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    Fan assembly for an engine having redundant trunnion retention
    11.
    发明授权
    Fan assembly for an engine having redundant trunnion retention 有权

    公开(公告)号：US12264590B2

    公开(公告)日：2025-04-01

    申请号：US18366800

    申请日：2023-08-08

    Applicant: General Electric Company

    Inventor： Abhijeet Jayshingrao Yadav ,  Nicholas Joseph Kray ,  Nitesh Jain

    IPC: B64C11/06 ,  F01D21/04 ,  F04D29/18 ,  F04D29/46

    Abstract: A fan assembly for an engine has a fan blade, a disk having a disk segment, a trunnion mechanism having a trunnion extending at least partially through the disk segment, and first and second attachment systems. The trunnion has a platform and a shaft. The fan blade is adjacent to the platform of the trunnion. The trunnion is attached to the disk segment using the first attachment system along a preload path. The first and second attachment systems further include first and second retention features, respectively, separate from the preload path. During normal operation of the fan assembly, the first attachment system retains the trunnion within the disk along a first load path. Upon a failure in the trunnion, the first and second retention features together retain the trunnion within the disk segment along a second load path, the first load path being different than the second load path.

    FAN ASSEMBLY FOR AN ENGINE HAVING REDUNDANT TRUNNION RETENTION
    12.
    发明申请
    FAN ASSEMBLY FOR AN ENGINE HAVING REDUNDANT TRUNNION RETENTION 有权

    公开(公告)号：US20250052172A1

    公开(公告)日：2025-02-13

    申请号：US18366800

    申请日：2023-08-08

    Applicant: General Electric Company

    Inventor： Abhijeet Jayshingrao Yadav ,  Nicholas Joseph Kray ,  Nitesh Jain

    IPC: F01D17/00 ,  F04D29/18 ,  F04D29/20

    Abstract: A fan assembly for an engine has a fan blade, a disk having a disk segment, a trunnion mechanism having a trunnion extending at least partially through the disk segment, and first and second attachment systems. The trunnion has a platform and a shaft. The fan blade is adjacent to the platform of the trunnion. The trunnion is attached to the disk segment using the first attachment system along a preload path. The first and second attachment systems further include first and second retention features, respectively, separate from the preload path. During normal operation of the fan assembly, the first attachment system retains the trunnion within the disk along a first load path. Upon a failure in the trunnion, the first and second retention features together retain the trunnion within the disk segment along a second load path, the first load path being different than the second load path.

    FRANGIBLE AIRFOIL
    16.
    发明申请
    FRANGIBLE AIRFOIL 有权

    公开(公告)号：US20230003132A1

    公开(公告)日：2023-01-05

    申请号：US17366525

    申请日：2021-07-02

    Applicant: General Electric Company

    Inventor： Nitesh Jain ,  Abhijeet Jayshingrao Yadav ,  Nicholas Joseph Kray ,  Ch K Phani Sri Krishna

    IPC: F01D5/28 ,  F01D5/14

    Abstract: An airfoil including a plurality of composite plies extending from a leading edge to a trailing edge and between a tip and a root. The airfoil further includes a frangible airfoil portion at the tip extending between the leading edge and the trailing edge and extending between the tip and a frangible line along a span including a first plurality of composite plies. The frangible airfoil portion includes a first plurality of composite plies including fibers having a first fiber modulus. The airfoil further includes a residual airfoil portion extending from the frangible line to the root along the span including a second plurality of composite plies. The second plurality of composite plies including one or more plies having a second fiber modulus. The second fiber modulus is greater than the first fiber modulus. Further, the residual airfoil portion meets the frangible airfoil portion at the frangible line.

    ENGINE MOUNT SYSTEM FOR IMPROVED PROPELLER WHIRL STABILITY
    17.
    发明申请
    ENGINE MOUNT SYSTEM FOR IMPROVED PROPELLER WHIRL STABILITY 有权

    公开(公告)号：US20250153854A1

    公开(公告)日：2025-05-15

    申请号：US18441853

    申请日：2024-02-14

    Applicant: General Electric Company

    Inventor： Abhishek Goverdhan ,  Abhijeet Jayshingrao Yadav ,  Andrew Bryan Cannella ,  Richa Awasthi ,  Rangasai M C ,  Pamela M. Boehm ,  Narayanan P ,  Saswati Roy

    IPC: B64D27/40 ,  F02C7/20

    Abstract: Active control apparatus of gas turbine engine mounts are disclosed. An example apparatus for mounting a casing of an unducted gas turbine engine to a pylon, the apparatus includes a mount system; a plurality of sensors to measure at least one parameter indicating propeller whirl stability; and a controller to tune a stiffness of the mount system depending on a function of the at least one parameter measured by the plurality of sensors, the controller to tune the stiffness of the mount system by signaling an actuator, the mount system including: a first linkage; a second linkage; a first pin; a second pin; an interface to engage with the first and second linkages, the interface to at least one of rotate or slide; and the actuator to cause the interface to engage with the first and second linkages based on the signaling from the controller.

    Segmented leading edge guards
    19.
    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.

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