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    Turbine engine with a blade having woven core and toughened region
    112.
    发明授权
    Turbine engine with a blade having woven core and toughened region 有权

    公开(公告)号：US12297749B2

    公开(公告)日：2025-05-13

    申请号：US18966717

    申请日：2024-12-03

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Arthur William Sibbach ,  Nicholas Joseph Kray ,  Gregory Carl Gemeinhardt

    IPC: F01D5/28

    Abstract: A turbine engine comprising a compressor section, combustor section, and turbine section in serial flow arrangement, and defining an engine longitudinal axis. The turbine engine includes an airfoil with an outer wall having a pressure side and a suction side, extending between a root and a tip in a span-wise direction, and extending between a leading edge and a trailing edge in a chord-wise direction. The airfoil includes a woven core, a first bonding layer including a toughened region, and a laminate skin provided exterior of the first bonding layer and bonded to the woven core by the first bonding layer.

    Monolithic composite blade and platform
    113.
    发明授权
    Monolithic composite blade and platform 有权

    公开(公告)号：US12264597B2

    公开(公告)日：2025-04-01

    申请号：US18070618

    申请日：2022-11-29

    Applicant: General Electric Company

    Inventor： Gregory Carl Gemeinhardt ,  Nicholas Joseph Kray ,  Andreas Mastorakis

    IPC: F01D5/28 ,  F02C3/04

    Abstract: A component for a gas turbine engine. The component includes a continuous fiber blade including an airfoil extending radially between a root and a tip and a blade attachment feature positioned at or adjacent to the root. The component further includes a platform coupled to the root of the continuous fiber blade. The platform includes a plurality of chopped fibers. Additionally, the component includes a thermoplastic polymer contained in both the continuous fiber blade and the platform. Moreover, the continuous fiber blade and platform are coupled together such that the continuous fiber blade and platform form a monolithic composite body.

    Fan assembly for an engine having redundant trunnion retention
    114.
    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.

    Turbine engine airfoil with a woven core and woven layer
    115.
    发明授权
    Turbine engine airfoil with a woven core and woven layer 有权

    公开(公告)号：US12241386B2

    公开(公告)日：2025-03-04

    申请号：US18171938

    申请日：2023-02-21

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Nicholas Joseph Kray ,  Arthur William Sibbach

    IPC: F01D5/28 ,  F01D5/14

    Abstract: A gas turbine engine includes a compressor section, combustor section, and turbine section in serial flow arrangement, and defining an engine longitudinal axis. Sets of blades can be rotatably driven about the longitudinal axis in the compressor section and the turbine section, with adjacent vanes provided between sets of blades. The airfoil structure defining one or more of the blades or vanes can include a core structure which includes a woven or foam core, with an exterior woven layer.

    FAN ASSEMBLY FOR AN ENGINE HAVING REDUNDANT TRUNNION RETENTION
    118.
    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.

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