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    Composite airfoils with frangible tips
    2.
    发明授权
    Composite airfoils with frangible tips 有权

    公开(公告)号：US12116903B2

    公开(公告)日：2024-10-15

    申请号：US17363102

    申请日：2021-06-30

    Applicant: General Electric Company

    Inventor： Nitesh Jain ,  Nicholas Joseph Kray ,  Daniel Edward Mollmann ,  David William Crall

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

    CPC classification number: F01D5/147 ,  F01D5/282 ,  F01D5/284 ,  F01D21/045 ,  F05D2220/36 ,  F05D2240/304 ,  F05D2240/307 ,  F05D2300/6033

    Abstract: Composite airfoils and methods for forming composite airfoils are provided. For example, a composite airfoil of a gas turbine engine comprises opposite pressure and suction sides extending radially along a span from a root to a tip, which define opposite radial extremities of the airfoil. The composite airfoil further comprises a body section and a tip section, which includes the tip, that each extend radially along the span. The composite airfoil is formed from a composite material comprising fibers disposed in a matrix material. The tip section has a tip fiber volume, and the body section has a body fiber volume that is greater than the tip fiber volume. Another composite airfoil comprises a tip cap applied over the tip that tapers from a first end to a second end such that each of the pressure and suction side walls of the tip cap narrows from a first thickness to a second thickness.

    Segmented leading edge guards
    3.
    发明授权
    Segmented leading edge guards 有权

    公开(公告)号：US12044147B1

    公开(公告)日：2024-07-23

    申请号：US18176241

    申请日：2023-02-28

    Applicant: General Electric Company

    Inventor： Abhijeet Jayshingrao Yadav ,  Nitesh Jain ,  Nicholas J. Kray ,  Nuthi Srinivas

    IPC: F01D5/28

    CPC classification number: F01D5/288 ,  F05D2220/32 ,  F05D2240/303 ,  F05D2300/611

    Abstract: Examples disclosed herein include a fan blade of a gas turbine engine. The disclosed fan blade includes a main body having a leading edge and a trailing edge. The fan blade includes a leading edge guard covering the leading edge and a leading section of the main body adjacent to the leading edge. The leading edge guard includes a plurality of leading edge guard segments consecutively arranged in a spanwise direction along the leading edge of the fan blade. Each of the plurality of leading edge guard segments are oriented at an angle relative to a root of the fan blade. Each of the plurality of leading edge guard segments includes a nose portion coupled to the leading edge and a wing portion coupled to opposing sides of the leading section of the main body.

    Pitch change mechanism for a fan of a gas turbine engine
    8.
    发明授权
    Pitch change mechanism for a fan of a gas turbine engine 有权

    公开(公告)号：US11970956B2

    公开(公告)日：2024-04-30

    申请号：US18146511

    申请日：2022-12-27

    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.

    Part-span shrouds for pitch controlled aircrafts
    9.
    发明授权
    Part-span shrouds for pitch controlled aircrafts 有权

    公开(公告)号：US11913355B2

    公开(公告)日：2024-02-27

    申请号：US17947589

    申请日：2022-09-19

    Applicant: General Electric Company

    Inventor： Nicholas J. Kray ,  Nitesh Jain ,  Gary W. Bryant

    IPC: F01D5/22 ,  F01D5/16

    CPC classification number: F01D5/225 ,  F01D5/16

    Abstract: Part-span shrouds for pitch controlled aircrafts are disclosed herein. An example apparatus includes a first portion extending from a first airfoil, the first portion including a first surface, the first surface being convex, a second portion extending from a second airfoil towards the first airfoil, the second portion including a second surface the first airfoil circumferentially adjacent to the second airfoil, the second surface being concave, and an interface formed by the first surface and the second surface, the interface reacting circumferential loads between the first airfoil and the second airfoil.

    COMPONENT FORMED FROM HYBRID MATERIAL
    10.
    发明申请
    COMPONENT FORMED FROM HYBRID MATERIAL 有权

    公开(公告)号：US20220298926A1

    公开(公告)日：2022-09-22

    申请号：US17207911

    申请日：2021-03-22

    Applicant: General Electric Company

    Inventor： Nitesh Jain ,  Nicholas Joseph Kray

    IPC: F01D21/04

    Abstract: Hybrid material components and methods of forming hybrid material components are provided. For example, a hybrid material component comprises a plurality of metallic tows and a plurality of non-metallic tows. Each metallic tow of the plurality of metallic tows is surrounded by a portion of the plurality of non-metallic tows such that the plurality of metallic tows are embedded within the plurality of non-metallic tows. An exemplary hybrid material component is a containment assembly of a gas turbine engine. Methods of forming such components include forming a hybrid material; laying up a plurality of layers of the material to form a layup; and processing the layup such that a plurality of metallic tows and a plurality of non-metallic tows are co-cured.

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