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公开(公告)号：US20240092496A1
公开(公告)日：2024-03-21
申请号：US17948870
申请日：2022-09-20
发明人： Michel Labrecque , Kevin Nguyen
摘要： 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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公开(公告)号：US09957889B2
公开(公告)日：2018-05-01
申请号：US14463031
申请日：2014-08-19
CPC分类号： F02C7/045 , F02C7/042 , F02K3/06 , F05D2220/323 , F05D2260/96
摘要： An aeroengine is provided with a splitter apparatus disposed in a section of an inlet duct. The splitter apparatus can be actuated from a stowed position to a deployed position to allow splitter(s) to selectively move from out of the inlet flow to a position extending into the inlet duct to divide the inlet flow into multiple passages.
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公开(公告)号：US12103695B2
公开(公告)日：2024-10-01
申请号：US17948870
申请日：2022-09-20
发明人： Michel Labrecque , Kevin Nguyen
摘要： 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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公开(公告)号：US12071252B1
公开(公告)日：2024-08-27
申请号：US18333696
申请日：2023-06-13
CPC分类号： B64D27/24 , B64C11/305 , B64C11/44
摘要： 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.
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公开(公告)号：US11739696B2
公开(公告)日：2023-08-29
申请号：US17548786
申请日：2021-12-13
发明人： Michel Labrecque , Kevin Nguyen , Ninad Joshi
CPC分类号： F02C9/16 , F02C3/04 , F05D2220/30 , F05D2240/35 , F05D2270/053 , F05D2270/303 , F05D2270/3013
摘要： 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：US11661887B2
公开(公告)日：2023-05-30
申请号：US17319439
申请日：2021-05-13
CPC分类号： F02C7/045 , F02C7/042 , B64D2033/0206 , B64D2033/0286 , F01D17/143 , F02K3/025 , F02K3/04 , F02K3/06 , F02K3/068 , F05D2250/311 , F05D2250/712 , F05D2250/90 , F05D2260/96
摘要： 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 passage for selective flight conditions. The inclusion of acoustic treatment may assist in controlling noise.
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公开(公告)号：US11066993B2
公开(公告)日：2021-07-20
申请号：US16256097
申请日：2019-01-24
摘要： 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 passage for selective flight conditions. The inclusion of acoustic treatment may assist in controlling noise.
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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
发明人： Carmine Lisio , Michel Labrecque
摘要： 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：US12116937B1
公开(公告)日：2024-10-15
申请号：US18129646
申请日：2023-03-31
发明人： Michel Labrecque , Patrick Valois , Karine Berube
摘要： 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
发明人： Michel Labrecque , Patrick Valois , Karine Berube
摘要： 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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