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    HYBRID ELECTRIC AIRCRAFT WITH GYROSCOPIC STABILIZATION CONTROL
    87.
    发明申请
    HYBRID ELECTRIC AIRCRAFT WITH GYROSCOPIC STABILIZATION CONTROL 有权

    公开(公告)号：US20250026470A1

    公开(公告)日：2025-01-23

    申请号：US18439870

    申请日：2024-02-13

    Applicant: General Electric Company ,  GE Avio S.r.l.

    Inventor： Mehdi Milani Baladi ,  Randy M. Vondrell

    IPC: B64C17/06 ,  B64C29/00 ,  B64D27/02 ,  B64D27/14 ,  B64D27/24 ,  B64D31/02

    Abstract: A hybrid electric aircraft equipped with gyroscopic stabilization control is provided. In one aspect, a hybrid electric aircraft includes a turbo-generator having a gas turbine engine and an electric generator operatively coupled thereto for generating electrical power. The turbo-generator defines a rotation axis. The aircraft also includes one or more electrically-driven propulsors for producing thrust for the aircraft. In addition, the aircraft includes a pivot mount operatively coupled with the turbo-generator. To provide gyroscopic stabilization control of the aircraft, the pivot mount is controlled to adjust the rotation axis of the turbo-generator relative to a prime stability axis of the aircraft. Additionally or alternatively, a rotational speed of the turbo-generator can be changed to provide gyroscopic stabilization control of the aircraft.

    Gas turbine engine
    88.
    发明授权
    Gas turbine engine 有权

    公开(公告)号：US12104539B2

    公开(公告)日：2024-10-01

    申请号：US17972720

    申请日：2022-10-25

    Applicant: General Electric Company

    Inventor： Daniel John Oehrle ,  Randy M. Vondrell

    IPC: F02C7/32 ,  B64D27/12

    CPC classification number: F02C7/32 ,  B64D27/12

    Abstract: A gas turbine engine defines an axial direction and a radial direction and comprises a turbomachine having an unducted primary fan, a core engine a combustor casing enclosing a combustor and defining an outer surface, a core cowl surrounding at least a portion of the core engine. The outer surface of the core cowl defines a peak cowl diameter (D) in the radial direction, and the outer surface of the combustor casing defines a maximum combustor casing diameter (d) along the radial direction. The core engine defines an overall core axial length (L) along the axial direction and an under-core cowl axial length (L1) along the axial direction. The gas turbine engine defines a core cowl diameter ratio (CDR) equal to the peak cowl diameter (D) divided by the maximum combustor casing diameter (d) and a core cowl length ratio (CLR) equal to the under-core cowl axial length (L1) divided by the overall core axial length (L). The CDR is between 2.7 and 3.5 and the CLR is between 0.25 and 0.50.

    GAS TURBINE ENGINE WITH THIRD STREAM
    89.
    发明公开
    GAS TURBINE ENGINE WITH THIRD STREAM 审中-公开

    公开(公告)号：US20240309829A1

    公开(公告)日：2024-09-19

    申请号：US18675270

    申请日：2024-05-28

    Applicant: General Electric Company

    Inventor： Brandon Wayne Miller ,  Randy M. Vondrell ,  David Marion Ostdiek ,  Craig William Higgins ,  Alexander Kimberley Simpson

    IPC: F02K3/065 ,  F02C3/06

    CPC classification number: F02K3/065 ,  F02C3/06

    Abstract: A gas turbine engine is provided. The gas turbine engine includes a turbomachine defining an engine inlet to an inlet duct, a fan duct inlet to a fan duct, and a core inlet to a core duct; a primary fan driven by the turbomachine; and a secondary fan located downstream of the primary fan within the inlet duct. The gas turbine engine defines a thrust to power airflow ratio between 3.5 and 100 and a core bypass ratio between 0.1 and 10, wherein the thrust to power airflow ratio is a ratio of an airflow through a bypass passage over the turbomachine plus an airflow through the fan duct to an airflow through the core duct, and wherein the core bypass ratio is a ratio of the airflow through the fan duct to the airflow through the core duct.

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