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    Sealing system for turbine shroud segments
    1.
    发明授权
    Sealing system for turbine shroud segments 有权

    公开(公告)号：US10934873B2

    公开(公告)日：2021-03-02

    申请号：US16182727

    申请日：2018-11-07

    Applicant: General Electric Company

    Inventor： Neelesh Nandkumar Sarawate ,  Christopher Edward Wolfe ,  John Patrick Pollinger

    IPC: F01D11/00 ,  F01D25/26 ,  F01D9/04

    Abstract: A turbine shroud is disposed between stages of stationary turbine nozzles. The turbine shroud includes arcuate shroud segments sealingly engaged with one another. Each shroud segment includes a bottom panel with a radially inner surface and a radially outer surface and opposite ends. Each end includes an end face, an end cutback face spaced from the end face, and an intermediate surface extending between the end face and the end cutback face to define a recess. One or more seals overlap the recess of a circumferentially adjacent pair of shroud segments to produce a sealed joint.

    VERTICALLY ORIENTED SEAL SYSTEM FOR GAS TURBINE VANES
    2.
    发明申请
    VERTICALLY ORIENTED SEAL SYSTEM FOR GAS TURBINE VANES 审中-公开

    公开(公告)号：US20200040750A1

    公开(公告)日：2020-02-06

    申请号：US16050008

    申请日：2018-07-31

    Applicant: General Electric Company

    Inventor： John Ellington Greene ,  Neelesh Nandkumar Sarawate

    IPC: F01D11/00 ,  F01D9/04

    Abstract: A seal system for a gas turbine vane includes a first seal layer and an optional second seal layer. Each first seal layer includes multiple seal segments, each of which includes a first leg, a second leg, and an intermediate portion between the first leg and the second leg. Each adjacent pair of seal segments of the first seal is separated by a gap. The seal segments define a substantially complete perimeter of a seal slot in which the first seal is installed. The second seal, which is also segmented, may or may not define the substantially complete perimeter of the seal slot. If present, the second seal segments are circumferentially offset from the first seal segments to block the gaps between the first seal segments. A turbine vane including the present seal system is also disclosed.

    SYSTEM AND METHOD FOR TRANSITION PIECE SEAL
    6.
    发明申请
    SYSTEM AND METHOD FOR TRANSITION PIECE SEAL 审中-公开

    公开(公告)号：US20180258782A1

    公开(公告)日：2018-09-13

    申请号：US15452458

    申请日：2017-03-07

    Applicant: General Electric Company

    Inventor： Rahul Anil Bidkar ,  Neelesh Nandkumar Sarawate

    IPC: F01D11/00 ,  F02C3/14 ,  F01D9/04 ,  F01D9/02

    CPC classification number: F01D11/003 ,  F01D9/023 ,  F01D9/041 ,  F01D11/005 ,  F01D25/243 ,  F01D25/30 ,  F02C3/14 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2240/35 ,  F05D2240/55 ,  F05D2240/57

    Abstract: A system includes a transition piece configured to receive combustion products from a combustion chamber, and the transition piece is coupled to a first support of the system. The system further includes a turbine nozzle configured to receive combustion products from the transition piece, and the turbine nozzle is coupled to a second support of the system. The system further includes a web plate disposed at a radial position about a turbine axis between the transition piece and the turbine nozzle. The web plate is configured to form a first seal between the web plate and the transition piece and the web plate is configured to form a second seal between the web plate and the turbine nozzle. In addition, the web plate extends in a circumferential direction about the turbine axis and the web plate is coupled to a third support of the system. Further, the web plate includes an inner surface, an outer surface, and an arm extending in a radial direction between the inner surface and the outer surface.

    METHOD AND SYSTEM TO FACILITATE SEALING IN GAS TURBINES
    8.
    发明申请
    METHOD AND SYSTEM TO FACILITATE SEALING IN GAS TURBINES 有权
    在气体涡轮机中密封的方法和系统

    公开(公告)号：US20150098808A1

    公开(公告)日：2015-04-09

    申请号：US14049020

    申请日：2013-10-08

    Applicant: General Electric Company

    Inventor： Victor John Morgan ,  Gregory Thomas Foster ,  Neelesh Nandkumar Sarawate ,  David Wayne Weber

    IPC: F01D11/08

    CPC classification number: F01D11/08 ,  F01D9/041 ,  F01D11/003 ,  F05D2230/60 ,  F05D2260/38 ,  Y10T29/4932

    Abstract: A method and system for sealing between components within a gas turbine is provided. A first recess defined in a first component receives a seal member. A second recess defined in a second component adjacent the first component also receives the seal member. The first and second recesses are located proximate a hot gas path defined through the gas turbine, and define circumferential paths about the turbine axis. The seal member includes a sealing face that extends in a direction substantially parallel to the turbine axis. The seal member also includes a plurality of seal layers, wherein at least one of the seal layers includes at least one stress relief region for facilitating flexing of the first seal member.

    Abstract translation: 提供了一种在燃气轮机内的部件之间进行密封的方法和系统。 限定在第一部件中的第一凹部接收密封构件。 限定在与第一部件相邻的第二部件中的第二凹部也接收密封部件。 第一和第二凹槽位于通过燃气涡轮机限定的热气路径附近，并限定围绕涡轮机轴线的圆周路径。 密封构件包括沿基本上平行于涡轮机轴线的方向延伸的密封面。 密封构件还包括多个密封层，其中至少一个密封层包括用于促进第一密封构件弯曲的至少一个应力释放区域。

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