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    Seal assemblies for turbine engines having wear detection features
    1.
    发明授权
    Seal assemblies for turbine engines having wear detection features 有权

    公开(公告)号：US12203375B2

    公开(公告)日：2025-01-21

    申请号：US17871063

    申请日：2022-07-22

    Applicant: General Electric Company

    Inventor： Narendra Anand Hardikar ,  Deepak Trivedi ,  Ravindra Shankar Ganiger ,  Scott Alan Schimmels ,  Kevin Richard Graziano

    IPC: F01D11/02 ,  F01D11/12

    Abstract: A seal assembly at a rotor-stator interface includes at least one non-contacting seal interface and at least one rub detection feature. The rub detection feature(s) is configured to generate a signal upon the rotor and the stator making contact at the rotor-stator interface and causing wear above a certain threshold at the rotor-stator interface. The seal assembly also includes at least one sensor arranged at the rotor-stator interface. The sensor is configured to sense the signal. The seal assembly further includes a controller communicatively coupled with the sensor(s). The controller is configured to receive the signal and estimate at least one of an amount and a location of the wear at the rotor-stator interface based on the signal.

    Seal assembly for a gas turbine engine
    4.
    发明授权
    Seal assembly for a gas turbine engine 有权

    公开(公告)号：US12215588B2

    公开(公告)日：2025-02-04

    申请号：US18190403

    申请日：2023-03-27

    Applicant: General Electric Company

    Inventor： Tajinder Singh ,  Rajesh Kumar ,  David Raju Yamarthi ,  Bryan Jung Woo Hong ,  Narendra Anand Hardikar ,  Ravindra Shankar Ganiger ,  Jeffrey Douglas Rambo

    IPC: F01D11/10

    Abstract: A turbine engine includes a rotor, a stator, and a seal assembly disposed between the rotor and the stator. The seal assembly includes seal segment. The seal segment includes a seal face that is configured to form a fluid bearing with the rotor. A lift channel extends within the seal segment from an opening on the seal face. The turbine engine further includes a spring assembly disposed within the lift channel. The spring assembly including a biasing element and a piston element coupled to the biasing element. The lift channel includes a lift volume portion extending is between the opening and the piston element. The piston element is movable within the lift channel based on a pressure within the fluid bearing to adjust a size of the lift volume portion.

    Seal assemblies for turbine engines
    6.
    发明授权
    Seal assemblies for turbine engines 有权

    公开(公告)号：US11891898B2

    公开(公告)日：2024-02-06

    申请号：US18081245

    申请日：2022-12-14

    Applicant: General Electric Company

    Inventor： Narendra Anand Hardikar ,  Scott Alan Schimmels

    IPC: F01D11/00

    CPC classification number: F01D11/003 ,  F05D2240/55

    Abstract: A rotary machine includes a stator and a rotor configured to rotate with respect to the stator. The rotor is arranged with the stator at a rotor-stator interface and defines a rotor face. Further, the rotary machine includes a seal assembly at the rotor-stator interface. The seal assembly includes at least one seal and a groove formed into the rotor at the rotor-stator interface. In addition, the seal assembly includes a removable insert positioned within the groove of the seal assembly and defining at least a portion of the rotor face. As such, during operation of the rotary machine, if the rotor and the stator make undesirable contact at the rotor-stator interface, the removable insert becomes damaged to prevent damage from occurring to the rotor and the stator.

    GAS TURBINE ENGINE DEFINING A ROTOR CAVITY
    7.
    发明申请
    GAS TURBINE ENGINE DEFINING A ROTOR CAVITY 有权

    公开(公告)号：US20240418130A1

    公开(公告)日：2024-12-19

    申请号：US18362341

    申请日：2023-07-31

    Applicant: General Electric Company

    Inventor： Narendra Anand Hardikar

    IPC: F02C7/28 ,  F01D9/04

    Abstract: A gas turbine engine includes a compressor section, a combustion section, and a turbine section arranged in serial flow order and defining a working gas flowpath, a compressor of the compressor section comprising an aft-most compressor stage; a stage of stator vanes located downstream of the aft-most compressor stage; a stator case including a seal pad; and a spool drivingly coupled to the compressor, the spool and the stator case together defining a rotor cavity in fluid communication with the working gas flowpath, the spool comprising a seal tooth assembly, the seal tooth assembly including a seal support extension, a seal tooth extending from the seal support extension toward the seal pad, and a dampener operable with the seal support extension.

    FACE SEAL ROBUST TO CASING VIBRATION
    10.
    发明申请
    FACE SEAL ROBUST TO CASING VIBRATION 有权

    公开(公告)号：US20240426222A1

    公开(公告)日：2024-12-26

    申请号：US18751022

    申请日：2024-06-21

    Applicant: General Electric Company

    Inventor： Deepak Trivedi ,  Rahul Anil Bidkar ,  Bugra H. Ertas ,  Narendra Anand Hardikar ,  Ravindra Shankar Ganiger

    IPC: F01D11/08 ,  F01D25/04

    Abstract: This disclosure is directed to seal assemblies for a turbomachine. The seal assemblies include one or more paired rotors and stators and at least one interface between the rotors and the stators. The components of the stator may be axially and radially movable by vibrations and other mechanical interference. The stators comprise a sealing element, a seal housing, and a stator interface connected to the engine housing. In some examples, seal assembly includes a damping element to isolate one or more of the rotating components from vibrations mechanical interference that might misalign the rotating components from the stationary components while the turbomachine is operational. In some examples, the damping element is positioned between the seal housing and the stator interface. In other examples, the damping element is positioned between the stator interface and the engine housing.

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