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公开(公告)号：US11565823B2
公开(公告)日：2023-01-31
申请号：US17099145
申请日：2020-11-16
申请人： AERO INNOVATIONS LLC
发明人： James M. Mills
摘要： A system and method of converting engines on a turboprop aircraft, including removing an existing engine and associated propeller from an aircraft fuselage, installing an engine mount adapter assembly to the fuselage, and installing a replacement engine to the engine mount adapter assembly, whereby at least some portions of the replacement engine are attached to the engine mount adapter assembly for structural support.
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公开(公告)号：US20230013754A1
公开(公告)日：2023-01-19
申请号：US17949511
申请日：2022-09-21
IPC分类号： B64C27/12 , F02C9/56 , F02C9/44 , F02C6/20 , B64D31/00 , B64D27/14 , B64D31/06 , F02C9/42 , F02C9/48 , F02C9/28 , B64D35/08 , B64C27/06 , B64D27/24 , B64D27/02
摘要： A power management system for a multi engine rotorcraft having a main rotor system with a main rotor speed. The power management system includes a first engine that provides a first power input to the main rotor system. A second engine selectively provides a second power input to the main rotor system. The second engine has at least a zero power input state and a positive power input state. A power anticipation system is configured to provide the first engine with a power adjustment signal in anticipation of a power input state change of the second engine during flight. The power adjustment signal causes the first engine to adjust the first power input to maintain the main rotor speed within a predetermined rotor speed threshold range during the power input state change of the second engine.
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公开(公告)号：US20220281583A1
公开(公告)日：2022-09-08
申请号：US17826276
申请日：2022-05-27
发明人： KISHORE RAMAKRISHNAN , SHOURYA OTTA , TREVOR WOOD
摘要： An aircraft having a fuselage, an aircraft body, at least one aircraft engine system and a feature. The fuselage defining a longitudinal centerline. The at least one aircraft engine system defining an axial centerline. The at least one aircraft engine system having a nacelle and at least one rotatable propeller. The at least one rotatable propeller having a free end that is spaced radially outward from the nacelle with respect to the axial centerline. The feature shaped to alter a flow of air between the aircraft body and the at least one rotatable propeller. The feature having a continuous rounded contour when viewed along a vertical plane normal to the longitudinal centerline and intersecting the feature.
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公开(公告)号：US20220073199A1
公开(公告)日：2022-03-10
申请号：US17329312
申请日：2021-05-25
发明人： Randy M. Vondrell , Matthew Ryan Polakowski , Kurt David Murrow , Glenn Crabtree , Darek Tomasz Zatorski
IPC分类号： B64C29/00 , B64C27/28 , H02J50/10 , A61L9/12 , H02J7/00 , B64C21/06 , B64D27/14 , B64D27/24 , H02P9/04
摘要： A propulsion system of an aircraft has at least one unducted fan and at least one ducted fan, the at least one unducted fan and the at least one ducted fan being powered by an electric power source and rotatable between a vertical thrust position and a forward thrust position, and a controller configured to distribute electrical power between the at least one unducted fan and the at least one ducted fan. During a first mode when the at least one unducted fan and the at least one ducted fan are in the vertical thrust position, the controller is configured to distribute the electrical power between the plurality of unducted fans and the plurality of ducted fans such that the at least one unducted fan is a primary source of thrust.
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公开(公告)号：US11142330B2
公开(公告)日：2021-10-12
申请号：US16117305
申请日：2018-08-30
IPC分类号： B64D35/00 , B64D27/14 , B64C21/00 , B64D33/04 , F16H1/22 , F16H37/06 , B64C1/16 , B64C21/06 , F02K3/062
摘要： An aircraft with an integrated boundary layer ingesting propulsion having a mechanically-distributed propulsion system. The mechanically-distributed propulsion system may include an engine to generate a mechanical drive power, a drive shaft, a direction-reversing transmission, and a propulsor fan. The drive shaft may be operatively coupled to the engine to receive the mechanical drive power. The direction-reversing transmission may have a first rotating shaft and a second rotating shaft, the first rotating shaft operatively coupled to the drive shaft to receive the mechanical drive power, which is configured to redirect the mechanical drive power received at the first rotating shaft from a first direction to face a second direction at the second rotating shaft. The propulsor fan may be coupled to the second rotating shaft to convert the mechanical drive power into thrust.
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公开(公告)号：US11046428B2
公开(公告)日：2021-06-29
申请号：US16502913
申请日：2019-07-03
发明人： Randy M. Vondrell , Matthew Ryan Polakowski , Kurt David Murrow , Glenn Crabtree , Darek Tomasz Zatorski
IPC分类号： B64C29/00 , B64C27/28 , H02J50/10 , A61L9/12 , H02J7/00 , H02J7/02 , B64C21/06 , B64D27/14 , B64D27/24 , H02P9/04 , B64C3/38 , B64D27/02
摘要： A method for operating a propulsion system of an aircraft includes moving a plurality of forward and aft propulsors to a vertical thrust position. While in the vertical thrust positions, the method also includes providing a first forward to aft ratio of electric power to the plurality of forward and aft propulsors. The method also includes moving the plurality of forward and aft propulsors to a forward thrust position. While in the forward thrust positions, the method also includes providing a second forward to aft ratio of electric power to the plurality of forward and aft propulsors. The first forward to aft ratio of electric power is different than the second forward to aft ratio of electric power to provide certain efficiencies for the aircraft.
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公开(公告)号：US20210140367A1
公开(公告)日：2021-05-13
申请号：US17256984
申请日：2019-07-03
摘要： The invention relates to an aircraft propulsion system (100) intended for being built into the rear of an aircraft fuselage, the propulsion system comprising at least two gas generators (102a, 102b) supplying a power turbine (104) having two counter-rotating turbine rotors (104a, 104b) for driving two fans (112a, 12b), and separate air inlets (106a, 106b) for supplying each gas generator, characterised in that it comprises an electrical drive device (140) configured to rotate at least one of the turbine rotors, at least one electrical generator (142a, 142b) configured to transform part of the energy of the flow from the gas generators into electrical power and an electric motor (146) supplied by said electrical generator and capable of rotating at least one of the turbine rotors, said electrical generator being installed on one of said gas generators, and in that said turbine rotor is capable of being rotated simultaneously by a flow from said gas generators and by the electrical drive device.
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公开(公告)号：US10934008B2
公开(公告)日：2021-03-02
申请号：US15429934
申请日：2017-02-10
摘要： An aircraft includes an electric power source having a combustion engine and an electric generator. The electric generator is powered by the combustion engine. The aircraft also includes a propulsion assembly including a propulsor and an electric motor, the electric motor configured for rotating the propulsor. The aircraft also includes an electrical outlet configured for connection with an outside power sink. The electrical outlet and the propulsion assembly are selectively in electrical communication with the electric power source such that the electric power source selectively provides electrical power to one of the electrical outlet or the propulsion assembly.
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公开(公告)号：US20200339241A1
公开(公告)日：2020-10-29
申请号：US16396006
申请日：2019-04-26
发明人： James Loebig
摘要： An aircraft is disclosed having a boundary layer ingestion propulsor. The aircraft comprises an elongated fuselage extending between a nose section and a tail section. The fuselage has an upswept underside in the tail section. The boundary layer ingestion propulsor is positioned in the tail section. The propulsor comprises a fan radially encased by a nacelle circumscribing the fuselage. The nacelle defines a leading edge line extending from a top dead center to a bottom dead center of the nacelle intersecting an axis of rotation of the fan at an angle no greater than seventy degrees.
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公开(公告)号：US10814955B2
公开(公告)日：2020-10-27
申请号：US15890785
申请日：2018-02-07
发明人： Jixian Yao , Nikolai N. Pastouchenko , Patrick John Lonneman , Patrick Michael Marrinan , Richard David Cedar
摘要： An aircraft includes a boundary layer ingestion fan defining a centerline and including a plurality of fan blades rotatable about the centerline. The aircraft also includes a fuselage extending between a forward end and an aft end along a longitudinal direction, the boundary layer ingestion fan positioned within the fuselage at the aft end of the fuselage, the fuselage defining an inlet upstream of the boundary layer ingestion fan extending at least about 180 degrees around the centerline of the boundary layer ingestion fan, the fuselage further defining an exhaust downstream of the boundary layer ingestion fan.
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