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    Stacked wheel assembly for a rotor of a rotary machine
    11.
    发明授权
    Stacked wheel assembly for a rotor of a rotary machine 有权

    公开(公告)号：US09689261B2

    公开(公告)日：2017-06-27

    申请号：US14076475

    申请日：2013-11-11

    Applicant: General Electric Company

    Inventor： Rajesh Kumar

    IPC: F01D5/06

    CPC classification number: F01D5/066

    Abstract: A stacked wheel assembly for a rotor of a rotary machine includes a plurality of stacked wheels for rotation about a common axis and forming a portion of the rotor. Also included is a tie bolt passing through aligned bolt holes of the plurality of stacked wheels for retaining the plurality of stacked wheels in axially stacked relation, the tie bolt extending out of a forward end of a forward wheel of the plurality of stacked wheels and out of an aft end of an aft wheel of the plurality of stacked wheels. Further included is a rotor component disposed adjacent the aft end of the aft wheel. Yet further included is a nut mounted within a forward face of the rotor component, the nut configured to be in threaded engagement with the tie bolt to exert a clamping force on the plurality of stacked wheels.

    FASTENER WITH RADIAL LOADING
    12.
    发明申请
    FASTENER WITH RADIAL LOADING 有权
    紧固件与径向加载

    公开(公告)号：US20140308088A1

    公开(公告)日：2014-10-16

    申请号：US13863441

    申请日：2013-04-16

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Fernando Jorge Casanova ,  Rajesh Kumar ,  Madhumita Roy

    IPC: F16B29/00

    CPC classification number: F16B5/02 ,  F16B4/004

    Abstract: A fastener is provided including a bolt having at least one threaded end, a first sleeve configured to fit over the bolt, and a second sleeve configured to fit over the first sleeve. At least one nut is configured to cooperate with threads in the threaded ends of the bolt. The first and second sleeves are configured to impart an outwardly radial load when the nuts are tightened on the bolt.

    Abstract translation: 提供了紧固件，其包括具有至少一个螺纹端的螺栓，被配置成装配在螺栓上的第一套筒以及配置成装配在第一套筒上的第二套筒。 至少一个螺母构造成与螺栓的螺纹端部中的螺纹配合。 当螺母紧固在螺栓上时，第一和第二套筒构造成赋予向外的径向载荷。

    Turbine engine including a gas path component having a hydrophobic coating
    13.
    发明授权
    Turbine engine including a gas path component having a hydrophobic coating 有权

    公开(公告)号：US12253023B1

    公开(公告)日：2025-03-18

    申请号：US18468198

    申请日：2023-09-15

    Applicant: General Electric Company

    Inventor： Arthur W. Sibbach ,  Rajesh Kumar ,  Jeffrey D. Rambo

    IPC: F02C3/06 ,  F02C3/30

    Abstract: A turbine engine for an aircraft. The turbine engine includes a combustor and a steam system. Fuel and steam are injected into the combustor to mix with compressed air to generate a fuel and air mixture. The fuel and air mixture is combusted in the combustor to generate combustion gases. The steam system is fluidly coupled to the combustor as the steam source to provide steam to the combustor. The steam system includes a hot gas path and a steam hot gas path component. The hot gas path is fluidly coupled to the combustor to receive the combustion gases and to route the combustion gases through the steam system. The steam hot gas path component includes a wall having a combustion-gas-facing surface facing the hot gas path and a hydrophobic coating formed on the combustion-gas-facing surface.

    SEAL SUPPORT ASSEMBLY FOR A TURBINE ENGINE
    15.
    发明公开
    SEAL SUPPORT ASSEMBLY FOR A TURBINE ENGINE 审中-公开

    公开(公告)号：US20240301801A1

    公开(公告)日：2024-09-12

    申请号：US18180449

    申请日：2023-03-08

    Applicant: General Electric Company

    Inventor： Ravindra Shankar Ganiger ,  Vidyashankar Ramasastry Buravalla ,  David Raju Yamarthi ,  Rajesh Kumar ,  Jeffrey Douglas Rambo

    IPC: F01D11/08 ,  F03G7/06

    CPC classification number: F01D11/08 ,  F03G7/0614 ,  F05D2220/30 ,  F05D2240/55

    Abstract: A turbine engine is provided. The turbine engine includes: a rotor; a stator having a carrier; a seal support assembly coupled to the carrier; and a seal assembly disposed between the rotor and the stator and supported by the seal support assembly, the seal assembly defining a high pressure side and a low pressure side and including a plurality of seal segments, the plurality of seal segments having a first seal segment, the first seal segment having a seal face configured to form a fluid bearing with the rotor, a lip assembly, and a body, the lip assembly positioned on the high pressure side, the lip assembly including a seal lip having a high pressure surface defining a first angle with an axial direction and a low pressure surface defining a second angle with the axial direction, the second angle being greater than the first angle.

    System and method for mitigating bowed rotor in a gas turbine engine
    16.
    发明授权
    System and method for mitigating bowed rotor in a gas turbine engine 有权

    公开(公告)号：US11879411B2

    公开(公告)日：2024-01-23

    申请号：US17838603

    申请日：2022-06-13

    Applicant: General Electric Company

    Inventor： Rajesh Kumar ,  Prateek Jalan ,  Kudum Shinde ,  Atanu Saha ,  Hiranya Kumar Nath ,  Ravindra Shankar Ganiger

    IPC: F02K3/02 ,  F02C7/12

    CPC classification number: F02K3/02 ,  F02C7/12 ,  F05D2260/20

    Abstract: A gas turbine engine includes a casing, a rotor assembly rotatably mounted within the casing, the rotor assembly comprising a forward rotor portion defining a forward rotor cavity and an aft rotor portion defining an aft rotor cavity, the aft rotor cavity being fluidly isolated from the forward rotor cavity, and a cooling system. The cooling system includes a forward cooling fluid supply, a forward supply line providing fluid communication between the forward cooling fluid supply and the forward rotor cavity, an aft cooling fluid supply, an aft supply line providing fluid communication between the aft cooling fluid supply and the aft rotor cavity, and a flow control system fluidly coupled to the forward supply line and the aft supply line for regulating a flow of forward cooling fluid and a flow of aft cooling fluid.

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