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公开(公告)号：US20240263588A1
公开(公告)日：2024-08-08
申请号：US18606371
申请日：2024-03-15
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Andrea Piazza , Jeffrey D. Clements
CPC classification number: F02C7/36 , F02C3/067 , F02K3/06 , F05D2200/13 , F05D2200/14 , F05D2200/221 , F05D2260/40311 , F05D2260/98
Abstract: A turbomachine engine can include a fan assembly, a vane assembly, a core engine, a gearbox, and an overall engine 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 a low-pressure turbine. The gearbox includes an input and an output. The input of the gearbox is coupled to the low-pressure turbine of the core engine and comprises a first rotational speed, the output of the gearbox 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 2.0-4.0.
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公开(公告)号：US20240052921A1
公开(公告)日：2024-02-15
申请号：US18165590
申请日：2023-02-07
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Andrea Piazza , Ravindra Shankar Ganiger
CPC classification number: F16H55/088 , F16H57/02 , F16H2057/02039
Abstract: A gearbox assembly includes a first gear and a second gear. The first gear includes a plurality of first gear teeth. The second gear includes a plurality of second gear teeth. The plurality of first gear teeth and the plurality of second gear teeth mesh with each other as the first gear and the second gear rotate. A profile shape of at least one first gear tooth of the first gear is characterized by a total profile modification between 66 micrometers and 120 micrometers.
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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：US11808214B2
公开(公告)日：2023-11-07
申请号：US18058034
申请日：2022-11-22
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Narayanan Payyoor , Weize Kang , Brandon W. Miller , Bugra Ertas , Andrea Piazza
CPC classification number: F02C7/36 , F02C7/06 , F05D2220/32 , F05D2240/50 , F05D2240/60 , F05D2260/40
Abstract: A turbomachine engine includes a fan section having a fan shaft, and a core engine having one or more compressor sections, one or more turbine sections that includes a power turbine, and a combustion chamber in flow communication with the compressor sections and turbine sections. The turbomachine engine includes a low-speed shaft coupled to the power turbine and having a midshaft that extends from a forward bearing to an aft bearing. The low-speed shaft is characterized by a midshaft rating (MSR) between two hundred (ft/sec)1/2 and three hundred (ft/sec)1/2. The low-speed shaft has a redline speed between fifty and two hundred fifty feet per second (ft/sec). The turbomachine engine includes a gearbox assembly that couples the fan shaft to the low-speed shaft and characterized by a gearbox assembly mode less than 95% of a midshaft mode of the midshaft or greater than 105% of the midshaft mode.
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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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Patent Agency Ranking
公开(公告)号：US20230323819A1
公开(公告)日：2023-10-12
申请号：US18209689
申请日：2023-06-14
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Andrea Piazza , Jeffrey D. Clements
CPC classification number: F02C7/36 , F02K3/06 , F02C3/067 , F05D2200/14 , F05D2260/98 , F05D2200/221 , F05D2260/40311 , F05D2200/13
Abstract: A turbomachine engine can include a fan assembly, a vane assembly, a core engine, a gearbox, and an overall engine 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 a low-pressure turbine. The gearbox includes an input and an output. The input of the gearbox is coupled to the low-pressure turbine of the core engine and comprises a first rotational speed, the output of the gearbox 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 2.0-4.0. The overall engine efficiency rating is greater than or equal to 0.35GR1.5 and less than or equal to 0.7GR1.5.
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47.发明授权公开(公告)号：US11732655B2
公开(公告)日：2023-08-22
申请号：US17581057
申请日：2022-01-21
Applicant: GE Avio S.r.l.
Inventor： Andrea Piazza
CPC classification number: F02C7/36 , C21D1/06 , F02C7/06 , F16H57/082 , F05D2230/41 , F05D2240/54 , F05D2260/40311 , F05D2300/506
Abstract: A gear assembly comprises a plurality of planet gear layshafts that have an outer surface having a plurality of gear surfaces and a surface having one or more bearing surfaces. The one or more bearing surfaces of the surfaces of the planet gear layshafts have a first case hardening depth and a first nitriding hardness depth. The gear surfaces of the outer surface of the planet gear layshafts have a second case hardening depth.
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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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