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    NESTED CONTROL LOOP STRUCTURE FOR HYBRID PROPULSION SYSTEM
    41.
    发明申请
    NESTED CONTROL LOOP STRUCTURE FOR HYBRID PROPULSION SYSTEM 有权

    公开(公告)号：US20230058484A1

    公开(公告)日：2023-02-23

    申请号：US17404145

    申请日：2021-08-17

    Applicant: Pratt & Whitney Canada Corp.

    Inventor： Richard Freer

    IPC: B60L58/13 ,  B60L15/20 ,  B64D27/24 ,  B64D31/00 ,  B64C27/54

    Abstract: In accordance with at least one aspect of the present disclosure, there is provided a method for controlling power in an aircraft. The method includes, monitoring an electric energy storage module electrically connected to an electrical bus for an exceedance of a first current limit and monitoring a generator module connected to the electrical bus for an exceedance of a second current limit. If the current limit of either of the electric energy storage module or the generator module is exceeded by a predetermined exceedance amount, the method includes reducing a power consumption for an electric machine by a predetermined bias until the exceedance of the electrical energy storage and the exceedance of the generator module are both less than or equal to zero.

    CONTROL FOR ELECTRICALLY ASSISTED TURBINES
    42.
    发明申请
    CONTROL FOR ELECTRICALLY ASSISTED TURBINES 有权

    公开(公告)号：US20230047326A1

    公开(公告)日：2023-02-16

    申请号：US17402483

    申请日：2021-08-13

    Applicant: Pratt & Whitney Canada Corp.

    Inventor： Richard Freer

    IPC: F02C9/28 ,  F02C7/22 ,  F01D15/10

    Abstract: In accordance with at least one aspect of this disclosure, there is provided a method of accelerating a gas turbine engine. The method includes adding torque to a core of the gas turbine engine to accelerate rotation of the core by controlling fuel flow to a plurality of fuel injectors of the gas turbine engine. The method also includes adding torque to the core by powering an electric machine that is operatively connected to the core. In embodiments, controlling fuel flow to the plurality of fuel injectors is based on feedback from the electric machine.

    Igniter for gas turbine engine
    43.
    发明授权
    Igniter for gas turbine engine 有权

    公开(公告)号：US11408351B2

    公开(公告)日：2022-08-09

    申请号：US16370046

    申请日：2019-03-29

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Michel Bousquet ,  Richard Freer

    IPC: F02C7/264 ,  F23Q7/00

    Abstract: There is disclosed an igniter for a gas turbine engine including: a base; an inner conductor extending along an axis from the base to an end; a resistive heating element electrically connected to the end of the conductor; an outer conductor being electrically connected to the heating element, the outer conductor surrounding and extending axially along the inner conductor and forming a return electrical path, the outer conductor being radially spaced apart from the inner conductor by a gap, and an electrical insulator in the gap.

    System and method for controlling a propulsor for a hybrid-electric aircraft propulsion system
    46.
    发明授权
    System and method for controlling a propulsor for a hybrid-electric aircraft propulsion system 有权

    公开(公告)号：US12296941B2

    公开(公告)日：2025-05-13

    申请号：US18196740

    申请日：2023-05-12

    Applicant: Pratt & Whitney Canada Corp.

    Inventor： Richard Freer

    IPC: B64C11/30 ,  B64D27/10 ,  B64D27/24 ,  B64D31/00 ,  B64D27/02

    Abstract: An assembly for an aircraft propulsion system includes a propulsor, an engine, and electrical distribution system, and a controller. The propulsor is configured for rotation about a rotational axis. The engine includes a rotor coupled with the propulsor. The electrical distribution system includes an electric motor. The electric motor is coupled with the propulsor. The electric motor and the rotor are configured to cooperatively control rotation of the propulsor about the rotational axis by applying a total torque to the propulsor. The total torque includes a motor torque of the electric motor and an engine torque of the rotor. The controller is configured to: identify a target rotation speed for the propulsor, identify a deviation of an actual rotation speed of the propulsor from the identified target rotation speed, change a target total torque for the propulsor, control the engine to change an actual engine torque of the rotor to the target total torque, and while controlling the engine to change the actual engine torque of the rotor to the target total torque, identify a torque difference between the actual engine torque and the target total torque and control the electric motor to apply a target motor torque to the propulsor based on the torque difference.

    SYSTEM AND METHOD FOR CONTROLLING A PROPULSOR FOR A HYBRID-ELECTRIC AIRCRAFT PROPULSION SYSTEM
    47.
    发明申请
    SYSTEM AND METHOD FOR CONTROLLING A PROPULSOR FOR A HYBRID-ELECTRIC AIRCRAFT PROPULSION SYSTEM 有权

    公开(公告)号：US20240375766A1

    公开(公告)日：2024-11-14

    申请号：US18196740

    申请日：2023-05-12

    Applicant: Pratt & Whitney Canada Corp.

    Inventor： Richard Freer

    IPC: B64C11/30 ,  B64D27/10 ,  B64D27/24 ,  B64D31/00

    Abstract: An assembly for an aircraft propulsion system includes a propulsor, an engine, and electrical distribution system, and a controller. The propulsor is configured for rotation about a rotational axis. The engine includes a rotor coupled with the propulsor. The electrical distribution system includes an electric motor. The electric motor is coupled with the propulsor. The electric motor and the rotor are configured to cooperatively control rotation of the propulsor about the rotational axis by applying a total torque to the propulsor. The total torque includes a motor torque of the electric motor and an engine torque of the rotor. The controller is configured to: identify a target rotation speed for the propulsor, identify a deviation of an actual rotation speed of the propulsor from the identified target rotation speed, change a target total torque for the propulsor, control the engine to change an actual engine torque of the rotor to the target total torque, and while controlling the engine to change the actual engine torque of the rotor to the target total torque, identify a torque difference between the actual engine torque and the target total torque and control the electric motor to apply a target motor torque to the propulsor based on the torque difference.

    Aircraft propulsion system with intermittent combustion engine and electric transmission system and method for operating the same
    48.
    发明授权
    Aircraft propulsion system with intermittent combustion engine and electric transmission system and method for operating the same 有权

    公开(公告)号：US12139265B2

    公开(公告)日：2024-11-12

    申请号：US18367657

    申请日：2023-09-13

    Applicant: Pratt & Whitney Canada Corp.

    Inventor： Richard Freer

    IPC: F02C5/06 ,  B64D27/08 ,  B64D27/20 ,  B64D27/24 ,  B64D33/08 ,  B64D27/02

    Abstract: An aircraft propulsion system for an aircraft having a nacelle that includes a pylon structure is provided. The system includes compressor and turbine sections, an IC engine, a fan, and an IC engine cooling system. The compressor section is powered by a first electric motor. The turbine section is configured to power a first electric generator configured to produce electrical power. The first fan is rotationally driven by a second electric motor. The fan has a hub and a plurality of fan blades extending radially outward from the hub. The hub is disposed in the pylon interior region and the fan blades are configured to extend outside of the pylon structure. The fan is positioned downstream of the compressor section. The IC engine cooling system has a heat exchanger and a pump configured to provide coolant communication between the IC engine and the heat exchanger.

    AIRCRAFT BATTERY CHARGING SYSTEM AND METHOD
    49.
    发明公开
    AIRCRAFT BATTERY CHARGING SYSTEM AND METHOD 审中-公开

    公开(公告)号：US20240332986A1

    公开(公告)日：2024-10-03

    申请号：US18435563

    申请日：2024-02-07

    Applicant: Pratt & Whitney Canada Corp.

    Inventor： Simon Lam ,  Remi Robache ,  Antwan Shenouda ,  Richard Freer ,  Raphael Gariepy

    IPC: H02J7/00 ,  H01M10/44 ,  H01M50/249 ,  H01M50/512

    CPC classification number: H02J7/0013 ,  H01M10/441 ,  H01M50/249 ,  H01M50/512 ,  H02J7/007182

    Abstract: An assembly for an aircraft includes a battery, a charger, and a battery monitoring system. The battery includes a plurality of battery strings. The charger is configured to charge the plurality of battery strings. The battery monitoring system further includes a processor in communication with a non-transitory memory storing instructions, which instructions when executed by the processor, cause the processor to determine the battery string voltage for each battery string of the plurality of battery strings and identify a battery string voltage hierarchy for the plurality of battery strings, the battery string voltage hierarchy identifying at least a lowest-voltage battery string of the plurality of battery strings, at least one intermediate-voltage battery string of the plurality of battery strings, and a highest-voltage battery string of the plurality of battery strings, and sequentially charge the plurality of battery strings with the charger based on the battery string voltage hierarchy.

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