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公开(公告)号：US12180896B2
公开(公告)日：2024-12-31
申请号：US18419892
申请日：2024-01-23
Applicant: GE Avio S.r.l.
Inventor： Pietro Molesini , Andrea Piazza , Fabio De Bellis
Abstract: 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 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 4.1-14.0.
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公开(公告)号：US20220364636A1
公开(公告)日：2022-11-17
申请号：US17488784
申请日：2021-09-29
Applicant: GE Avio S.r.l.
Inventor： Lucia Azzini , Fabio De Bellis , Andrea Piazza
IPC: F16H55/06 , F16H1/28 , F16H57/08 , F02C7/36 , C23C16/50 , C23C16/26 , C23C16/30 , C23C16/34 , C23C24/04
Abstract: 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.
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公开(公告)号：US11920491B2
公开(公告)日：2024-03-05
申请号：US17835879
申请日：2022-06-08
Applicant: GE Avio S.r.l.
Inventor： Pietro Molesini , Fabio De Bellis , Andrea Piazza
CPC classification number: F01D25/18 , F16H1/28 , F16H57/0423 , F16H57/0427 , F16H57/043 , F16H57/046 , F16H57/0486 , F05D2220/36 , F05D2260/40311 , F05D2260/98
Abstract: 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.
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公开(公告)号：US11365688B2
公开(公告)日：2022-06-21
申请号：US17344736
申请日：2021-06-10
Applicant: GE Avio S.r.l.
Inventor： Pietro Molesini , Andrea Piazza , Fabio De Bellis
Abstract: 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.
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公开(公告)号：US20210062910A1
公开(公告)日：2021-03-04
申请号：US17009021
申请日：2020-09-01
Applicant: GE Avio S.r.l.
Inventor： Saypen Baraggia Au Yeung , Pietro Molesini , Fabio De Bellis
Abstract: 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.
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Patent Agency Ranking
公开(公告)号：US20240240593A1
公开(公告)日：2024-07-18
申请号：US18419892
申请日：2024-01-23
Applicant: GE Avio S.r.l.
Inventor： Pietro Molesini , Andrea Piazza , Fabio De Bellis
CPC classification number: F02C7/36 , F01D25/18 , F05D2220/32 , F05D2260/40311 , F05D2260/98
Abstract: 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 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 4.1-14.0.
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公开(公告)号：US11808208B2
公开(公告)日：2023-11-07
申请号：US17663536
申请日：2022-05-16
Applicant: GE Avio S.r.l.
Inventor： Fabio De Bellis , Leonardo Orlando , Cristiano Consales , Francesco Santacroce
CPC classification number: F02C7/06 , B64D33/08 , F02C7/36 , F16H57/0423 , F16H57/0471
Abstract: 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.
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公开(公告)号：US20230073996A1
公开(公告)日：2023-03-09
申请号：US18046612
申请日：2022-10-14
Applicant: GE Avio S.r.l.
Inventor： Pietro Molesini , Andrea Piazza , Fabio De Bellis
Abstract: 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.
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公开(公告)号：US11486312B2
公开(公告)日：2022-11-01
申请号：US17364687
申请日：2021-06-30
Applicant: GE Avio S.r.l.
Inventor： Pietro Molesini , Andrea Piazza , Fabio De Bellis
Abstract: 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.
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公开(公告)号：US12168239B2
公开(公告)日：2024-12-17
申请号：US17643544
申请日：2021-12-09
Applicant: GE Avio S.r.l.
Inventor： Saypen Baraggia Au Yeung , Pietro Molesini , Miriam Manzoni , Fabio De Bellis
Abstract: 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.
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