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11.发明授权公开(公告)号：US09702451B2
公开(公告)日：2017-07-11
申请号：US14857294
申请日：2015-09-17
Applicant: GE AVIO S.r.l.
Inventor： Michele Gravina
CPC classification number: F16H57/082 , F03D15/10 , F05B2260/40311 , F16H3/46 , F16H48/40 , F16H57/08 , Y02E10/722
Abstract: A planet-carrier for an epicyclic gearing having an annular structure, provided with a coupling portion for being connected to a rotating member or to a static structure in an angularly fixed manner, and a ring that is coaxial to the annular structure along a transmission axis and consists of a plurality of plate-shaped sectors and of a plurality of attachment sectors, alternating with one another about the transmission axis; the plate-shaped sectors lie on a plane orthogonal to the transmission axis and are fixed with respect to pairs of pins, which protrude in opposite directions from the plate-shaped sectors and are adapted to carry respective planet gears; each of the attachment sectors is fastened to the structure by a corresponding pair of arms, which converge with each other towards the ring and are elastically deformable so as to allow a relative movement between the ring and the structure under load.
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公开(公告)号：US11493407B2
公开(公告)日：2022-11-08
申请号：US16584125
申请日：2019-09-26
Applicant: GE Avio S.r.l.
Inventor： Michele Gravina
Abstract: A system for torque measurement is generally provided. The system includes a sensor disposed between an outer bearing race and a static structure of a bearing assembly. The sensor is disposed adjacent along a thrust load direction to the outer bearing race. The system further includes a rotor assembly rotatably coupled to the bearing assembly, and a controller communicatively coupled to the sensor. The controller is configured to store and execute operations. The operations include determining a torque measurement from the rotor assembly based at least on an axial thrust load from the rotor assembly.
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公开(公告)号：US11371590B2
公开(公告)日：2022-06-28
申请号：US16019902
申请日：2018-06-27
Applicant: GE Avio S.r.l.
Inventor： Michele Gravina
Abstract: A gear transmission for aeronautical applications including an input shaft rotating about an axis, an output shaft rotating about the axis, and a transfer group for transferring the torque from the input shaft to the output shaft. The transfer group includes a first torque splitting stage, receiving the torque from the input shaft, and a second torque splitting stage, receiving the torque from the first stage. The first stage presents at least one first rotating member and the second stage presents at least one second rotating member. The input shaft and the first rotating member cooperate with one another at respective interaction surfaces. The rotating members cooperate with one another at respective friction surfaces. One of the interaction surfaces has first engagement elements, and another of the interaction surfaces has second engagement elements that are clutch coupled to one another.
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公开(公告)号：US20210388770A1
公开(公告)日：2021-12-16
申请号：US17347347
申请日：2021-06-14
Applicant: GE Avio S.r.l.
Inventor： Juraj Hrubec , Michele Gravina , 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 have a tubular shape.
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公开(公告)号：US10823260B2
公开(公告)日：2020-11-03
申请号：US16020064
申请日：2018-06-27
Applicant: GE Avio S.r.l.
Inventor： Michele Gravina , Marco Facchini
Abstract: A transmission device for splitting torque between two coaxial gears, in particular for a planetary gearing for aeronautic applications, has a motion input member and two transmission members, which are coaxial and have respective shafts provided with gears at an axial end and respective external flanges, at the opposite axial end; the two flanges are axially facing and placed abutting against each other, and are fixed to the motion input member so as to split the torque transmitted from the motion input member between the two flanges; one of the two shafts is axially hollow and houses, with radial clearance, an intermediate portion of the other shaft; the latter is formed by at least two pieces which are coaxial and fixed to each other.
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Patent Agency Ranking
公开(公告)号：US10823083B2
公开(公告)日：2020-11-03
申请号：US16163927
申请日：2018-10-18
Applicant: GE AVIO S.R.L
Inventor： Michele Gravina
Abstract: An epicyclic gearbox includes a sun gear assembly, a planet gear assembly, and a ring gear assembly engaged with a forward planet gear and an aft planet gear of the planet gear assembly. A first axial shroud is also provided positioned forward of the forward planet gear or aft of the aft planet gear along an axial direction. The first axial shroud covers substantially all of a forward side of the forward planet gear or an aft side of the aft planet gear. The planet gear assembly is coupled to a planet gear carrier, the planet gear carrier including a radial shroud including one or more radial shroud surfaces extending along at least a portion of an outer circumference of the forward planet gear and along at least a portion of an outer circumference of the aft planet gear.
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公开(公告)号：US20200325979A1
公开(公告)日：2020-10-15
申请号：US16303519
申请日：2017-06-02
Applicant: GE AVIO S.R.L.
Inventor： Michele Gravina , Lorenzo Cipolla , Federico Dellavalle
Abstract: A spray bar for lubricating gear meshes in an epicyclic transmission has a base having an inlet designed to receive, in use, a flow of pressurized oil. The spray bar has two tube portions, which project from the base along respective axes, define respective channels parallel to each other and permanently communicating with the inlet, and are laterally defined by respective outer surfaces having outlet nozzles for spraying oil from the channels.
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公开(公告)号：US10458535B2
公开(公告)日：2019-10-29
申请号：US15492040
申请日：2017-04-20
Applicant: GE Avio S.r.l.
Inventor： Michele Gravina , Federico Dellavalle , Elio Perona
Abstract: An oil transfer unit has a rotating part, a stationary part provided with an oil mouth, and a floating part having a support body coupled to the stationary part; the floating part has an annular pad, that is distinct from the body and is provided with a cylindrical surface fitted onto an outer cylindrical surface of the rotating part in a non-contact configuration, with an annular groove provided between the pad and the rotating part to put the oil mouth into communication with an inner chamber of the rotating part; both sides of the groove are sealed by a hydrostatic seal between the cylindrical surfaces; an angular retaining constraint is provided to retain angularly the pad with respect to the body; at least one element is breakable or plastically deformable to release the angular constraint when the torque transferred to the body, in use, exceeds a defined threshold.
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公开(公告)号：US11885267B2
公开(公告)日：2024-01-30
申请号：US17578806
申请日：2022-01-19
Applicant: GE Avio S.r.l.
Inventor： Paolo Altamura , Michele Gravina
CPC classification number: F02C7/36 , F02C7/06 , F02K3/072 , F05D2240/52 , F05D2260/40311
Abstract: A gas turbine engine includes a fan assembly having a plurality of fan blades; and a turbomachine. The turbomachine includes a compressor section, a combustion section, and a turbine section in serial flow order. The turbomachine further including a first input power source; a second input power source configured to counter-rotate relative to the first input power source; a power output component operably connected to the fan assembly; and a gear assembly located forward of the combustion section of the turbomachine, the gear assembly configured to receive power from the first input power source and the second input power source and provide power to the power output component, the gear assembly comprising a helical gear.
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公开(公告)号：US20230048465A1
公开(公告)日：2023-02-16
申请号：US17578806
申请日：2022-01-19
Applicant: GE Avio S.r.l.
Inventor： Paolo Altamura , Michele Gravina
Abstract: A gas turbine engine includes a fan assembly having a plurality of fan blades; and a turbomachine. The turbomachine includes a compressor section, a combustion section, and a turbine section in serial flow order. The turbomachine further including a first input power source; a second input power source configured to counter-rotate relative to the first input power source; a power output component operably connected to the fan assembly; and a gear assembly located forward of the combustion section of the turbomachine, the gear assembly configured to receive power from the first input power source and the second input power source and provide power to the power output component, the gear assembly comprising a helical gear.
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