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    ROTOR DYNAMICS ACCOMMODATION USING ELECTRICAL POWER ASSIST
    14.
    发明申请
    ROTOR DYNAMICS ACCOMMODATION USING ELECTRICAL POWER ASSIST 有权

    公开(公告)号：US20210047970A1

    公开(公告)日：2021-02-18

    申请号：US16991275

    申请日：2020-08-12

    Applicant: Raytheon Technologies Corporation

    Inventor： Gary Collopy ,  Arthur M. Salve, JR. ,  Michael Winter

    IPC: F02C7/36 ,  B64D27/02

    Abstract: Hybrid electric propulsion systems are described. The systems include a gas turbine engine having low and high speed spools, each spool having a respective compressor and turbine. A mechanical power transmission is configured to at least one of extract power from and supply power to at least one of the low speed spool and the high speed spool, an electric machine is configured to augment rotational power of at least one of the spools, and a controller is operable to determine a rotational speed of the low speed spool, determine a rotational speed of the high speed spool, determine if a predetermined operational zone of operation based on the determined rotational speeds is present, and when a predetermined operational zone is determined, control a power augmentation of at least one spool to limit dwell operation of the gas turbine engine within the predetermined operational zone.

    HYBRID GAS TURBINE ENGINE STARTING CONTROL
    15.
    发明申请
    HYBRID GAS TURBINE ENGINE STARTING CONTROL 有权

    公开(公告)号：US20210025339A1

    公开(公告)日：2021-01-28

    申请号：US16936602

    申请日：2020-07-23

    Applicant: Raytheon Technologies Corporation

    Inventor： Neil Terwilliger ,  Gary Collopy

    IPC: F02C9/44 ,  F02C7/236 ,  F02C7/264

    Abstract: A system includes a gas turbine engine having a low speed spool, a high speed spool, and a combustor. The system also includes a low spool motor configured to augment rotational power of the low speed spool. The system further includes a controller configured to cause fuel flow. The controller is operable to control the low spool motor to drive rotation of the low speed spool responsive to a thrust command while the controller does not command fuel flow to the combustor.

    HYBRID GAS TURBINE ENGINE STARTING CONTROL
    18.
    发明公开
    HYBRID GAS TURBINE ENGINE STARTING CONTROL 审中-公开

    公开(公告)号：US20230160358A1

    公开(公告)日：2023-05-25

    申请号：US18151652

    申请日：2023-01-09

    Applicant: Raytheon Technologies Corporation

    Inventor： Neil Terwilliger ,  Gary Collopy

    IPC: F02K5/00 ,  F01D19/00 ,  F01D25/36 ,  F02C7/26 ,  F02C7/32 ,  F02C9/28

    CPC classification number: F02K5/00 ,  F01D19/00 ,  F01D25/36 ,  F02C7/26 ,  F02C7/32 ,  F02C9/28 ,  B64D2027/026

    Abstract: A system includes a gas turbine engine of an aircraft, the gas turbine engine having a low speed spool, a high speed spool, and a combustor. The system also includes a low spool motor configured to augment rotational power of the low speed spool and a high spool motor configured to augment rotational power of the high speed spool. The system further includes a controller configured to cause fuel flow. The controller is configured to control a thrust response of the gas turbine engine to a thrust target between zero and a thrust level to move the aircraft during engine start and during engine idle. The controller is also configured to control the low spool motor to drive rotation of the low speed spool responsive to a thrust command while the controller does not command fuel flow to the combustor.

    SURGE RECOVERY SYSTEM AND METHODS
    19.
    发明申请
    SURGE RECOVERY SYSTEM AND METHODS 有权

    公开(公告)号：US20220349354A1

    公开(公告)日：2022-11-03

    申请号：US17867507

    申请日：2022-07-18

    Applicant: RAYTHEON TECHNOLOGIES CORPORATION

    Inventor： Michael M. Romero ,  Gary Collopy

    IPC: F02C9/16 ,  F02C7/32

    Abstract: A surge control system includes a rotor system with at least one compressor section and at least one turbine section operably coupled to a shaft. The surge control system also includes sensors configured to collect sensor data from the rotor system, an electric motor operably coupled to the rotor system, and a controller. The controller is operable to detect surge event from the sensor data, determine an amount of power to apply to the rotor system, and increase the amount of power provided to the rotor system to recover from the surge event.

    ELECTRIC POWER ASSIST FOR IN-FLIGHT ENGINE RE-START
    20.
    发明申请
    ELECTRIC POWER ASSIST FOR IN-FLIGHT ENGINE RE-START 有权

    公开(公告)号：US20210115857A1

    公开(公告)日：2021-04-22

    申请号：US16991143

    申请日：2020-08-12

    Applicant: Raytheon Technologies Corporation

    Inventor： Gary Collopy

    IPC: F02C7/262 ,  F02C6/20 ,  F02C7/268

    Abstract: A hybrid electric propulsion system including: a gas turbine engine comprising a low speed spool and a high speed spool, the low speed spool comprising a low pressure compressor and a low pressure turbine, and the high speed spool comprising a high pressure compressor and a high pressure turbine; an electric motor configured to augment rotational power of the high speed spool or the low speed spool; and a controller to: detect an in-flight windmill re-start condition of the gas turbine engine; and cause power to be supplied from a power source to the electric motor in order to augment rotational power of the high speed or the low speed spool during the detected in-flight windmill re-start condition.

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