REVERSE FLOW GAS TURBINE ENGINE HAVING ELECTRIC MACHINE

    公开(公告)号:US20250122831A1

    公开(公告)日:2025-04-17

    申请号:US18990439

    申请日:2024-12-20

    Abstract: An aircraft engine assembly includes a gas turbine engine having an intake channel configured to receive an incoming flow of air and form an intake flow of air, the intake channel configured to turn the received incoming flow of air from an incoming flow direction to a first axial direction of the gas turbine engine, the incoming flow direction reverse of the first axial direction, and an electric machine coupled with the low pressure shaft and located at the aft end of the gas turbine engine proximate the intake channel, the electric machine in heat exchange communication with the intake flow of air such that the electric machine transfers heat to the incoming flow of air within the intake channel when the electric machine is operated.

    Turbine engine screen
    50.
    发明授权

    公开(公告)号:US12276227B1

    公开(公告)日:2025-04-15

    申请号:US18592663

    申请日:2024-03-01

    Inventor: Tomasz Iglewski

    Abstract: A screen for an aeronautical gas turbine engine includes a plurality of first filaments and a plurality of second filaments. The plurality of second filaments define a plurality of openings with the plurality of first filaments. The plurality of first filaments and the plurality of second filaments define a first arrangement in which the plurality of first filaments are perpendicular to the plurality of second filaments. Upon application of a force to the screen, at least some of the plurality of first filaments and at least some of the plurality of second filaments are configured to translate from the first arrangement to a second arrangement in which a size of at least one of the openings is configured to change from a first size to a second size.

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