Patents by Inventor Simone CASTELLANI
Simone CASTELLANI has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Publication number: 20240125279Abstract: 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.Type: ApplicationFiled: December 21, 2023Publication date: April 18, 2024Inventors: Giuseppe Cervelli, Simone Castellani, Miriam Manzoni, Giuseppe Bellocchio, Vojtech Jirasek
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Patent number: 11873771Abstract: 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.Type: GrantFiled: December 5, 2022Date of Patent: January 16, 2024Assignees: GE AVIO S.R.L., GE AVIATION CZECH S.R.O.Inventors: Giuseppe Cervelli, Simone Castellani, Miriam Manzoni, Giuseppe Bellocchio, Vojtech Jirasek
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Patent number: 11649771Abstract: A control system (10) for a gas turbine engine (1) having a gas generator (4) and a turbine (6) driven by the gas generator (4), is provided with: a control unit (12) to control a forward operating mode or a reverse operating mode of the gas turbine engine (1); and a supervising unit (14), operatively coupled to the control unit (12), to receive an input signal (PLA) indicative of a forward, or reverse, power request and to cause the control unit (12) to control the forward, or reverse, operating mode based on the input signal (PLA). The supervising unit (14) has an enabling stage (20) to enable a transition between the forward and reverse operating modes based on a check that a safety condition is satisfied.Type: GrantFiled: January 19, 2018Date of Patent: May 16, 2023Assignee: GE Avio S.R.L.Inventors: Simone Castellani, Pierpaolo Forte
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Publication number: 20230106850Abstract: 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.Type: ApplicationFiled: December 5, 2022Publication date: April 6, 2023Inventors: Giuseppe Cervelli, Simone Castellani, Miriam Manzoni, Giuseppe Bellocchio, Vojtech Jirasek
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Patent number: 11519346Abstract: 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.Type: GrantFiled: July 2, 2020Date of Patent: December 6, 2022Assignees: GE AVIO S.R.L., GE AVIATION CZECH S.R.O.Inventors: Giuseppe Cervelli, Simone Castellani, Miriam Manzoni, Giuseppe Bellocchio, Vojtech Jirasek
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Patent number: 11472575Abstract: 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.Type: GrantFiled: March 1, 2018Date of Patent: October 18, 2022Assignee: GE AVIO S.R.L.Inventors: Felice Felippone, Stefano Ettorre, Simone Castellani
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Patent number: 11287781Abstract: 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.Type: GrantFiled: February 16, 2018Date of Patent: March 29, 2022Assignee: GE AVIO S.R.L.Inventors: Simone Castellani, Giuseppe Donini, Pierpaolo Forte, Cristian Lai
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Patent number: 11204087Abstract: The present disclosure is directed to a shaft assembly (95) for a turbine engine (10), the shaft assembly (95) defining an axial direction and a radial direction, wherein the turbine engine (10) includes a fan or propeller assembly (14) and an engine core (20) and further wherein the fan or propeller assembly (14) includes a gearbox (45). The shaft (assembly 95) includes a coupling shaft (100) defining a plurality of coupling shaft teeth (105) extended in the axial direction, wherein each coupling shaft tooth (105) is in circumferential arrangement along the coupling shaft (100). The coupling shaft (100) includes a first material (103) and the plurality of coupling shaft teeth (105) include a second material (104) different from the first material (103).Type: GrantFiled: January 26, 2018Date of Patent: December 21, 2021Assignee: GE AVIO S.R.L.Inventors: Marco Garabello, Simone Castellani
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Patent number: 11162433Abstract: 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.Type: GrantFiled: June 27, 2018Date of Patent: November 2, 2021Assignee: GE AVIO S.R.L.Inventors: Lorenzo Cipolla, Giampaolo Gabbi, Simone Castellani, Federico Dellavalle, Felice Felippone
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Patent number: 11161597Abstract: 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.Type: GrantFiled: January 24, 2018Date of Patent: November 2, 2021Assignee: GE AVIO S.R.LInventors: Davide Lauria, Alessio Gargioli, Simone Castellani, Marco Garabello
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Publication number: 20210215106Abstract: A control system (10) for a gas turbine engine (1) having a gas generator (4) and a turbine (6) driven by the gas generator (4), is provided with: a control unit (12) to control a forward operating mode or a reverse operating mode of the gas turbine engine (1); and a supervising unit (14), operatively coupled to the control unit (12), to receive an input signal (PLA) indicative of a forward, or reverse, power request and to cause the control unit (12) to control the forward, or reverse, operating mode based on the input signal (PLA). The supervising unit (14) has an enabling stage (20) to enable a transition between the forward and reverse operating modes based on a check that a safety condition is satisfied.Type: ApplicationFiled: January 19, 2018Publication date: July 15, 2021Inventors: Simone Castellani, Pierpaolo Forte
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Patent number: 10981662Abstract: The present disclosure is directed to a method for determining an aircraft minimum low pitch setting for a propeller assembly and minimum gas generator idle speed for a gas generator, in which the propeller assembly and the gas generator together comprise a gas turbine engine. The method comprises determining, via one or more controllers, an operating condition of the aircraft based at least on a weight on wheels (WoW) signal and a throttle lever position. The WoW signal produces a first mode or a second mode different from the first mode, and the throttle lever position defines at least a takeoff position and an idle power position.Type: GrantFiled: June 27, 2018Date of Patent: April 20, 2021Assignee: GE AVIO SRLInventors: Stefano Ettorre, Felice Felippone, Simone Castellani
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Publication number: 20210079855Abstract: 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.Type: ApplicationFiled: July 2, 2020Publication date: March 18, 2021Inventors: Giuseppe Cervelli, Simone Castellani, Miriam Manzoni, Giuseppe Bellocchio, Vojtech Jirasek
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Publication number: 20200298959Abstract: 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.Type: ApplicationFiled: March 11, 2020Publication date: September 24, 2020Inventors: Simone Castellani, Giuseppe Cervelli
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Publication number: 20200247529Abstract: 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.Type: ApplicationFiled: January 24, 2018Publication date: August 6, 2020Inventors: Davide Lauria, Alessio Gargioli, Simone Castellani, Marco Garabello
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Publication number: 20200080475Abstract: 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.Type: ApplicationFiled: December 11, 2017Publication date: March 12, 2020Inventors: Mehdi Milani Baladi, Christopher Michael Chapman, Simone Castellani
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Publication number: 20200010219Abstract: 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.Type: ApplicationFiled: March 1, 2018Publication date: January 9, 2020Inventors: Felice Felippone, Stefano Ettorre, Simone Castellani
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Publication number: 20200003290Abstract: The present disclosure is directed to a shaft assembly (95) for a turbine engine (10), the shaft assembly (95) defining an axial direction and a radial direction, wherein the turbine engine (10) includes a fan or propeller assembly (14) and an engine core (20) and further wherein the fan or propeller assembly (14) includes a gearbox (45). The shaft (assembly 95) includes a coupling shaft (100) defining a plurality of coupling shaft teeth (105) extended in the axial direction, wherein each coupling shaft tooth (105) is in circumferential arrangement along the coupling shaft (100). The coupling shaft (100) includes a first material (103) and the plurality of coupling shaft teeth (105) include a second material (104) different from the first material (103).Type: ApplicationFiled: January 26, 2018Publication date: January 2, 2020Inventors: Marco Garabello, Simone Castellani
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Publication number: 20190384234Abstract: 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.Type: ApplicationFiled: February 16, 2018Publication date: December 19, 2019Inventors: Simone Castellani, Giuseppe Donini, Pierpaolo Forte, Cristian Lai
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Publication number: 20190032577Abstract: 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.Type: ApplicationFiled: June 27, 2018Publication date: January 31, 2019Inventors: Lorenzo CIPOLLA, Giampaolo GABBI, Simone CASTELLANI, Federico DELLAVALLE, Felice FELIPPONE