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    INTEGRATED NOZZLE AND DIAPHRAGM WITH OPTIMIZED INTERNAL VANE THICKNESS
    3.
    发明申请
    INTEGRATED NOZZLE AND DIAPHRAGM WITH OPTIMIZED INTERNAL VANE THICKNESS 有权

    公开(公告)号：US20210087979A1

    公开(公告)日：2021-03-25

    申请号：US16575785

    申请日：2019-09-19

    Applicant: General Electric Company

    Inventor： Travis J Packer ,  Brad Wilson VanTassel ,  William Scott Zemitis

    IPC: F02C9/22

    Abstract: A vane of a turbine system is provided. The vane includes: an internal cavity configured to receive a flow of cooling fluid; a variable thickness wall adjacent the internal cavity; and an impingement plate separating the variable thickness wall from the internal cavity, the impingement plate including a plurality of apertures for directing the cooling fluid into an impingement cavity and against the variable thickness wall, wherein the impingement plate is configured to follow a contour of the variable thickness wall.

    TURBINE SHROUD INCLUDING PLURALITY OF COOLING PASSAGES
    4.
    发明申请
    TURBINE SHROUD INCLUDING PLURALITY OF COOLING PASSAGES 审中-公开

    公开(公告)号：US20200025026A1

    公开(公告)日：2020-01-23

    申请号：US16040062

    申请日：2018-07-19

    Applicant: General Electric Company

    Inventor： Travis J Packer ,  Benjamin Paul Lacy ,  Ibrahim Sezer ,  Zachary John Snider ,  Brad Wilson VanTassel

    IPC: F01D25/12 ,  F01D11/08

    Abstract: Turbine shrouds for turbine systems are disclosed. The turbine shrouds may include a unitary body including a forward and aft end, an outer surface facing a cooling chamber formed between the unitary body and a turbine casing of the turbine system, and an inner surface facing a hot gas flow path. The shrouds may also include a first cooling passage extending within the unitary body, and a plurality of impingement openings formed through the outer surface of the unitary body to fluidly couple the first cooling passage to the cooling chamber. Additionally, the shrouds may include a second cooling passage and/or a third cooling passage. The second cooling passage may extend adjacent the forward end and may be in fluid communication with the first cooling passage. The third cooling passage may extend adjacent the aft end, and may be in fluid communication with the first cooling passage.

    Nested damper pin and vibration dampening system for turbine nozzle or blade
    7.
    发明授权
    Nested damper pin and vibration dampening system for turbine nozzle or blade 有权

    公开(公告)号：US11976565B2

    公开(公告)日：2024-05-07

    申请号：US17815372

    申请日：2022-07-27

    Applicant: General Electric Company

    Inventor： Zachary John Snider ,  Brad Wilson VanTassel ,  Brian Denver Potter ,  John McConnell Delvaux

    IPC: F01D5/16

    CPC classification number: F01D5/16 ,  F05D2220/32 ,  F05D2260/96

    Abstract: A vibration dampening system includes a vibration dampening element for a turbine nozzle or blade. A body opening extends through the turbine nozzle or blade, e.g., through the airfoil among potentially other parts of the nozzle or blade. A vibration dampening element includes a plurality of stacked damper pins within the body opening. The damper pins include an outer body having an inner opening, a first end surface and an opposing second end surface; and an inner body nested and movable within the inner opening of the outer body. The end surfaces frictionally engage to dampen vibration. The inner body has a first central opening including a first portion configured to engage an elongated body therein and an outer surface configured to frictionally engage a portion of the inner opening of the outer body to dampen vibration.

    TURBINE COMPONENT WITH HEATED STRUCTURE TO REDUCE THERMAL STRESS
    8.
    发明公开
    TURBINE COMPONENT WITH HEATED STRUCTURE TO REDUCE THERMAL STRESS 审中-公开

    公开(公告)号：US20230399959A1

    公开(公告)日：2023-12-14

    申请号：US17806317

    申请日：2022-06-10

    Applicant: General Electric Company

    Inventor： Brandon Lee Cox ,  Brad Wilson VanTassel ,  Benjamin Paul Lacy

    IPC: F01D25/08 ,  F01D5/12

    CPC classification number: F01D25/08 ,  F01D5/12 ,  F05D2220/30 ,  F05D2260/941

    Abstract: A turbine component includes a first structure exposed to a hot gas path and a second structure integral with the first structure but isolated from the hot gas path. A first fluid passage in the first structure delivers a thermal transfer fluid, e.g., air, through the first structure to cool the first structure. A second fluid passage is defined within the second structure and is in fluid communication with the first fluid passage. After heat transfer in the first structure, the thermal transfer fluid is hotter than a temperature of the second structure and thus increases the temperature of the second structure. The heat transfer to the second structure reduces a temperature difference between the first structure and the second structure that would, without heating, cause thermal stress between the structures. The heating of the second structure reduces the need for early maintenance and lengthens the lifespan of the component.

    COOLANT DELIVERY VIA AN INDEPENDENT COOLING CIRCUIT
    9.
    发明申请
    COOLANT DELIVERY VIA AN INDEPENDENT COOLING CIRCUIT 有权

    公开(公告)号：US20220220858A1

    公开(公告)日：2022-07-14

    申请号：US16663912

    申请日：2019-10-25

    Applicant: General Electric Company

    Inventor： Matthew Troy Hafner ,  Brad Wilson VanTassel ,  Christopher Donald Porter ,  Srikanth Chandrudu Kottilingam

    IPC: F01D5/18

    Abstract: An embodiment of an independent cooling circuit for selectively delivering cooling fluid to a component of a gas turbine system includes: a plurality of independent circuits of cooling channels embedded within an exterior wall of the component, wherein the plurality of circuits of cooling channels are interwoven together; an impingement plate; and a plurality of feed tubes connecting the impingement plate to the exterior wall of the component and fluidly coupling each of the plurality of circuits of cooling channels to at least one supply of cooling fluid, wherein, in each of the plurality of circuits of cooling channels, the cooling fluid flows through the plurality of feed tubes into the circuit of cooling channels only in response to a formation of a breach in the exterior wall of the component that exposes at least one of the cooling channels of the circuit of cooling channels.

    COOLANT DELIVERY VIA AN INDEPENDENT COOLING CIRCUIT
    10.
    发明申请
    COOLANT DELIVERY VIA AN INDEPENDENT COOLING CIRCUIT 有权

    公开(公告)号：US20220205363A1

    公开(公告)日：2022-06-30

    申请号：US16663873

    申请日：2019-10-25

    Applicant: General Electric Company

    Inventor： Matthew Troy Hafner ,  Brad Wilson VanTassel ,  Christopher Donald Porter ,  Srikanth Chandrudu Kottilingam

    IPC: F01D5/18

    Abstract: A coolant delivery system for a component of a gas turbine system includes: a plurality of independent circuits of cooling channels embedded within an exterior wall of the component, each independent circuit of cooling channels including a plurality of headers and a plurality of feed tubes fluidly coupling the plurality of headers to a supply of cooling fluid; and an impingement plate connected to the exterior wall of the component by the plurality of feed tubes of the independent circuits of cooling channels, wherein, in each of the plurality of independent circuits of cooling channels, the cooling fluid flows through the plurality of feed tubes and the plurality of headers into the circuit of cooling channels only in response to a formation of a breach in the exterior wall of the component that exposes at least one of the cooling channels of the circuit of cooling channels.

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