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    Exhaust nozzle assembly for an aircraft propulsion system
    1.
    发明授权
    Exhaust nozzle assembly for an aircraft propulsion system 有权

    公开(公告)号：US12103695B2

    公开(公告)日：2024-10-01

    申请号：US17948870

    申请日：2022-09-20

    Applicant: Pratt & Whitney Canada Corp.

    Inventor： Michel Labrecque ,  Kevin Nguyen

    IPC: B64D33/04 ,  B64D27/10 ,  B64D29/00 ,  F02K1/06 ,  F02K1/08 ,  F02K1/09 ,  F02K1/36

    CPC classification number: B64D33/04 ,  B64D27/10 ,  B64D29/00 ,  F02K1/06 ,  F02K1/08 ,  F02K1/09 ,  F02K1/36

    Abstract: An exhaust nozzle assembly for a propulsion system include a primary nozzle, an outer shroud, an ejector nozzle, and an actuator. The primary nozzle extends along an exhaust centerline. The primary nozzle includes a downstream axial end. The outer shroud surrounds the primary nozzle. The ejector nozzle extends axially between a first axial end and a second axial end. The second axial end forms a nozzle exit plane for the exhaust nozzle assembly. The ejector nozzle converges in a direction from the first axial end to the second axial end. The ejector nozzle forms a mixing cross-sectional area between the primary nozzle and the ejector nozzle at the downstream axial end. The actuator is mounted on the ejector nozzle. The actuator is configured to move the ejector nozzle between a first position and a second position, relative to the outer shroud, to control an area of the mixing cross-sectional area.

    Aircraft and associated method of controlling an electric aircraft powerplant
    2.
    发明授权
    Aircraft and associated method of controlling an electric aircraft powerplant 有权

    公开(公告)号：US12071252B1

    公开(公告)日：2024-08-27

    申请号：US18333696

    申请日：2023-06-13

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Eric Sylvain Durocher ,  Michel Labrecque

    IPC: B64C11/30 ,  B64C11/44 ,  B64D27/24

    CPC classification number: B64D27/24 ,  B64C11/305 ,  B64C11/44

    Abstract: The aircraft can include a rotary airfoil device having an output shaft rotatable around an airfoil rotation axis; an electric engine having a source shaft drivingly coupled to the output shaft; a controller in communication with the electric engine; a low voltage electric system operable to power the controller; a high voltage electric system having a high voltage battery operable to power the electric engine, the high voltage battery further operable to power the low voltage electric system via a voltage converter; and an electromagnetic generator having a generator shaft coupled to the output shaft, the electromagnetic generator operable to power the low voltage electric system.

    System and method for synthesizing engine output power
    3.
    发明授权
    System and method for synthesizing engine output power 有权

    公开(公告)号：US11739696B2

    公开(公告)日：2023-08-29

    申请号：US17548786

    申请日：2021-12-13

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Michel Labrecque ,  Kevin Nguyen ,  Ninad Joshi

    IPC: F02C9/16 ,  F02C3/04

    CPC classification number: F02C9/16 ,  F02C3/04 ,  F05D2220/30 ,  F05D2240/35 ,  F05D2270/053 ,  F05D2270/303 ,  F05D2270/3013

    Abstract: A method and a system for synthesizing output power provided by an engine are provided. The engine comprising a compressor section, a combustor, and a turbine section in serial fluid flow communication. The engine is operated and, during the operating of the engine, a pressure of fluid at an exit of the compressor section, a temperature upstream of the exit of the compressor section, and a fuel flow rate to the engine are determined. A synthesized value of output power provided by the engine is determined based on a product of at least a first factor, a second factor, and a third factor, the first factor being a function of the pressure, the second factor being a function of the temperature, and the third factor being a function of the fuel flow rate. The synthesized value of output power provided by the engine is output.

    ELECTRIC MOTOR PROPULSION SYSTEM FOR AN AIRCRAFT
    4.
    发明申请
    ELECTRIC MOTOR PROPULSION SYSTEM FOR AN AIRCRAFT 有权

    公开(公告)号：US20240417083A1

    公开(公告)日：2024-12-19

    申请号：US18209892

    申请日：2023-06-14

    Applicant: Pratt & Whitney Canada Corp.

    Inventor： Eric S. Durocher ,  Michel Labrecque

    IPC: B64D27/24 ,  B64D35/00 ,  F16H1/22 ,  F16H57/038 ,  F16H57/04 ,  H02K7/116

    Abstract: An assembly for a propulsion system of an aircraft includes a gearbox module, an electric motor assembly, a first accessory load assembly, and a propulsor. The gearbox module includes a gear assembly and an output shaft. The gear assembly includes a main gear and a plurality of offset gears. The electric motor assembly includes an electric motor. The electric motor includes a rotor. The rotor is mounted to a first offset gear of the plurality of offset gears. The rotor is configured for rotation about a rotational axis to drive rotation of the gear assembly and the output shaft. The first accessory load assembly includes at least one first accessory load. The at least one first accessory load is mounted to a second offset gear of the plurality of offset gears. The propulsor is coupled to the output shaft.

    ELECTRIC MOTOR PROPULSION SYSTEM FOR AN AIRCRAFT
    5.
    发明申请
    ELECTRIC MOTOR PROPULSION SYSTEM FOR AN AIRCRAFT 有权

    公开(公告)号：US20240409230A1

    公开(公告)日：2024-12-12

    申请号：US18207796

    申请日：2023-06-09

    Applicant: Pratt & Whitney Canada Corp.

    Inventor： Eric S. Durocher ,  Michel Labrecque

    IPC: B64D35/02 ,  B64D27/24

    Abstract: An assembly for a propulsion system of an aircraft includes a gearbox, at least one accessory load assembly, a propulsor, and an electric motor. The gearbox module includes a gear assembly and an output shaft. The gear assembly is connected to the output shaft. The at least one accessory load assembly includes at least one accessory load coupled to the output shaft. The propulsor is coupled to the output shaft. The electric motor includes a rotor. The rotor is coupled to the gear assembly to drive rotation of the output shaft about a rotational axis. The rotation of the output shaft drives rotation of the propulsor and the at least one accessory load for each accessory load assembly of the at least one accessory load assembly.

    Boosting gas turbine engine power with fluid motor
    6.
    发明授权
    Boosting gas turbine engine power with fluid motor 有权

    公开(公告)号：US12146443B2

    公开(公告)日：2024-11-19

    申请号：US18129646

    申请日：2023-03-31

    Applicant: Pratt & Whitney Canada Corp.

    Inventor： Michel Labrecque ,  Patrick Valois ,  Karine Berube

    IPC: F02C7/36 ,  F02C3/10 ,  F02C3/107 ,  F02C7/27 ,  F02C7/32

    Abstract: An aircraft system is provided that includes a thrust rotor and a powerplant coupled to and configured to drive rotation of the thrust rotor. The powerplant includes a gas turbine engine, a drivetrain and a fluid motor. The gas turbine engine includes a rotating assembly, a compressor section, a combustor section, a turbine section and a flowpath extending through the compressor section, the combustor section and the turbine section. The rotating assembly includes a turbine rotor in the turbine section. The turbine rotor is configured to convert fluid power of combustion products flowing through the flowpath within the turbine section into mechanical power for driving rotation of the rotating assembly during a mode of engine operation. The drivetrain is configured to rotatably couple the fluid motor to the rotating assembly. The fluid motor is configured to boost the mechanical power for driving the rotation of the rotating assembly during the mode of engine operation.

    EXHAUST NOZZLE ASSEMBLY FOR AN AIRCRAFT PROPULSION SYSTEM
    7.
    发明公开
    EXHAUST NOZZLE ASSEMBLY FOR AN AIRCRAFT PROPULSION SYSTEM 审中-公开

    公开(公告)号：US20240092496A1

    公开(公告)日：2024-03-21

    申请号：US17948870

    申请日：2022-09-20

    Applicant: Pratt & Whitney Canada Corp.

    Inventor： Michel Labrecque ,  Kevin Nguyen

    IPC: B64D33/04 ,  B64D27/10 ,  B64D29/00 ,  F02K1/36

    CPC classification number: B64D33/04 ,  B64D27/10 ,  B64D29/00 ,  F02K1/36

    Abstract: An exhaust nozzle assembly for a propulsion system include a primary nozzle, an outer shroud, an ejector nozzle, and an actuator. The primary nozzle extends along an exhaust centerline. The primary nozzle includes a downstream axial end. The outer shroud surrounds the primary nozzle. The ejector nozzle extends axially between a first axial end and a second axial end. The second axial end forms a nozzle exit plane for the exhaust nozzle assembly. The ejector nozzle converges in a direction from the first axial end to the second axial end. The ejector nozzle forms a mixing cross-sectional area between the primary nozzle and the ejector nozzle at the downstream axial end. The actuator is mounted on the ejector nozzle. The actuator is configured to move the ejector nozzle between a first position and a second position, relative to the outer shroud, to control an area of the mixing cross-sectional area.

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