Patents by Inventor Matteo Renato Usseglio
Matteo Renato Usseglio 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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Patent number: 11946388Abstract: A turbine engine with an outer rotor that circumscribes an inner rotor. The outer rotor includes circumferentially arranged components with a radial outer end and radial inner end. Inner ends of confronting sides of adjacent components include at least one damper element to dampen the relative motion of the components or to provide at least a partial seal between adjacent components.Type: GrantFiled: July 13, 2022Date of Patent: April 2, 2024Assignee: GE Avio S.r.l.Inventors: Antonio Giusseppe D'Ettole, Andrea Depalma, Roberto Maddaleno, Matteo Renato Usseglio
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Publication number: 20240093644Abstract: An aircraft engine is provided. The aircraft engine includes a compressor section having a compressor. A turbine section is downstream of the compressor section. The turbine section includes a turbine having turbine blades arranged in counter rotating stages. The aircraft engine further includes one or more fluid supply lines and a fuel cell assembly fluidly coupled to the one or more fluid supply lines for receiving one or more input fluids. The fuel cell assembly is in fluid communication with the turbine section to provide one or more output products to the turbine section. The aircraft engine further includes a heat exchanger in fluid communication with the turbine downstream of the counter rotating stages of turbine blades to receive exhaust gases from the turbine. The heat exchanger is thermally coupled to the one or more fluid supply lines of the fuel cell assembly.Type: ApplicationFiled: September 16, 2022Publication date: March 21, 2024Inventors: Paul Hadley Vitt, Matteo Renato Usseglio, Brian Lewis Devendorf
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Patent number: 11885233Abstract: A turbine engine with at least a compressor section, combustor section, turbine section and a set of airfoils. The airfoils include geometric characteristics to create a high contraction ratio (CR), a low blade turning (BT) at a radially inward location the airfoil, a low solidity, or a low aspect ratio (AR).Type: GrantFiled: July 28, 2022Date of Patent: January 30, 2024Assignees: General Electric Company, GE Avio S.r.l.Inventors: Ernesto Sozio, Francesco Bertini, Jeffrey Donald Clements, Jonathan Ong, Lyle Douglas Dailey, Paul Hadley Vitt, Matteo Renato Usseglio
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Patent number: 11885237Abstract: A turbomachine having an engine centerline and a first rotor. The first rotor having a first annular drum and being connected to a first plurality of blades. At least one blade of the first plurality of blades having a blade root, a blade tip, a first arm, a second arm and a first seal. The first arm extending from the blade root and having a radial retention hook. The second arm extending from the blade tip.Type: GrantFiled: December 14, 2022Date of Patent: January 30, 2024Assignee: GE AVIO S.r.l.Inventors: Matteo Renato Usseglio, Antonio Giuseppe D'Ettole, Andrea Depalma
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Patent number: 11873725Abstract: A fastener cover for a flanged joint including first and second annular flanges extending about an axis, comprising: an annular, axially-extending, inboard wall; an annular, axially-extending outboard wall positioned radially outboard of the inboard wall; and a first radial wall interconnecting the inboard and outboard walls, wherein, collectively, the inboard and outboard walls and the first radial wall define a cavity for receiving a portion of a fastener; at least one fastener pocket including sidewalls extending axially away from the first radial wall and defining a tubular shape, which is closed off opposite the first radial wall by a floor plate having a clearance hole passing therethrough for accepting a shank of the fastener; and wherein the cover includes a balance weight receptacle for accepting at least one balance weight.Type: GrantFiled: March 15, 2022Date of Patent: January 16, 2024Assignee: GE Avio S.r.l.Inventors: Roberto Maddaleno, Andrea Depalma, Antonio Giuseppe D'Ettole, Matteo Renato Usseglio, Christian Campanale
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Publication number: 20230374935Abstract: A turbine section for a gas turbine engine defines a radial direction and includes a low-pressure (LP) turbine that includes a first plurality of LP turbine blades that includes a first stage having first stage LP turbine blades that rotate in a first direction at a first speed, a second plurality of LP turbine blades that includes a plurality of stages of LP turbine blades disposed downstream of the first stage LP turbine blades that rotate in a second direction opposite the first direction at a second speed, a first LP turbine spool connected to the first plurality of LP turbine blades on an inner side of the first plurality of LP turbine blades in the radial direction, and a second LP turbine spool connected to the second plurality of LP turbine blades on an inner side of the second plurality of LP turbine blades in the radial directionType: ApplicationFiled: May 18, 2022Publication date: November 23, 2023Inventors: Paul Hadley Vitt, Lyle Douglas Dailey, Matteo Renato Usseglio, Andreas Peters
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Patent number: 11821334Abstract: A turbine blade including an airfoil portion extending between a leading edge and a trailing edge, a base portion positioned below the airfoil portion, the base portion including an outwardly-extending wing positioned below the airfoil portion, and an aero-brake feature positioned between the outwardly-extending wing and the airfoil portion and extending outward from the base portion, where the aero-brake feature is structurally configured to disrupt axial airflow across the turbine blade.Type: GrantFiled: July 29, 2021Date of Patent: November 21, 2023Assignee: GE AVIO S.R.L.Inventors: Massimiliano Airaudo, Paolo Calza, Francesco Bertini, Matteo Renato Usseglio, Cristian Lizzer, Ernesto Sozio, Matteo Furfaro, Marco Thiene
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Publication number: 20230340906Abstract: A turbine section and an exhaust section for a gas turbine engine includes a low pressure (LP) turbine having first stage LP turbine blades that rotate in a first direction at a first speed, and final stage LP turbine blades downstream of the first stage LP turbine blades that rotate in a second direction opposite the first direction at a second speed. The second speed is lower than the first speed.Type: ApplicationFiled: April 5, 2022Publication date: October 26, 2023Inventors: Paul Hadley Vitt, Lyle Douglas Dailey, Matteo Renato Usseglio, Andreas Peters, Jonathan Ong
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Patent number: 11692457Abstract: A turbomachine, a computing system for a turbomachine, and a method for overspeed protection are provided. The turbomachine includes a first rotor assembly interdigitated with a second rotor assembly together operably coupled to a gear assembly. A plurality of sensors is configured to receive rotor state data indicative of one or more of a speed, geometric dimension, or capacitance, or change thereof, or rate of change thereof, relative to the first rotor assembly or the second rotor assembly. A controller executes operations including receiving rotor state data from the plurality of sensors; comparing rotor state data to one or more rotor state limits; and contacting one or more of the first rotor assembly or the second rotor assembly to a contact surface adjacent to the respective first rotor assembly or the second rotor assembly if the rotor state data exceeds the rotor state limit.Type: GrantFiled: September 10, 2021Date of Patent: July 4, 2023Assignees: General Electric Company, GE Avio S.r.l.Inventors: Roberto Maddaleno, Antonio Giuseppe D'Ettole, Matteo Renato Usseglio, Alessandra Torri, Darek Tomasz Zatorski
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Patent number: 11674400Abstract: A gas turbine engine including a frame assembly; a turbine assembly; and a nozzle disposed in the turbine assembly, wherein the nozzle defines an inner end along a radial direction and an outer end along the radial direction, wherein the outer end of the nozzle is supported by the frame assembly, wherein the inner end of the nozzle is supported by the frame assembly, and wherein the inner end of the nozzle is displaceable relative to the frame assembly in at least the radial direction.Type: GrantFiled: August 4, 2021Date of Patent: June 13, 2023Assignees: GE AVIO S.R.L., AVIO POLSKA SP. Z O.OInventors: Matteo Renato Usseglio, Enrico Ganzitti, Gianfranco Brandino, Rafal Robak, Tomasz Mucha
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Publication number: 20230167745Abstract: A rotating blade assembly for a turbine engine having a drive shaft, the rotating blade assembly comprising a disc, at least one blade assembly, and a retainer. The disc being operably coupled to the drive shaft and including a seat having at least a portion of a first through hole. The at least one blade assembly having an upper platform, a lower platform, a dovetail extending from the lower platform, and a blade extending between the upper platform and the lower platform. The retainer assembly securing the disc to the at least one blade assembly and comprising a hollow tubular element, a pin, and a fastener.Type: ApplicationFiled: August 16, 2022Publication date: June 1, 2023Inventors: Roberto Maddaleno, Matteo Renato Usseglio
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Patent number: 11661893Abstract: A method of servicing a gas turbine engine, the method including preparing the gas turbine engine for service; installing a shaft protection cover to an aft end of a fan shaft of the gas turbine engine; installing an oil collector drum at least partially around a gearbox of the gas turbine engine; and removing at least a portion of the gearbox from the gas turbine engine.Type: GrantFiled: November 9, 2021Date of Patent: May 30, 2023Assignee: GE AVIO S.R.L.Inventors: Andrea Depalma, Antonio Giuseppe D'Ettole, Roberto Maddaleno, Matteo Renato Usseglio
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Publication number: 20230130213Abstract: A turbine engine with at least a compressor section, combustor section, turbine section and a set of airfoils. The airfoils include geometric characteristics to create a high contraction ratio (CR), a low blade turning (BT) at a radially inward location the airfoil, a low solidity, or a low aspect ratio (AR).Type: ApplicationFiled: July 28, 2022Publication date: April 27, 2023Inventors: Ernesto Sozio, Francesco Bertini, Jeffrey Donald Clements, Jonathan Ong, Lyle Douglas Dailey, Paul Hadley Vitt, Matteo Renato Usseglio
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Publication number: 20230112829Abstract: A turbomachine having an engine centerline and a first rotor. The first rotor having a first annular drum and being connected to a first plurality of blades. At least one blade of the first plurality of blades having a blade root, a blade tip, a first arm, a second arm and a first seal. The first arm extending from the blade root and having a radial retention hook. The second arm extending from the blade tip.Type: ApplicationFiled: December 14, 2022Publication date: April 13, 2023Inventors: Matteo Renato Usseglio, Antonio Giuseppe D'Ettole, Andrea Depalma
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Patent number: 11566532Abstract: A turbine clearance control system is provided. The turbine clearance control system includes a cooling air source and a turbine casing surrounding a portion of a turbine, wherein the turbine casing defines an integral cooling duct within the turbine casing, the integral cooling duct including apertures on an interior surface of the turbine casing.Type: GrantFiled: September 10, 2021Date of Patent: January 31, 2023Assignee: GE Avio S.r.l.Inventors: Agostino Scialpi, Daniele Coutandin, Matteo Renato Usseglio, Giuseppe Greco
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Patent number: 11549379Abstract: A blade for a turbomachine includes a blade root portion for securing the blade to a rotatable annular outer drum rotor. The blade root portion includes one or more radial retention features for radially retaining each of the blade root portions within the rotatable annular outer drum rotor. Further, at least one of the radial retention feature(s) includes at least one sealing member integrated therewith.Type: GrantFiled: August 10, 2020Date of Patent: January 10, 2023Assignee: GE AVIO S.r.l.Inventors: Matteo Renato Usseglio, Antonio Giuseppe D'Ettole, Andrea Depalma
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Publication number: 20220364473Abstract: A turbine engine with an outer rotor that circumscribes an inner rotor. The outer rotor includes circumferentially arranged components with a radial outer end and radial inner end. Inner ends of confronting sides of adjacent components include at least one damper element to dampen the relative motion of the components or to provide at least a partial seal between adjacent components.Type: ApplicationFiled: July 13, 2022Publication date: November 17, 2022Inventors: Antonio Giusseppe D'Ettole, Andrea Depalma, Roberto Maddaleno, Matteo Renato Usseglio
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Publication number: 20220333503Abstract: A fastener cover for a flanged joint including first and second annular flanges extending about an axis, comprising: an annular, axially-extending, inboard wall; an annular, axially-extending outboard wall positioned radially outboard of the inboard wall; and a first radial wall interconnecting the inboard and outboard walls, wherein, collectively, the inboard and outboard walls and the first radial wall define a cavity for receiving a portion of a fastener; at least one fastener pocket including sidewalls extending axially away from the first radial wall and defining a tubular shape, which is closed off opposite the first radial wall by a floor plate having a clearance hole passing therethrough for accepting a shank of the fastener; and wherein the cover includes a balance weight receptacle for accepting at least one balance weight.Type: ApplicationFiled: March 15, 2022Publication date: October 20, 2022Applicant: GE Avio S.r.l.Inventors: Roberto Maddaleno, Andrea Depalma, Antonio Giuseppe D'Ettole, Matteo Renato Usseglio, Christian Campanale
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Patent number: 11473439Abstract: A gas turbine engine defining a longitudinal direction and a radial direction is provided.Type: GrantFiled: September 23, 2021Date of Patent: October 18, 2022Assignees: General Electric Company, GE AVIO S.R.L.Inventors: Luca Giacobone, Matteo Renato Usseglio, Andrea Depalma, Roberto Maddaleno, Darek Tomasz Zatorski
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Publication number: 20220290571Abstract: A gas turbine engine including a frame assembly; a turbine assembly; and a nozzle disposed in the turbine assembly, wherein the nozzle defines an inner end along a radial direction and an outer end along the radial direction, wherein the outer end of the nozzle is supported by the frame assembly, wherein the inner end of the nozzle is supported by the frame assembly, and wherein the inner end of the nozzle is displaceable relative to the frame assembly in at least the radial direction.Type: ApplicationFiled: August 4, 2021Publication date: September 15, 2022Inventors: Matteo Renato Usseglio, Enrico Ganzitti, Gianfranco Brandino, Rafal Robak, Tomasz Mucha