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    HYBRID ELECTRIC IDLE AND BRAKING FOR AN AIRCRAFT
    3.
    发明申请
    HYBRID ELECTRIC IDLE AND BRAKING FOR AN AIRCRAFT 有权

    公开(公告)号：US20220356849A1

    公开(公告)日：2022-11-10

    申请号：US17314202

    申请日：2021-05-07

    Applicant: Raytheon Technologies Corporation

    Inventor： Jonathan Gilson ,  Zubair Ahmed Baig ,  Martin Richard Amari ,  Michael Winter

    IPC: F02C7/32 ,  B64D27/24 ,  B64D27/16 ,  F01D15/10 ,  F01D19/02

    Abstract: An engine system of an aircraft includes an energy storage system, a gas turbine engine, and a controller. The gas turbine engine includes a low spool, a high spool, a low-spool generator operably coupled to the low spool, and a high-spool electric motor operably coupled to the high spool. The controller is configured to detect a braking condition of the aircraft, transfer power from the low-spool generator to the energy storage system based on the storage capacity state of the energy storage system, and transfer power to the high spool through the high-spool electric motor to support combustion in the gas turbine engine while a rotational speed of the low spool is reduced responsive to the low-spool generator extracting energy from the low spool.

    ELECTRIC MACHINES FOR AIRCRAFT ENGINE FAULT DETECTION
    5.
    发明公开
    ELECTRIC MACHINES FOR AIRCRAFT ENGINE FAULT DETECTION 审中-公开

    公开(公告)号：US20230227171A1

    公开(公告)日：2023-07-20

    申请号：US17846250

    申请日：2022-06-22

    Applicant: Raytheon Technologies Corporation

    Inventor： Zubair Ahmed Baig ,  Martin Richard Amari ,  Michael Winter

    IPC: B64D31/06 ,  B64D27/10 ,  B64D27/24

    CPC classification number: B64D31/06 ,  B64D27/10 ,  B64D27/24 ,  B64D2027/026

    Abstract: Methods and systems for monitoring operation of hybrid electric engines of aircraft. The methods include monitoring a motor condition of an electrical power system associated with an engine condition using a motor sensor, wherein the electrical power system comprises an electric machine operably coupled to at least one shaft of an engine core, wherein the electric machine is configured to at least one of add power to the at least one shaft and extract power from the at least one shaft, receiving motor data from the motor sensor at a motor controller, wherein the motor controller is configured to control operation of, at least, the electric machine, analyzing the motor data to determine the presence of a fault in the engine core, and, when a fault is detected, performing a fault response action.

    HYBRID ELECTRIC SINGLE ENGINE DESCENT ENERGY MANAGEMENT
    10.
    发明申请
    HYBRID ELECTRIC SINGLE ENGINE DESCENT ENERGY MANAGEMENT 有权

    公开(公告)号：US20230139190A1

    公开(公告)日：2023-05-04

    申请号：US17976213

    申请日：2022-10-28

    Applicant: Raytheon Technologies Corporation

    Inventor： Martin Richard Amari ,  Zubair Ahmed Baig

    IPC: B64D27/24 ,  H02J7/14 ,  B60L50/15

    Abstract: A system of a hybrid aircraft includes a first gas turbine engine, a second gas turbine engine, a power source, and a controller. The first gas turbine engine includes a first electric machine. The second gas turbine engine includes a second electric machine. The controller is operable to determine an operating condition of the first gas turbine engine and the second gas turbine engine and to detect a change in a thrust command for the hybrid aircraft. The controller is further operable to determine an adjustment to the second electric machine to compensate for the change in the thrust command while the first gas turbine engine is operating in a fuel-driven mode and the second gas turbine engine is operating in an electrically-driven mode. At least a portion of electric power to perform the adjustment to the second electric machine is extracted from the power source.

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