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公开(公告)号：US10829235B2
公开(公告)日：2020-11-10
申请号：US16872447
申请日：2020-05-12
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Carmine Lisio , Michel Labrecque
Abstract: The present disclosure provides a method and a system for controlling operation of an engine of an aircraft. The method comprises, at a controller of the engine, obtaining an actual engine output power for the engine, the actual engine output power based on a propeller rotation speed and a propeller blade pitch angle; converting the actual engine output power to a predicted thrust value; determining an actual engine power limit associated with a thrust limit of a propeller coupled to the engine from the predicted thrust value; and setting a maximum engine power limit of the engine using the actual engine power limit associated with the thrust limit of the propeller.
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公开(公告)号：US20230184177A1
公开(公告)日：2023-06-15
申请号：US17548786
申请日：2021-12-13
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Michel Labrecque , Kevin Nguyen , Ninad Joshi
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.
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公开(公告)号：US11674450B1
公开(公告)日：2023-06-13
申请号：US17548779
申请日：2021-12-13
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Michel Labrecque , Kevin Nguyen , Ninad Joshi
CPC classification number: F02C9/16 , F02C3/04 , F05D2220/30 , F05D2240/35 , F05D2270/051 , F05D2270/303 , F05D2270/3013
Abstract: A method and a system for synthesizing thrust from a turbofan engine are provided. The turbofan 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 turbofan engine, a pressure of fluid at an exit of the compressor section and a temperature of fluid at a location upstream of the exit of the compressor section are determined. A synthesized value of thrust from the turbofan engine is determined based on a product of at least a first factor and a second factor, the first factor being a function of the pressure and the second factor being a function of the temperature. The synthesized value of thrust from the turbofan engine is output.
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公开(公告)号：US10221764B2
公开(公告)日：2019-03-05
申请号：US14462981
申请日：2014-08-19
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Michel Labrecque , Vincent Couture-Gagnon , Richard Ullyott
Abstract: A variable geometry inlet system of an aircraft engine includes an inlet duct. The inlet duct includes at least first and second sections moveable between extended and retracted positions such that the inlet duct defines a variable axial length of an inlet in controlling noise.
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公开(公告)号：US10054050B2
公开(公告)日：2018-08-21
申请号：US14463114
申请日：2014-08-19
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Michel Labrecque , Vincent Couture-Gagnon , Richard Ullyott
CPC classification number: F02C7/045 , F01D17/08 , F01D17/105 , F02C7/042 , F02C7/05 , F02C7/052 , F02K3/025
Abstract: An aeroengine has an inlet system with a forward end with respect to a flight direction. The inlet system includes a main inlet duct for selectively directing a first air flow from a forward main intake opening of the main inlet duct to a compressor rotor, the forward main intake opening being defined at the forward end of the inlet system and a secondary inlet duct for directing a second air flow from a secondary intake opening of the secondary inlet duct to the compressor rotor only when the main inlet duct is closed. A control apparatus is provided for selecting the first and second air flow to enter into the compressor rotor.
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Patent Agency Ranking
公开(公告)号：US20240375782A1
公开(公告)日：2024-11-14
申请号：US18196711
申请日：2023-05-12
Applicant: Pratt & Whitney Canada Corp.
Inventor： Eric S. Durocher , Michel Labrecque , Todd A. Spierling
Abstract: An assembly for a propulsion system of an aircraft includes an electric motor, a first gearbox module, a second gearbox module, and a propeller. The electric motor includes a rotor. The rotor includes a first axial end and a second axial end. The first gearbox module includes a first gear assembly. The first gear assembly is coupled to the first axial end. The second gearbox module includes a second gear assembly. The second gear assembly is coupled to the second axial end. The propeller is coupled to the first gear assembly. The first gear assembly is configured to drive rotation of the propeller in response to rotation of the rotor.
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公开(公告)号：US12116937B1
公开(公告)日：2024-10-15
申请号：US18129646
申请日：2023-03-31
Applicant: Pratt & Whitney Canada Corp.
Inventor： Michel Labrecque , Patrick Valois , Karine Berube
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.
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公开(公告)号：US20240328364A1
公开(公告)日：2024-10-03
申请号：US18129646
申请日：2023-03-31
Applicant: Pratt & Whitney Canada Corp.
Inventor： Michel Labrecque , Patrick Valois , Karine Berube
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.
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公开(公告)号：US20240328363A1
公开(公告)日：2024-10-03
申请号：US18129640
申请日：2023-03-31
Applicant: Pratt & Whitney Canada Corp.
Inventor： Eric S. Durocher , Guillaume Landry-Drolet , Paul Weaver , Michel Abdelnour , Louis Flamand , Michel Labrecque
CPC classification number: F02C7/32 , F02C6/00 , F02C7/36 , F05D2220/323 , F05D2220/76 , F05D2260/4031
Abstract: An aircraft system is provided that includes an open propulsor rotor, a gas turbine engine, an electric machine and a drivetrain. The gas turbine engine includes a first 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 first rotating assembly is coupled to and is configured to drive rotation of the open propulsor rotor. The first rotating assembly includes a first turbine rotor in the turbine section. The electric machine is outside of the gas turbine engine. The electric machine includes an electric machine rotor. The drivetrain couples the electric machine rotor to the first rotating assembly.
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公开(公告)号：US11828248B1
公开(公告)日：2023-11-28
申请号：US17809033
申请日：2022-06-27
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Michel Labrecque , Kevin Nguyen
Abstract: There is provided an exhaust mixer arrangement for a turbofan engine having a bypass passage for channelling a bypass flow and a core passage for channelling a core flow around a central axis. The exhaust mixer arrangement comprises a mixer body mounted for rotation about the central axis. The mixer body has an annular wall extending around the central axis. The annular wall defines a plurality of circumferentially distributed alternating inner and outer lobes, with each inner lobe protruding into the core passage, and each outer lobe protruding into the annular bypass passage. A driving unit is operatively connected to the mixer body for selectively driving the mixer body in rotation about the central axis. A controller is operatively connected to the driving unit for controlling a rotational speed of the mixer body as a function of a flight operating condition.
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