Patents by Inventor Alessio Gargioli
Alessio Gargioli 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: 20230184174Abstract: A gearbox assembly for a gas turbine engine includes a planetary gear set comprising a sun gear, a planet gear, and a ring gear, the sun gear configured for connection to a first drive shaft of the gas turbine engine and the ring gear configured for connection to a second drive shaft of the gas turbine engine, and an electric machine assembly comprising an input and an electric machine. The electric machine comprising a rotor coupled to the input and a stator fixedly positioned within the gearbox assembly, the input of the electric machine assembly coupled to one of the sun gear, the ring gear, or the planet gear of the planetary gear set.Type: ApplicationFiled: February 10, 2023Publication date: June 15, 2023Inventors: Marco Garabello, Alessio Gargioli, Fabrizio Bussi, Giuseppe Argentieri, Salvalore Garofalo
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Publication number: 20230121607Abstract: An aircraft engine component (100) may include a wall (200) comprising an aluminum alloy and/or a magnesium alloy, and a protective coating (108) covering the wall (200). The protective coating (108) may include a prime layer (206), a silicone elastomer layer (208), and an abrasion resistant layer (210). The prime layer (206) may at least partially cover a surface (202) of the wall (200). The prime layer (206) may include a silane coupling agent and an organic titanate. The silicone elastomer layer (208) may at least partially cover the prime layer (206). The silicone elastomer layer (208) may include one or more filler materials dispersed in a matrix of cross-linked silicone polymers. The abrasion resistant layer (210) may at least partially cover the silicone elastomer layer (208). The abrasion resistant layer (210) may include a fiber-reinforced elastomeric material.Type: ApplicationFiled: December 30, 2021Publication date: April 20, 2023Inventors: Simone Iurlaro, Alessio Gargioli, Marco Garabello, Salvatore Garofalo, Enrica Gilardi, Ottavia Pica, Giuseppe Argentieri
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Patent number: 11591969Abstract: The present disclosure is directed to a turbine engine (10) defining an axial direction and a radial direction. The turbine engine includes a fan or propeller assembly (14) comprising a gearbox; an engine core (20) comprising one or more rotors, wherein at least one of the rotors defines an axially extended annular hub; and a flexible coupling shaft (100) defining a first end and a second end along the axial direction, wherein the first end is connected to the engine core and the second end is connected to the gearbox, and further wherein the flexible coupling shaft extends from the one or more rotors to the gearbox in the axial direction and inward of the hub in the radial direction.Type: GrantFiled: January 24, 2018Date of Patent: February 28, 2023Assignee: GE AVIO S.R.L.Inventors: Marco Garabello, Paolo Altamura, Gian Mario Bragallini, Alessio Gargioli, Jan Biskupski
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Patent number: 11591971Abstract: A gearbox assembly for a gas turbine engine includes a planetary gear set comprising a sun gear, a planet gear, and a ring gear, the sun gear configured for connection to a first drive shaft of the gas turbine engine and the ring gear configured for connection to a second drive shaft of the gas turbine engine, and an electric machine assembly comprising an input and an electric machine. The electric machine comprising a rotor coupled to the input and a stator fixedly positioned within the gearbox assembly, the input of the electric machine assembly coupled to one of the sun gear, the ring gear, or the planet gear of the planetary gear set.Type: GrantFiled: February 11, 2021Date of Patent: February 28, 2023Assignee: GE AVIO S.R.L.Inventors: Marco Garabello, Alessio Gargioli, Fabrizio Bussi, Giuseppe Argentieri, Salvatore Garofalo
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Publication number: 20230019363Abstract: An engine assembly defining an axial direction (A) and including a gearbox, an engine core including at least one rotor, and a flexible coupling shaft having a first end and a second end along the axial direction (A). The first end of the flexible coupling shaft is connected to the engine core and the second end of the flexible coupling shaft is connected to the gearbox. A damper system is positioned at the second end of the flexible coupling shaft. The damper system is configured to reduce vibrations to the flexible coupling shaft during operation of the engine assembly.Type: ApplicationFiled: December 15, 2021Publication date: January 19, 2023Inventors: Marco Garabello, Simone Iurlaro, Salvatore Garofalo, Alessio Gargioli, Giuseppe Argentieri
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Patent number: 11391326Abstract: The present disclosure is directed to a shaft assembly (95) for a turbine engine (10), wherein the turbine engine includes a fan or propeller assembly (14) and an engine core (20), and further wherein the fan or propeller assembly includes a gearbox (45), and wherein the engine core includes one or more rotors (32). The shaft assembly (95) includes a flexible shaft (100) defining a first end (101) and a second end (102) along the axial direction, wherein the first end is connected to the engine core (20) and the second end is connected to the gearbox (45), and wherein a plurality of splines (110) is defined at the second end (102) and coupled to a spline interface (46) at the gearbox (45); and a coupling (120) extended at least partially in the radial direction and coupled to the engine core and the flexible shaft.Type: GrantFiled: January 26, 2018Date of Patent: July 19, 2022Assignee: GE AVIO S.R.L.Inventors: Marco Garabello, Paolo Altamura, Gian Mario Bragallini, Alessio Gargioli, Jan Biskupski
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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: 20210246835Abstract: A gearbox assembly for a gas turbine engine includes a planetary gear set comprising a sun gear, a planet gear, and a ring gear, the sun gear configured for connection to a first drive shaft of the gas turbine engine and the ring gear configured for connection to a second drive shaft of the gas turbine engine, and an electric machine assembly comprising an input and an electric machine. The electric machine comprising a rotor coupled to the input and a stator fixedly positioned within the gearbox assembly, the input of the electric machine assembly coupled to one of the sun gear, the ring gear, or the planet gear of the planetary gear set.Type: ApplicationFiled: February 11, 2021Publication date: August 12, 2021Inventors: Marco Garabello, Alessio Gargioli, Fabrizio Bussi, Giuseppe Argentieri, Salvatore Garofalo
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Publication number: 20200248630Abstract: The present disclosure is directed to a turbine engine (10) defining an axial direction and a radial direction. The turbine engine includes a fan or propeller assembly (14) comprising a gearbox; an engine core (20) comprising one or more rotors, wherein at least one of the rotors defines an axially extended annular hub; and a flexible coupling shaft (100) defining a first end and a second end along the axial direction, wherein the first end is connected to the engine core and the second end is connected to the gearbox, and further wherein the flexible coupling shaft extends from the one or more rotors to the gearbox in the axial direction and inward of the hub in the radial direction.Type: ApplicationFiled: January 24, 2018Publication date: August 6, 2020Inventors: Marco Garabello, Paolo Altamura, Gian Mario Bragallini, Alessio Gargioli, Jan Biskupski
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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: 20190383331Abstract: The present disclosure is directed to a shaft assembly (95) for a turbine engine (10), wherein the turbine engine includes a fan or propeller assembly (14) and an engine core (20), and further wherein the fan or propeller assembly includes a gearbox (45), and wherein the engine core includes one or more rotors (32). The shaft assembly (95) includes a flexible shaft (100) defining a first end (101) and a second end (102) along the axial direction, wherein the first end is connected to the engine core (20) and the second end is connected to the gearbox (45), and wherein a plurality of splines (110) is defined at the second end (102) and coupled to a spline interface (46) at the gearbox (45); and a coupling (120) extended at least partially in the radial direction and coupled to the engine core and the flexible shaft.Type: ApplicationFiled: January 26, 2018Publication date: December 19, 2019Inventors: Marco Garabello, Paolo Altamura, Gian Mario Bragallini, Alessio Gargioli, Jan Biskupski