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公开(公告)号：US20230203993A1
公开(公告)日：2023-06-29
申请号：US18167751
申请日：2023-02-10
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, 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：US20230160341A1
公开(公告)日：2023-05-25
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 , F16H57/0471 , F16H57/0423 , F02C7/36
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：US20220397040A1
公开(公告)日：2022-12-15
申请号：US17835879
申请日：2022-06-08
Applicant: GE Avio S.r.l.
Inventor： Pietro Molesini , Fabio De Bellis , Andrea Piazza
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：US11473507B2
公开(公告)日：2022-10-18
申请号：US17364707
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 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：US20220184641A1
公开(公告)日：2022-06-16
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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Patent Agency Ranking
公开(公告)号：US20240044292A1
公开(公告)日：2024-02-08
申请号：US18484760
申请日：2023-10-11
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, 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.
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公开(公告)号：US11802516B2
公开(公告)日：2023-10-31
申请号：US18167751
申请日：2023-02-10
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, 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：US11708794B2
公开(公告)日：2023-07-25
申请号：US18046612
申请日：2022-10-14
Applicant: GE Avio S.r.l.
Inventor： Pietro Molesini , Andrea Piazza , Fabio De Bellis
CPC classification number: F02C7/36 , F01D17/162 , F02C7/06 , F05D2200/13 , F05D2200/14 , F05D2200/22 , F05D2220/323 , F05D2260/40311 , F05D2260/98
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：US11578666B2
公开(公告)日：2023-02-14
申请号：US17837771
申请日：2022-06-10
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：US20220316404A1
公开(公告)日：2022-10-06
申请号：US17837771
申请日：2022-06-10
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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