Patents by Inventor Fabio De Bellis
Fabio De Bellis 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: 11920491Abstract: A gear assembly for use with a turbomachine comprises a sun gear, a plurality of planet gear layshafts that each support a first stage planet gear and a second stage planet gear, and a ring gear. The sun gear is configured to rotate about a longitudinal centerline of the gear assembly, and the plurality of planet gear layshafts comprise an interior passage that receives one or more lubrication supply lines.Type: GrantFiled: June 8, 2022Date of Patent: March 5, 2024Assignee: GE Avio S.r.l.Inventors: Pietro Molesini, Fabio De Bellis, Andrea Piazza
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Publication number: 20240044292Abstract: A turbomachine engine can include a fan assembly, a vane assembly, a core engine, and a gearbox. The fan assembly can include a plurality of fan blades. The vane assembly can include a plurality of vanes, and the vanes can, in some instances, be disposed aft of the fan blades. The core engine can include one or more compressor sections and one or more turbine sections. The gearbox includes an input and an output. The input is coupled to the one or more turbine sections of the core engine and comprises a first rotational speed, the output is coupled to the fan assembly and has a second rotational speed. A gear ratio of the first rotational speed to the second rotational speed is within a range of 4.1-11.0, and a gearbox oil flow rate at an inlet of the gearbox within a range of 5-25 gallons per minute at a max takeoff condition.Type: ApplicationFiled: October 11, 2023Publication date: February 8, 2024Applicant: GE Avio S.r.l.Inventors: Pietro Molesini, Andrea Piazza, Fabio De Bellis
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Patent number: 11808208Abstract: An integrated lubrication system and an engine that includes the integrated lubrication system. The system has a first and a second lubrication supply line and one or more spray bars. The first lubrication supply line extends radially inward toward a central axis of the engine, has a first plurality of jet outlets, and is configured to deliver a lubrication fluid to a first location on one or more engine components. The second lubrication supply line extends parallel to the central axis, has a second plurality of jet outlets, and is configured to deliver the lubrication fluid to a second location on the one or more engine components. The first lubrication supply line is configured to lubricate the one or more engine components in a first engine power condition and the second lubrication supply line is configured to lubricate the one or more engine components in a second engine power condition.Type: GrantFiled: May 16, 2022Date of Patent: November 7, 2023Assignee: GE AVIO S.R.L.Inventors: Fabio De Bellis, Leonardo Orlando, Cristiano Consales, Francesco Santacroce
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Patent number: 11802516Abstract: A turbomachine engine can include a fan assembly, a vane assembly, a core engine, a gearbox, and a gearbox efficiency rating. The fan assembly can include a plurality of fan blades. The vane assembly can include a plurality of vanes, and the vanes can, in some instances, be disposed aft of the fan blades. The core engine can include one or more compressor sections and one or more turbine sections. The gearbox includes an input and an output. The input is coupled to the one or more turbine sections of the core engine and comprises a first rotational speed, the output is coupled to the fan assembly and has a second rotational speed, and a gear ratio of the first rotational speed to the second rotational speed is within a range of 4.1-14.0. The gearbox efficiency rating is 0.10-1.8.Type: GrantFiled: February 10, 2023Date of Patent: October 31, 2023Inventors: Pietro Molesini, Andrea Piazza, Fabio De Bellis
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Patent number: 11708794Abstract: A turbomachine engine can include a fan assembly, a pitch change mechanism, a vane assembly, a core engine, a gearbox, and a gearbox efficiency rating. The fan assembly can include a plurality of fan blades. The pitch change mechanism can be coupled to the fan assembly. The vane assembly can include a plurality of vanes. The core engine can include one or more compressor sections and one or more turbine sections. The gearbox includes an input and an output. The input is coupled to the one or more turbine sections of the core engine and comprises a first rotational speed, the output is coupled to the fan assembly and has a second rotational speed, and a gear ratio of the first rotational speed to the second rotational speed is within a range of 4.1-14.0. The gearbox efficiency rating is 0.10-1.8.Type: GrantFiled: October 14, 2022Date of Patent: July 25, 2023Assignee: GE Avio S.R.L.Inventors: Pietro Molesini, Andrea Piazza, Fabio De Bellis
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Publication number: 20230203993Abstract: A turbomachine engine can include a fan assembly, a vane assembly, a core engine, a gearbox, and a gearbox efficiency rating. The fan assembly can include a plurality of fan blades. The vane assembly can include a plurality of vanes, and the vanes can, in some instances, be disposed aft of the fan blades. The core engine can include one or more compressor sections and one or more turbine sections. The gearbox includes an input and an output. The input is coupled to the one or more turbine sections of the core engine and comprises a first rotational speed, the output is coupled to the fan assembly and has a second rotational speed, and a gear ratio of the first rotational speed to the second rotational speed is within a range of 4.1-14.0. The gearbox efficiency rating is 0.10-1.8.Type: ApplicationFiled: February 10, 2023Publication date: June 29, 2023Applicant: GE Avio S.r.l.Inventors: Pietro Molesini, Andrea Piazza, Fabio De Bellis
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Publication number: 20230160341Abstract: An integrated lubrication system and an engine that includes the integrated lubrication system. The system has a first and a second lubrication supply line and one or more spray bars. The first lubrication supply line extends radially inward toward a central axis of the engine, has a first plurality of jet outlets, and is configured to deliver a lubrication fluid to a first location on one or more engine components. The second lubrication supply line extends parallel to the central axis, has a second plurality of jet outlets, and is configured to deliver the lubrication fluid to a second location on the one or more engine components. The first lubrication supply line is configured to lubricate the one or more engine components in a first engine power condition and the second lubrication supply line is configured to lubricate the one or more engine components in a second engine power condition.Type: ApplicationFiled: May 16, 2022Publication date: May 25, 2023Inventors: Fabio De Bellis, Leonardo Orlando, Cristiano Consales, Francesco Santacroce
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Publication number: 20230073996Abstract: A turbomachine engine can include a fan assembly, a pitch change mechanism, a vane assembly, a core engine, a gearbox, and a gearbox efficiency rating. The fan assembly can include a plurality of fan blades. The pitch change mechanism can be coupled to the fan assembly. The vane assembly can include a plurality of vanes. The core engine can include one or more compressor sections and one or more turbine sections. The gearbox includes an input and an output. The input is coupled to the one or more turbine sections of the core engine and comprises a first rotational speed, the output is coupled to the fan assembly and has a second rotational speed, and a gear ratio of the first rotational speed to the second rotational speed is within a range of 4.1-14.0. The gearbox efficiency rating is 0.10-1.8.Type: ApplicationFiled: October 14, 2022Publication date: March 9, 2023Applicant: GE Avio S.r.l.Inventors: Pietro Molesini, Andrea Piazza, Fabio De Bellis
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Patent number: 11578666Abstract: A turbomachine engine can include a fan assembly, a vane assembly, a core engine, a gearbox, and a gearbox efficiency rating. The fan assembly can include a plurality of fan blades. The vane assembly can include a plurality of vanes, and the vanes can, in some instances, be disposed aft of the fan blades. The core engine can include one or more compressor sections and one or more turbine sections. The gearbox includes an input and an output. The input is coupled to the one or more turbine sections of the core engine and comprises a first rotational speed, the output is coupled to the fan assembly and has a second rotational speed, and a gear ratio of the first rotational speed to the second rotational speed is within a range of 4.1-14.0. The gearbox efficiency rating is 0.10-1.8.Type: GrantFiled: June 10, 2022Date of Patent: February 14, 2023Inventors: Pietro Molesini, Andrea Piazza, Fabio De Bellis
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Publication number: 20220397040Abstract: A gear assembly for use with a turbomachine comprises a sun gear, a plurality of planet gear layshafts that each support a first stage planet gear and a second stage planet gear, and a ring gear. The sun gear is configured to rotate about a longitudinal centerline of the gear assembly, and the plurality of planet gear layshafts comprise an interior passage that receives one or more lubrication supply lines.Type: ApplicationFiled: June 8, 2022Publication date: December 15, 2022Applicant: GE Avio S.r.l.Inventors: Pietro Molesini, Fabio De Bellis, Andrea Piazza
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Publication number: 20220364636Abstract: A component includes a metallic substrate having a tribological surface and a coating. The coating includes a first layer disposed on the tribological surface and a second layer disposed on the first layer. The first layer includes titanium, chromium, or a diamond-like carbon (DLC). The second layer includes a disulfide.Type: ApplicationFiled: September 29, 2021Publication date: November 17, 2022Inventors: Lucia Azzini, Fabio De Bellis, Andrea Piazza
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Patent number: 11486312Abstract: A turbomachine engine can include an unducted fan assembly, an unducted vane assembly, a core engine, a gearbox, and a gearbox efficiency rating. The unducted fan assembly can include a plurality of fan blades. The unducted vane assembly can include a plurality of vanes, and the vanes can, in some instances, be disposed aft of the fan blades. The core engine can include one or more compressor sections and one or more turbine sections. The gearbox includes an input and an output. The input is coupled to the one or more turbine sections of the core engine and comprises a first rotational speed, the output is coupled to the unducted fan assembly and has a second rotational speed, and a gear ratio of the first rotational speed to the second rotational speed is within a range of 4.1-14.0. The gearbox efficiency rating is 0.10-1.8.Type: GrantFiled: June 30, 2021Date of Patent: November 1, 2022Inventors: Pietro Molesini, Andrea Piazza, Fabio De Bellis
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Patent number: 11473507Abstract: A turbomachine engine can include a fan assembly, a pitch change mechanism, a vane assembly, a core engine, a gearbox, and a gearbox efficiency rating. The fan assembly can include a plurality of fan blades. The pitch change mechanism can be coupled to the fan assembly. The vane assembly can include a plurality of vanes. The core engine can include one or more compressor sections and one or more turbine sections. The gearbox includes an input and an output. The input is coupled to the one or more turbine sections of the core engine and comprises a first rotational speed, the output is coupled to the fan assembly and has a second rotational speed, and a gear ratio of the first rotational speed to the second rotational speed is within a range of 4.1-14.0. The gearbox efficiency rating is 0.10-1.8.Type: GrantFiled: June 30, 2021Date of Patent: October 18, 2022Inventors: Pietro Molesini, Andrea Piazza, Fabio De Bellis
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Publication number: 20220316404Abstract: A turbomachine engine can include a fan assembly, a vane assembly, a core engine, a gearbox, and a gearbox efficiency rating. The fan assembly can include a plurality of fan blades. The vane assembly can include a plurality of vanes, and the vanes can, in some instances, be disposed aft of the fan blades. The core engine can include one or more compressor sections and one or more turbine sections. The gearbox includes an input and an output. The input is coupled to the one or more turbine sections of the core engine and comprises a first rotational speed, the output is coupled to the fan assembly and has a second rotational speed, and a gear ratio of the first rotational speed to the second rotational speed is within a range of 4.1-14.0. The gearbox efficiency rating is 0.10-1.8.Type: ApplicationFiled: June 10, 2022Publication date: October 6, 2022Applicant: GE Avio S.r.l.Inventors: Pietro Molesini, Andrea Piazza, Fabio De Bellis
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Patent number: 11401829Abstract: A turbomachine engine can include a fan assembly, a vane assembly, a core engine, a gearbox, and a gearbox efficiency rating. The fan assembly can include a plurality of fan blades. The vane assembly can include a plurality of vanes, and the vanes can, in some instances, be disposed aft of the fan blades. The core engine can include one or more compressor sections and one or more turbine sections. The gearbox includes an input and an output. The input is coupled to the one or more turbine sections of the core engine and comprises a first rotational speed, the output is coupled to the fan assembly and has a second rotational speed, and a gear ratio of the first rotational speed to the second rotational speed is within a range of 4.1-14.0. The gearbox efficiency rating is 0.10-1.8.Type: GrantFiled: June 30, 2021Date of Patent: August 2, 2022Inventors: Pietro Molesini, Andrea Piazza, Fabio De Bellis
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Patent number: 11391364Abstract: A gear assembly for an aeronautical engine that includes a first gear disposed at a centerline axis of the gear assembly; a second gear coupled to the first gear in adjacent radial arrangement to form a first mesh between the first gear and the second gear; a third gear coupled to the second gear in adjacent radial arrangement to form a second mesh between the second gear and the third gear; a collector rotatably coupled with the third gear; and a lubricant input portion disposed between a portion of the first gear and the second gear such that a first supply opening of the lubricant input portion is directed at the first mesh between the first gear and the second gear. The first supply opening provides a flow of lubricant to the first mesh with a portion of the flow of lubricant is collected by the collector.Type: GrantFiled: September 1, 2020Date of Patent: July 19, 2022Assignee: GE AVIO S.R.L.Inventors: Saypen Baraggia Au Yeung, Pietro Molesini, Fabio De Bellis
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Patent number: 11365688Abstract: A turbomachine engine can include a fan assembly, a vane assembly, a core engine, a gearbox, and a gearbox efficiency rating. The fan assembly can include a plurality of fan blades. The vane assembly can include a plurality of vanes, and the vanes can, in some instances, be disposed aft of the fan blades. The core engine can include one or more compressor sections and one or more turbine sections. The gearbox includes an input and an output. The input is coupled to the one or more turbine sections of the core engine and comprises a first rotational speed, the output is coupled to the fan assembly and has a second rotational speed, and a gear ratio of the first rotational speed to the second rotational speed is within a range of 4.1-14.0. The gearbox efficiency rating is 0.10-1.8.Type: GrantFiled: June 10, 2021Date of Patent: June 21, 2022Inventors: Pietro Molesini, Andrea Piazza, Fabio De Bellis
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Publication number: 20220184641Abstract: An air/oil separator is provided. The air/oil separator includes an oil manifold having a first air/oil inlet and a second air/oil inlet; a first separation chamber in communication with the first air/oil inlet; and a second separation chamber separate from the first separation chamber, the second separation chamber in communication with the second air/oil inlet.Type: ApplicationFiled: December 9, 2021Publication date: June 16, 2022Inventors: Saypen Baraggia Au Yeung, Pietro Molesini, Miriam Manzoni, Fabio De Bellis
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Publication number: 20220056811Abstract: A turbomachine engine can include a fan assembly, a vane assembly, a core engine, a gearbox, and a gearbox efficiency rating. The fan assembly can include a plurality of fan blades. The vane assembly can include a plurality of vanes, and the vanes can, in some instances, be disposed aft of the fan blades. The core engine can include one or more compressor sections and one or more turbine sections. The gearbox includes an input and an output. The input is coupled to the one or more turbine sections of the core engine and comprises a first rotational speed, the output is coupled to the fan assembly and has a second rotational speed, and a gear ratio of the first rotational speed to the second rotational speed is within a range of 4.1-14.0. The gearbox efficiency rating is 0.10-1.8.Type: ApplicationFiled: June 30, 2021Publication date: February 24, 2022Applicant: GE Avio S.r.l.Inventors: Pietro Molesini, Andrea Piazza, Fabio De Bellis
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Publication number: 20220042464Abstract: A turbomachine engine can include a fan assembly, a vane assembly, a core engine, a gearbox, and a gearbox efficiency rating. The fan assembly can include a plurality of fan blades. The vane assembly can include a plurality of vanes, and the vanes can, in some instances, be disposed aft of the fan blades. The core engine can include one or more compressor sections and one or more turbine sections. The gearbox includes an input and an output. The input is coupled to the one or more turbine sections of the core engine and comprises a first rotational speed, the output is coupled to the fan assembly and has a second rotational speed, and a gear ratio of the first rotational speed to the second rotational speed is within a range of 4.1-14.0. The gearbox efficiency rating is 0.10-1.8.Type: ApplicationFiled: June 30, 2021Publication date: February 10, 2022Applicant: GE Avio S.r.l.Inventors: Pietro Molesini, Andrea Piazza, Fabio De Bellis