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公开(公告)号：US11519346B2
公开(公告)日：2022-12-06
申请号：US16920159
申请日：2020-07-02
Applicant: GE Aviation Czech s.r.o. , GE Avio S.r.l.
Inventor： Giuseppe Cervelli , Simone Castellani , Miriam Manzoni , Giuseppe Bellocchio , Vojtech Jirasek
Abstract: A variable pitch propeller assembly operatively coupled with an engine and methods for controlling the pitch of a plurality of propeller blades thereof is provided. In one example aspect, the variable pitch propeller assembly includes features for combining overspeed, feathering, and reverse functionality in a single secondary control valve. The secondary control valve is operable to selectively allow a controlled amount of hydraulic fluid to flow to or from a pitch actuation assembly such that the pitch of the propeller blades can be adjusted to operate the variable pitch propeller assembly in one of a constant speed mode, a feather mode, and a reverse mode.
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公开(公告)号：US20210079855A1
公开(公告)日：2021-03-18
申请号：US16920159
申请日：2020-07-02
Applicant: GE Aviation Czech s.r.o. , GE Avio S.r.l.
Inventor： Giuseppe Cervelli , Simone Castellani , Miriam Manzoni , Giuseppe Bellocchio , Vojtech Jirasek
Abstract: A variable pitch propeller assembly operatively coupled with an engine and methods for controlling the pitch of a plurality of propeller blades thereof is provided. In one example aspect, the variable pitch propeller assembly includes features for combining overspeed, feathering, and reverse functionality in a single secondary control valve. The secondary control valve is operable to selectively allow a controlled amount of hydraulic fluid to flow to or from a pitch actuation assembly such that the pitch of the propeller blades can be adjusted to operate the variable pitch propeller assembly in one of a constant speed mode, a feather mode, and a reverse mode.
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3.发明授权公开(公告)号：US12037100B2
公开(公告)日：2024-07-16
申请号：US16815942
申请日：2020-03-11
Applicant: GE Avio S.r.l.
Inventor： Simone Castellani , Giuseppe Cervelli
CPC classification number: B64C11/40 , F01D5/021 , F05D2260/70
Abstract: A variable pitch propeller assembly is operatively coupled with an engine and methods for controlling the pitch of a plurality of propeller blades thereof are associated. In one example aspect, the variable pitch propeller assembly includes features for combining overspeed, feathering, and reverse functionality in a single secondary control valve. The secondary control valve is operable to selectively allow a controlled amount of hydraulic fluid to flow to or from a pitch actuation assembly such that the pitch of the propeller blades can be adjusted to operate the variable pitch propeller assembly in one of a constant speed mode, a feather mode, and a reverse mode.
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公开(公告)号：US20200247529A1
公开(公告)日：2020-08-06
申请号：US16481937
申请日：2018-01-24
Applicant: GE Avio S.r.l.
Inventor： Davide Lauria , Alessio Gargioli , Simone Castellani , Marco Garabello
Abstract: The present disclosure is directed to a turbine engine (10) defining an axial direction, a radial direction, a circumferential direction, a first end (99) and a second end (98) opposite of the first end (99) along the axial direction. The turbine engine includes a propeller assembly (14) proximate to the first end including a plurality of blades (42) arranged in the circumferential direction disposed around an axial centerline (12), and a feathering mechanism (60) including a hollow piston rod (19). The feathering mechanism rotates the plurality of blades about a pitch axis (13) extended in the radial direction from the axial centerline. The turbine engine further includes a housing (45) proximate to the second end disposed in adjacent arrangement with the propeller assembly in the axial direction. The axial centerline is defined through the propeller assembly and the housing. The turbine engine further includes a beta tube assembly (100) extended through the hollow piston rod and at least partially through the housing in coaxial alignment with the axial centerline. The beta tube assembly defines an at least partially hollow walled pipe (101) extended along the axial direction. The beta tube assembly further defines a plurality of grooves (111, 112) extended along the axial direction proximate to the housing. A first groove (111) extends at least partially in the circumferential direction and along the axial direction to at least partially define a helix (114) corresponding to a rotatable range of the plurality of blades about the pitch axis, and a second groove (112) extends in the axial direction.
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公开(公告)号：US20190384234A1
公开(公告)日：2019-12-19
申请号：US16485031
申请日：2018-02-16
Applicant: GE Avio S.r.l.
Inventor： Simone Castellani , Giuseppe Donini , Pierpaolo Forte , Cristian Lai
Abstract: An electronic control system (30) for a turbopropeller engine (1) having a gas turbine (2, 4, 5, 6) and a propeller (7), coupled to the gas turbine, the control system (10) having a propeller control unit (14) and a turbine control unit (15) to jointly control engine power output based on an input request (PLA), wherein the propeller control unit (14) has a first reference generator (16), to determine a reference propeller speed (Npref) based on the input request (PLA), and a first regulator (19), to regulate a propeller speed (Np). The propeller control unit (14) has a reference correction stage (31) to apply a correction to the reference propeller speed (Npref) and generate thereby a corrected reference propeller speed (I), and the first regulator (19) regulates the propeller speed (Np) based on the corrected reference propeller speed (I) to achieve optimized efficiency.
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Patent Agency Ranking
公开(公告)号：US11472575B2
公开(公告)日：2022-10-18
申请号：US16490814
申请日：2018-03-01
Applicant: GE Avio S.r.l.
Inventor： Felice Felippone , Stefano Ettorre , Simone Castellani
Abstract: A method (600) for testing control logic for a propeller driven by a gas turbine engine of an aircraft includes overriding (602) a signal indicating the aircraft is operating in a ground mode. The method can further include testing (604) minimum pitch protection logic when the signal is overridden; determining (606) the gas turbine engine is operating at a ground fine setting; restoring (608) the signal to an original state in which the signal indicates the aircraft is operating in the ground mode; modifying (610) pitch protection logic; determining (614) the propeller is operating at an overspeed condition; and testing (616) the propeller overspeed protection logic. In addition, the method can also determine (612) the propeller is operating at a low pitch condition when the gas turbine engine is operating at the ground fine setting.
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公开(公告)号：US11162433B2
公开(公告)日：2021-11-02
申请号：US16019944
申请日：2018-06-27
Applicant: GE Avio S.r.l.
Inventor： Lorenzo Cipolla , Giampaolo Gabbi , Simone Castellani , Federico Dellavalle , Felice Felippone
Abstract: The present disclosure is directed to a system for controlling an output of a gas generator via an operator manipulated input device. The system includes one or more sensors measuring one or more environmental conditions, a gas generator shaft speed, and a power turbine torque. The system further includes an operator manipulated input device and one or more controllers including one or more processors and one or more memory devices. The one or more memory devices stores instructions that when executed by the one or more processors cause the one or more processors to perform operations. The operations include receiving, via an operator manipulated input device, a throttle lever position defining at least an idle position, a takeoff position, and one or more intermediate positions therebetween; receiving, via one or more sensors, one or more environmental conditions, wherein the environmental condition includes one or more of an ambient air temperature, an ambient air pressure, and an ambient airflow rate; determining, via the controller, a first commanded fuel flow of the gas generator based on a gas generator speed output curve based at least on the throttle lever position, the one or more environmental conditions, and a coefficient reference table; determining, via the controller, a second commanded fuel flow of the gas generator based on a power turbine torque output curve based at least on the one or more environmental conditions; and generating, via the gas generator, a gas generator output based on the first commanded fuel flow or the second commanded fuel flow.
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公开(公告)号：US11161597B2
公开(公告)日：2021-11-02
申请号：US16481937
申请日：2018-01-24
Applicant: GE Avio S.r.l.
Inventor： Davide Lauria , Alessio Gargioli , Simone Castellani , Marco Garabello
Abstract: The present disclosure is directed to a turbine engine (10) defining an axial direction, a radial direction, a circumferential direction, a first end (99) and a second end (98) opposite of the first end (99) along the axial direction. The turbine engine includes a propeller assembly (14) proximate to the first end including a plurality of blades (42) arranged in the circumferential direction disposed around an axial centerline (12), and a feathering mechanism (60) including a hollow piston rod (19). The feathering mechanism rotates the plurality of blades about a pitch axis (13) extended in the radial direction from the axial centerline. The turbine engine further includes a housing (45) proximate to the second end disposed in adjacent arrangement with the propeller assembly in the axial direction. The axial centerline is defined through the propeller assembly and the housing. The turbine engine further includes a beta tube assembly (100) extended through the hollow piston rod and at least partially through the housing in coaxial alignment with the axial centerline. The beta tube assembly defines an at least partially hollow walled pipe (101) extended along the axial direction. The beta tube assembly further defines a plurality of grooves (111, 112) extended along the axial direction proximate to the housing. A first groove (111) extends at least partially in the circumferential direction and along the axial direction to at least partially define a helix (114) corresponding to a rotatable range of the plurality of blades about the pitch axis, and a second groove (112) extends in the axial direction.
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公开(公告)号：US20200080475A1
公开(公告)日：2020-03-12
申请号：US16468969
申请日：2017-12-11
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Mehdi Milani Baladi , Christopher Michael Chapman , Simone Castellani
Abstract: A propulsion system for a vehicle (10) includes a propulsor (102) for generating a thrust for the vehicle, a motor (104) operable with the propulsor for driving the propulsor, a motor mount (164) for mounting the motor in or to the vehicle, and a thrust measuring device (172). The thrust measuring device (172) includes a strain sensor (174) mounted to a structural component of at least one of the propulsor (102), the motor (104), or the motor (164) mount for directly measuring a strain on the structural component caused by the thrust generated by the propulsor during operation of the propulsion system.
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公开(公告)号：US12123359B2
公开(公告)日：2024-10-22
申请号：US15978097
申请日：2018-05-12
Applicant: GE Avio S.r.l.
Inventor： Mehdi Milani Baladi , Robert Jon McQuiston , Aniello Esposito , Joseph Donofrio , Nicholas William Simone , Simone Castellani
CPC classification number: F02C9/18 , F02C6/08 , F04D27/0215 , F05D2220/323 , F05D2260/606 , F05D2270/101 , F05D2270/30
Abstract: An aircraft can comprise an engine, an environmental control system, an engine controller, and a plurality of sensors detecting engine or aircraft parameters. Engine or aircraft operation can be updated in real time based on input from the sensors, including airflow management or operation parameters.
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