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    ELECTRIC MACHINE SYSTEMS
    2.
    发明申请
    ELECTRIC MACHINE SYSTEMS 有权

    公开(公告)号：US20210226519A1

    公开(公告)日：2021-07-22

    申请号：US17225490

    申请日：2021-04-08

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Eric LATULIPE ,  Richard FREER

    IPC: H02K29/03 ,  F16H1/22 ,  H02K7/116 ,  H02K16/02

    Abstract: An electric machine system described herein comprises a first and second electric machines configured to drive a load. The first electric machine has a plurality of first rotors driven using electric power having a first phase. The second electric machine has a plurality of second rotors driven using electric power having a second phase. The second phase differs from the first phase. Each of one or more shafts connects a first rotor with a second rotor. The first rotor is coaxial with and axially spaced apart from the second rotor.

    ELECTRIC MACHINE SYSTEMS
    3.
    发明申请
    ELECTRIC MACHINE SYSTEMS 审中-公开

    公开(公告)号：US20200186018A1

    公开(公告)日：2020-06-11

    申请号：US16212802

    申请日：2018-12-07

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Eric LATULIPE ,  Richard FREER

    IPC: H02K29/03 ,  H02K7/116 ,  H02K16/02 ,  F16H1/22

    Abstract: An electric machine system described herein comprises a first electric machine rotor, a first gear and a second gear. The first gear is connected to the first electric machine rotor and to a first input/output shaft. The second gear is connected to the first electric machine rotor and to a second input/output shaft. The first electric machine rotor is disposed between the first gear and the second gear.

    HYBRID POWER PLANT FOR AIRCRAFT
    6.
    发明申请
    HYBRID POWER PLANT FOR AIRCRAFT 有权

    公开(公告)号：US20210388733A1

    公开(公告)日：2021-12-16

    申请号：US17156933

    申请日：2021-01-25

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Patrick VALOIS ,  Hervé TURCOTTE ,  Richard FREER ,  Jonatan TREMBLAY ,  Eric LATULIPE

    IPC: F01D15/10 ,  F01D15/12 ,  F02C3/073

    Abstract: An hybrid aircraft power plant, has: a gas turbine engine having a high-pressure spool including a high-pressure compressor, a high-pressure turbine, and a high-pressure shaft drivingly engaging the high-pressure turbine to the high-pressure compressor, a low-pressure spool including a low-pressure compressor, a low-pressure turbine, and a low-pressure shaft drivingly engaging the low-pressure turbine to the low-pressure compressor; an electric motor drivingly engaged to the low-pressure shaft; and a torque-transmitting device operatively connected to the HP-shaft and having an engaged configuration in which the torque-transmitting device drivingly engages the electric motor to the high-pressure shaft and a disengaged configuration in which the torque-transmitting device disconnects the electric motor from the high-pressure shaft.

    OPERATION OF A HYBRID ELECTRIC AIRCRAFT PROPULSION SYSTEM
    7.
    发明申请
    OPERATION OF A HYBRID ELECTRIC AIRCRAFT PROPULSION SYSTEM 审中-公开

    公开(公告)号：US20200083823A1

    公开(公告)日：2020-03-12

    申请号：US16411275

    申请日：2019-05-14

    Applicant: PRATT & WHITNEY CANADA CORP

    Inventor： Eric LATULIPE ,  Richard FREER

    IPC: H02P6/12 ,  B64D35/08 ,  H02K47/04

    Abstract: Methods and systems for operating a hybrid electric aircraft propulsion system. The method comprises providing alternating current (AC) electric power to a first electric motor to drive a first rotating propulsor, providing the first electric motor with AC electric power from at least one motor inverter operatively coupled to a direct current (DC) power source, detecting a failure in a path to the first electric motor, and selectively rearranging a first switching arrangement between the generator, the at least one motor inverter, and the first electric motor.

    ELECTRIC MACHINE SYSTEMS
    8.
    发明申请
    ELECTRIC MACHINE SYSTEMS 有权

    公开(公告)号：US20210234449A1

    公开(公告)日：2021-07-29

    申请号：US17231705

    申请日：2021-04-15

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Eric LATULIPE ,  Richard FREER

    IPC: H02K29/03 ,  F16H1/22 ,  H02K7/116 ,  H02K16/02

    Abstract: An electric machine system disclosed herein comprises first and second electric machines configured to drive a load. The first electric machine has a plurality of first rotors. The second electric machine has a plurality of second rotors. At least one of the second rotors is indexed relative to a respective one of the first rotors to, in use, provide a torque phase offset between the first and second electric machines. A shaft is coupled to the load and connects the respective one of the first rotors with the at least one of the second rotors. The respective one of the first rotors is coaxial with and axially spaced apart from the at least one of the second rotors.

    MULTI-ROTOR ELECTRICAL MACHINE WITH RADIAL CONFIGURATION
    9.
    发明申请
    MULTI-ROTOR ELECTRICAL MACHINE WITH RADIAL CONFIGURATION 有权

    公开(公告)号：US20210021181A1

    公开(公告)日：2021-01-21

    申请号：US16516501

    申请日：2019-07-19

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Eric LATULIPE

    IPC: H02K16/02

    Abstract: The electric machine includes a plurality of rotors drivingly coupled to a common shaft defining a shaft axis about which the common shaft is rotatable, and a common stator for the plurality of rotors, the common stator extending circumferentially about the common shaft. The rotors are rotatable about respective rotor axes which are substantially perpendicular to the shaft axis.

    HYBRID ELECTRIC AIRCRAFT PROPULSION SYSTEM AND METHOD
    10.
    发明申请
    HYBRID ELECTRIC AIRCRAFT PROPULSION SYSTEM AND METHOD 审中-公开

    公开(公告)号：US20200079514A1

    公开(公告)日：2020-03-12

    申请号：US16411262

    申请日：2019-05-14

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Eric LATULIPE ,  Richard Freer

    IPC: B64D27/02 ,  B64D31/06 ,  B64D27/10 ,  B64D27/24 ,  F01D15/10 ,  F02K3/06 ,  H02P5/74 ,  H02P9/00

    Abstract: There is provided a hybrid electric aircraft propulsion system and method for operating same. The method comprises providing, to a first electric motor and a second electric motor, alternating current (AC) electric power from a generator, the generator receiving rotational power from a thermal engine, providing, to the first electric motor and the second electric motor, AC electric power from at least one motor inverter, the at least one motor inverter configured to convert DC electric power from a DC power source into AC electric power, and selectively driving the first and second electric motors from the generator, the at least one motor inverter, or a combination thereof, wherein the first electric motor drives a first rotating propulsor and the second electric motor drives a second rotating propulsor.

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