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公开(公告)号：US12140081B2
公开(公告)日：2024-11-12
申请号：US18481597
申请日：2023-10-05
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Narayanan Payyoor , Weize Kang , Brandon W. Miller , Bugra H. Ertas , Andrea Piazza
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：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：US11905890B2
公开(公告)日：2024-02-20
申请号：US17806574
申请日：2022-06-13
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Ravindra Shankar Ganiger , Andrea Piazza , Gontla Nagashiresha , Bugra H. Ertas , Sanjeev Jha
CPC classification number: F02C7/36 , F01D15/10 , F02K3/06 , F05D2220/768 , F05D2260/40311
Abstract: A differential gearbox assembly for a turbine engine having a fan shaft and a drive shaft. The differential gearbox assembly includes an epicyclic gear assembly coupling the fan shaft to the drive shaft. The epicyclic gear assembly includes a sun gear, a planet gear constrained by a planet carrier, and a ring gear. The sun gear is coupled to the drive shaft and the planet carrier is coupled to the fan shaft. The sun gear, the planet gear, and the ring gear all rotate about the drive shaft. The differential gearbox assembly includes an electric machine assembly that includes an input coupled to the epicyclic gear assembly. The electric machine assembly provides mechanical power to the fan shaft through the epicyclic gear assembly.
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公开(公告)号：US11466624B1
公开(公告)日：2022-10-11
申请号：US17694444
申请日：2022-03-14
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Andrea Piazza , Jeffrey D. Clements
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 3.2-4.0. The overall engine efficiency rating is within a range of 0.57-8.0.
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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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Patent Agency Ranking
公开(公告)号：US20250137529A1
公开(公告)日：2025-05-01
申请号：US19003582
申请日：2024-12-27
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Bugra H. Ertas , Xiaohua Zhang , Miriam Manzoni , Flavia Turi , Andrea Piazza , Arthur W. Sibbach
Abstract: A gas turbine engine includes a gearbox assembly that includes a gearbox and a gutter for collecting a gearbox lubricant scavenge flow from the gearbox. The gutter is characterized by a lubricant extraction volume ratio between 0.01 and 0.3. The lubricant extraction volume ratio defined by: V G V GB . V G is a gutter volume of the gutter and VGB is a gearbox volume. The gas turbine engine includes a lubrication system that includes a lubricant tank that stores lubricant, one or more primary gearbox lubricant supply lines, one or more secondary gearbox lubricant supply lines, and a lubricant pump for supplying the lubricant to the gearbox assembly through the primary gearbox lubricant supply lines and the secondary gearbox lubricant supply lines. The lubrication system modulates a mass flow rate of the lubricant to the gearbox assembly through the primary gearbox lubricant supply lines or the secondary gearbox lubricant supply lines.
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公开(公告)号：US20250116208A1
公开(公告)日：2025-04-10
申请号：US18751984
申请日：2024-06-24
Applicant: GE Avio S.r.l.
Inventor： Andrea Piazza
Abstract: A lubrication system for a turbine engine. The turbine engine includes a propulsor and one or more rotating components. The lubrication system includes a sump, a primary lubrication system, an auxiliary lubrication system, and a fuel system. The sump stores lubricant therein. The primary lubrication system supplies the lubricant from the sump to the one or more rotating components during normal operation of the turbine engine. The auxiliary lubrication system includes an auxiliary pump. The fuel system stores hydrogen fuel. The fuel system includes a fuel cell controller that generates electricity from the hydrogen fuel. The electricity powers the auxiliary pump when the propulsor is windmilling such that the auxiliary pump pumps the lubricant from the sump to the one or more rotating components.
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公开(公告)号：US20250116207A1
公开(公告)日：2025-04-10
申请号：US18751978
申请日：2024-06-24
Applicant: GE Avio S.r.l.
Inventor： Andrea Piazza
IPC: F01D25/20
Abstract: A lubrication system for a turbine engine. The turbine engine includes a propulsor and one or more rotating components. The lubrication system includes a sump, a primary lubrication system, an auxiliary lubrication system, and a strain energy storage system. The sump stores lubricant therein. The primary lubrication system supplies the lubricant from the sump to the one or more rotating components during normal operation of the turbine engine. The auxiliary lubrication system includes an auxiliary pump including an auxiliary pump shaft. The strain energy storage system includes a spring drivingly coupled to the auxiliary pump shaft. The spring stores strain energy during normal operation of the turbine engine and releases the strain energy when the propulsor is windmilling to rotate the auxiliary pump shaft to power the auxiliary pump such that the auxiliary pump pumps the lubricant from the sump to the one or more rotating components.
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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：US20240117769A1
公开(公告)日：2024-04-11
申请号：US18481597
申请日：2023-10-05
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Narayanan Payyoor , Weize Kang , Brandon W. Miller , Bugra H. 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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