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    Turbine wheel cover-plate mounted gas turbine interstage seal
    11.
    发明授权
    Turbine wheel cover-plate mounted gas turbine interstage seal 有权

    公开(公告)号：US10662793B2

    公开(公告)日：2020-05-26

    申请号：US14556305

    申请日：2014-12-01

    Applicant: General Electric Company

    Inventor： Omprakash Samudrala ,  Edip Sevincer ,  Jonathan Michael Webster ,  Fernando Jorge Casanova

    IPC: F01D11/00 ,  F02C7/28 ,  F01D5/30

    Abstract: A sealing system for a multi-stage turbine includes multiple first interstage seal subsystems disposed circumferentially about a rotor wheel shaft of the multi-stage turbine and extending axially between a first turbine stage and a second turbine stage of the multi-stage turbine. Each of the first interstage seal subsystems includes multiple near flow path seal segments. The first interstage seal subsystem also includes a forward coverplate disposed axially between a first turbine wheel of the first turbine stage and the near flow path seal segment and an aft coverplate disposed axially between the near flow path seal segment and a second turbine wheel of the second turbine stag. Further, each of the forward coverplate and the aft coverplate extends radially to a first stage bucket and a second stage bucket respectively.

    FACE SEAL ASSEMBLY AND AN ASSOCIATED METHOD THEREOF
    13.
    发明申请
    FACE SEAL ASSEMBLY AND AN ASSOCIATED METHOD THEREOF 审中-公开

    公开(公告)号：US20180003069A1

    公开(公告)日：2018-01-04

    申请号：US15397317

    申请日：2017-01-03

    Applicant: General Electric Company

    Inventor： Rahul Anil Bidkar ,  Azam Mihir Thatte ,  Jifeng Wang ,  Xiaoqing Zheng ,  Edip Sevincer

    IPC: F01D11/06 ,  F01D25/16 ,  F01D5/02 ,  F01D9/02 ,  F16J15/40

    CPC classification number: F16J15/40 ,  F01D25/22 ,  F05D2240/53 ,  F16J15/342

    Abstract: A turbomachine and a method of operating the turbomachine are disclosed. The turbomachine includes a stator, a rotor including a rotor bearing face, a face seal assembly, a first pressure cavity, and a second pressure cavity. The face seal assembly includes a seal ring including a seal bearing face, a first pressure cavity, and a plurality of isolated hydrostatic ports extending from the first pressure cavity to the seal bearing face. The face seal assembly is slidably coupled to the stator and defines a face seal clearance between the rotor and seal bearing faces. The second and third pressure cavities are defined by the stator, the rotor, and the face seal assembly. The third pressure cavity is disposed downstream of the second pressure cavity with reference to flow of a process fluid along the stator and rotor. The first pressure cavity is isolated from the second and third pressure cavities.

    Seals with a thermal barrier for turbomachinery
    14.
    发明授权
    Seals with a thermal barrier for turbomachinery 有权

    公开(公告)号：US09850772B2

    公开(公告)日：2017-12-26

    申请号：US14695288

    申请日：2015-04-24

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Neelesh Nandkumar Sarawate ,  Edip Sevincer ,  Anthony Marin

    IPC: F01D25/00 ,  F01D11/00

    CPC classification number: F01D11/005 ,  F01D25/005 ,  F05D2300/6033

    Abstract: Seal assemblies for reducing leakage between components of turbomachinery include a metallic shim, at least a pair of non-metallic end blocks, and ceramic fiber positioned between the shim and the end blocks. The shim may be mechanically coupled with the end blocks such that the metallic shim, end blocks and ceramic fiber are coupled. The end blocks account for misalignment of turbine components by ensuring sealing engagement of the seal to the components. The end blocks may be a ceramic or glass material, and the ceramic fiber may be a high temperature woven ceramic fiber. The ceramic fiber and/or the end blocks protect the metallic shim from reaching harmful temperatures during use of the seal, such as use in high temperature turbines including CMC components.

    TURBINE SNAP IN SPRING SEAL
    15.
    发明申请
    TURBINE SNAP IN SPRING SEAL 审中-公开

    公开(公告)号：US20170089211A1

    公开(公告)日：2017-03-30

    申请号：US14864221

    申请日：2015-09-24

    Applicant: General Electric Company

    Inventor： Mark Broomer ,  Edip Sevincer ,  Anthony Christopher Marin

    IPC: F01D11/00 ,  F16J15/04

    CPC classification number: F01D11/005 ,  F05D2220/32 ,  F05D2240/55 ,  F05D2250/71 ,  F05D2250/75 ,  F05D2300/501 ,  F16J15/04 ,  F16J15/0887

    Abstract: Snap in annular spring seal including continuous or split full 360 degree ring having radially outer second seal end spaced outwardly of a radially inner first end of the ring and axial biasing means urging first and second seal ends apart. Biasing means may include an axially aftwardly opening conical section connecting first and second seal ends and second seal end having outer aftwardly opening V-shaped cross-sectional bend or circular cross-sectional bend. Spring seal may extend radially and circumferentially between and in sealing engagement with first and second annular turbine components. First end may be spring-loaded and removably secured in U-shaped or V-shaped slot of turbine component. Slot may include symmetrical inner U-shaped bent first seal end including annular substantially parallel or non-parallel forward and aft legs connected by semi-circular cross-sectional bend. Seal may include bowed section connecting circular seal ends.

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