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    Frangible Gas Turbine Engine Airfoil
    61.
    发明申请
    Frangible Gas Turbine Engine Airfoil 审中-公开

    公开(公告)号：US20200116028A1

    公开(公告)日：2020-04-16

    申请号：US16161296

    申请日：2018-10-16

    Applicant: General Electric Company

    Inventor： Nicholas Joseph Kray ,  Nitesh Jain

    IPC: F01D5/14 ,  F01D5/28 ,  F01D21/04

    Abstract: An airfoil defining a span extending between a root and a tip and a chord at each point along the span extending between a leading edge and a trailing edge. The airfoil includes a leading edge sheath coupled to the leading edge of the airfoil. The leading edge sheath includes a flange extending from a frangible line toward the tip along the span and defining a first width along the chord at each point along the span S. The leading edge sheath further includes a base extending from the frangible line at least partially along the span to the root and defining a second width along the chord at a point along the span of the frangible line such that the second width is greater than the first width.

    Methods and apparatus for passive fan blade tip clearance control
    65.
    发明授权
    Methods and apparatus for passive fan blade tip clearance control 有权

    公开(公告)号：US12173616B2

    公开(公告)日：2024-12-24

    申请号：US18154556

    申请日：2023-01-13

    Applicant: General Electric Company

    Inventor： Abhijeet Yadav ,  Kishore Budumuru ,  Nitesh Jain

    IPC: F01D5/14 ,  F01D5/28 ,  F02C7/20

    Abstract: Methods, apparatus, systems, and articles of manufacture are disclosed for passive fan blade tip clearance control. A fan blade for a gas turbine engine, the fan blade comprising a fan blade body including a tip region at a blade tip of the fan blade body and a blade tip insert disposed within the tip region of the fan blade body, the blade tip insert is formed from a material that passively adjusts a shape of the blade tip insert to maintain a blade tip clearance between the blade tip and an engine casing or nacelle by at least one of expanding or contracting based on temperature.

    GAS TURBINE AIRFOIL NOISE REDUCTION
    67.
    发明申请
    GAS TURBINE AIRFOIL NOISE REDUCTION 有权

    公开(公告)号：US20240376824A1

    公开(公告)日：2024-11-14

    申请号：US18314244

    申请日：2023-05-09

    Applicant: General Electric Company

    Inventor： Balaraju Suresh ,  Guru Venkata Dattu Jonnalagadda ,  Trevor Howard Wood ,  Nicholas Joseph Kray ,  Vishnu Vardhan Venkata Tatiparthi ,  Nitesh Jain

    IPC: F01D5/14

    Abstract: An airfoil for a turbofan engine includes a first contoured sidewall, a second contoured sidewall, a leading edge, and a trailing edge with each extending in a spanwise direction defined between a root and a tip portion of the airfoil. The first contoured sidewall and the second contoured sidewall define an outer surface of the airfoil. The airfoil further includes a plurality of protrusions where each protrusion of the plurality of protrusions has a curvilinear shape and extends outwardly from the outer surface along at least one of the first contoured sidewall or the second contoured sidewall. The plurality of protrusions is defined downstream from a mid-point of a chord length of the airfoil and terminates upstream of the trailing edge.

    PITCH CHANGE MECHANISM FOR A FAN OF A GAS TURBINE ENGINE
    68.
    发明公开
    PITCH CHANGE MECHANISM FOR A FAN OF A GAS TURBINE ENGINE 审中-公开

    公开(公告)号：US20240271539A1

    公开(公告)日：2024-08-15

    申请号：US18644467

    申请日：2024-04-24

    Applicant: General Electric Company

    Inventor： Abhijeet Jayshingrao Yadav ,  Nicholas Joseph Kray ,  Nitesh Jain ,  Ricardo Hernandez Pandeli

    IPC: F01D7/00

    CPC classification number: F01D7/00

    Abstract: A gas turbine engine including: a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order; a fan defining a fan axis and comprising a plurality of fan blades rotatable about the fan axis; and a pitch change mechanism operable with the plurality of fan blades, the pitch change mechanism including a plurality of linkages, the plurality of linkages including a first linkage coupled to a first fan blade of the plurality of fan blades and a second linkage coupled to a second fan blade of the plurality of fan blades; and a non-uniform blade actuator system operable with one or more of the plurality of linkages to control a pitch of the first fan blade relative to a pitch of the second fan blade.

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