, the contact region comprising a first volume during a startup condition and a shutdown condition of the turbine system and a second volume during a steady state condition of the turbine system, wherein the second volume is less than the first volume.

    Abstract translation: 用于涡轮机系统的涡轮机桶护罩装置包括尖端护罩的接触区域，其中接触区域紧邻相邻的末端护罩。 还包括设置在接触区域附近的负热膨胀材料，所述接触区域在涡轮机系统的启动状态和关闭状态期间包括第一体积和在涡轮机系统的稳定状态期间的第二体积，其中第二体积 体积小于第一卷。

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