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公开(公告)号：US11199138B2
公开(公告)日：2021-12-14
申请号：US16482024
申请日：2018-01-24
Applicant: GE Avio S.r.l.
Inventor： Marco Garabello , Paolo Altamura , Gian Mario Bragallini
Abstract: A turbine engine defines an axial direction and a radial direction and includes a shaft assembly, a fan or propeller assembly, an engine core, a coupling shaft, a spacer, a sleeve, and a nut The coupling shaft defines an annular surface extended along the axial direction and a groove extended in a circumferential direction. The spacer defines a first portion disposed in the groove of the coupling shaft. The sleeve defines a threaded portion that extends along the axial direction and is disposed outward of the spacer in the radial direction. The nut defines a plurality of nut threads configured to mate with the plurality of sleeve threads of the sleeve. The nut defines a radial portion adjacent to at least a portion of the sleeve and at least a portion of the spacer in the axial direction.
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公开(公告)号：US10578166B2
公开(公告)日：2020-03-03
申请号：US15521067
申请日：2015-10-22
Applicant: GE AVIO S.r.l.
Inventor： Paolo Altamura
Abstract: An accessory assembly of a turbine engine has a support structure and a shaft coupled to the support structure by means of a pair of main bearings and provided with an end portion, which has a shear neck designed to break when the torque transmitted to that shaft exceeds a predetermined design threshold; the accessory assembly also has a gear, which defines a motion inlet, is fixed to the end portion and, when said shear neck breaks, remains supported by a single secondary bearing; the latter is distinct from said main bearings and is arranged axially between said shear neck and the gear.
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公开(公告)号：US20170335896A1
公开(公告)日：2017-11-23
申请号：US15521067
申请日：2015-10-22
Applicant: GE AVIO S.r.l.
Inventor： Paolo Altamura
Abstract: An accessory assembly of a turbine engine has a support structure and a shaft coupled to the support structure by means of a pair of main bearings and provided with an end portion, which has a shear neck designed to break when the torque transmitted to that shaft exceeds a predetermined design threshold; the accessory assembly also has a gear, which defines a motion inlet, is fixed to the end portion and, when said shear neck breaks, remains supported by a single secondary bearing; the latter is distinct from said main bearings and is arranged axially between said shear neck and the gear.
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公开(公告)号：US09523424B2
公开(公告)日：2016-12-20
申请号：US14698723
申请日：2015-04-28
Applicant: GE AVIO S.R.L.
Inventor： Paolo Altamura
CPC classification number: F16H57/0479 , F16H57/0427 , F16H57/043 , F16H57/0434 , F16H57/0441 , F16H57/0456 , F16H57/046 , F16H57/0482 , F16H57/0486 , F16H57/082
Abstract: An epyciclic transmission has a sun gear rotational about a transmission axis, a plurality of planet wheels meshing with the sun gear, and a carrier which supports the planet wheels and is rotational about the transmission axis; the transmission also has a lubricating system provided with at least one nozzle arranged in fixed position, with a collection channel fixed with respect to the carrier and configured to receive a jet of oil exiting from the nozzle, and with at least one pump having a casing fixed to the carrier; the pump is actuated by means of a transmission device in response to the rotation of the carrier to pump the oil from the collection channel to zones on the carrier which require lubrication.
Abstract translation: 一个太阳齿轮围绕传动轴转动太阳齿轮，与太阳齿轮啮合的多个行星轮，以及支撑行星轮并围绕传动轴旋转的载体; 所述变速器还具有设置有至少一个布置在固定位置的喷嘴的润滑系统，其中收集通道相对于所述载体固定并且构造成接收从所述喷嘴出来的油喷射器，并且至少一个泵具有壳体 固定在承运人身上 响应于载体的旋转，泵通过传动装置致动，以将油从收集通道泵送到需要润滑的载体上的区域。
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公开(公告)号：US12234907B2
公开(公告)日：2025-02-25
申请号：US18166605
申请日：2023-02-09
Applicant: GE Avio S.r.l.
Inventor： Giulio Zagato , Leonardo Coviello , Francesco Santacroce , Cristiano Consales , Paolo Altamura
Abstract: A planetary gear system includes a carrier including a first side having a first oil manifold opening therethrough, and a second side having a second oil manifold opening therethrough, a first oil manifold and a second oil manifold. The first oil manifold has a first flange portion floatingly engaging with the first oil manifold opening, and a second flange portion engaging with the second oil manifold opening of the carrier, the second flange portion including a first oil manifold mounting flange. The second oil manifold has a second oil manifold flange portion engaging with the second oil manifold opening of the carrier, and including a second oil manifold mounting flange. At least one connecting member connects the first oil manifold mounting flange and the second oil manifold mounting flange so as to mount the first oil manifold and the second oil manifold to the carrier.
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Patent Agency Ranking
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：US20230142971A1
公开(公告)日：2023-05-11
申请号：US18091753
申请日：2022-12-30
Applicant: GE Avio S.r.l.
Inventor： Marco Facchini , Gianluca Andrei , Paolo Altamura
CPC classification number: F01D25/00 , F01D5/022 , F16H1/46 , F02C7/36 , F16H1/2809 , F16H3/44 , F16H57/08 , F16H1/32 , F16H2001/289 , F05D2260/40311
Abstract: A turbomachine engine includes a fan assembly and a core engine comprising a turbine and an input shaft rotatable with the turbine is provided. A single-stage epicyclic gear assembly receives the input shaft at a first speed and drives an output shaft coupled to the fan assembly at a second speed. A sun gear rotates about a longitudinal centerline of the gear assembly and has a sun gear-mesh region along the longitudinal centerline of the gear assembly where the sun gear is configured to contact a plurality of planet gears. A ring gear-mesh region is provided along the longitudinal centerline of the gear assembly where a ring gear is configured to contact the plurality of planet gears. The sun gear-mesh region is axially offset from the ring gear-mesh region along the longitudinal centerline.
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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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公开(公告)号：US20210108568A1
公开(公告)日：2021-04-15
申请号：US16497951
申请日：2018-03-23
Applicant: GE Avio S.r.l.
Inventor： Antonio Caimano , Paolo Altamura , Massimo Civardi , Giorgio Rivetto
Abstract: A gas turbine engine (10) includes a compressor section, a turbine section, and an accessory gearbox (100). A turning unit (200) for the gas turbine engine includes an output assembly (204) configured to be mechanically coupled to the gas turbine engine, and an electric motor (202). The electric motor is operable to rotate, through the output assembly, one or more components of the compressor section or the turbine section at a rotational speed less than about fifty revolutions per minute during a shut-down condition of the gas turbine engine.
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公开(公告)号：US20200248630A1
公开(公告)日：2020-08-06
申请号：US16482086
申请日：2018-01-24
Applicant: GE Avio S.r.l.
Inventor： Marco Garabello , Paolo Altamura , Gian Mario Bragallini , Alessio Gargioli , Jan Biskupski
Abstract: The present disclosure is directed to a turbine engine (10) defining an axial direction and a radial direction. The turbine engine includes a fan or propeller assembly (14) comprising a gearbox; an engine core (20) comprising one or more rotors, wherein at least one of the rotors defines an axially extended annular hub; and a flexible coupling shaft (100) defining a first end and a second end along the axial direction, wherein the first end is connected to the engine core and the second end is connected to the gearbox, and further wherein the flexible coupling shaft extends from the one or more rotors to the gearbox in the axial direction and inward of the hub in the radial direction.
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