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公开(公告)号：US11591969B2
公开(公告)日：2023-02-28
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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公开(公告)号：US11204087B2
公开(公告)日：2021-12-21
申请号：US16482011
申请日：2018-01-26
Applicant: GE Avio S.r.l.
Inventor： Marco Garabello , Simone Castellani
Abstract: The present disclosure is directed to a shaft assembly (95) for a turbine engine (10), the shaft assembly (95) defining an axial direction and a radial direction, wherein the turbine engine (10) includes a fan or propeller assembly (14) and an engine core (20) and further wherein the fan or propeller assembly (14) includes a gearbox (45). The shaft (assembly 95) includes a coupling shaft (100) defining a plurality of coupling shaft teeth (105) extended in the axial direction, wherein each coupling shaft tooth (105) is in circumferential arrangement along the coupling shaft (100). The coupling shaft (100) includes a first material (103) and the plurality of coupling shaft teeth (105) include a second material (104) different from the first material (103).
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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：US20200003290A1
公开(公告)日：2020-01-02
申请号：US16482011
申请日：2018-01-26
Applicant: GE Avio S.r.l.
Inventor： Marco Garabello , Simone Castellani
Abstract: The present disclosure is directed to a shaft assembly (95) for a turbine engine (10), the shaft assembly (95) defining an axial direction and a radial direction, wherein the turbine engine (10) includes a fan or propeller assembly (14) and an engine core (20) and further wherein the fan or propeller assembly (14) includes a gearbox (45). The shaft (assembly 95) includes a coupling shaft (100) defining a plurality of coupling shaft teeth (105) extended in the axial direction, wherein each coupling shaft tooth (105) is in circumferential arrangement along the coupling shaft (100). The coupling shaft (100) includes a first material (103) and the plurality of coupling shaft teeth (105) include a second material (104) different from the first material (103).
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公开(公告)号：US20210246835A1
公开(公告)日：2021-08-12
申请号：US17173523
申请日：2021-02-11
Applicant: GE Avio S.r.l.
Inventor： Marco Garabello , Alessio Gargioli , Fabrizio Bussi , Giuseppe Argentieri , Salvatore Garofalo
Abstract: A gearbox assembly for a gas turbine engine includes a planetary gear set comprising a sun gear, a planet gear, and a ring gear, the sun gear configured for connection to a first drive shaft of the gas turbine engine and the ring gear configured for connection to a second drive shaft of the gas turbine engine, and an electric machine assembly comprising an input and an electric machine. The electric machine comprising a rotor coupled to the input and a stator fixedly positioned within the gearbox assembly, the input of the electric machine assembly coupled to one of the sun gear, the ring gear, or the planet gear of the planetary gear set.
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Patent Agency Ranking
公开(公告)号：US12116939B2
公开(公告)日：2024-10-15
申请号：US18167416
申请日：2023-02-10
Applicant: GE Avio S.r.l.
Inventor： Marco Garabello , Alessio Gargioli , Fabrizio Bussi , Giuseppe Argentieri , Salvatore Garofalo
CPC classification number: F02C7/36 , F02C7/32 , B64D27/026 , F05D2220/323 , F05D2260/40311
Abstract: A gearbox assembly for a gas turbine engine includes a planetary gear set comprising a sun gear, a planet gear, and a ring gear, the sun gear configured for connection to a first drive shaft of the gas turbine engine and the ring gear configured for connection to a second drive shaft of the gas turbine engine, and an electric machine assembly comprising an input and an electric machine. The electric machine comprising a rotor coupled to the input and a stator fixedly positioned within the gearbox assembly, the input of the electric machine assembly coupled to one of the sun gear, the ring gear, or the planet gear of the planetary gear set.
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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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公开(公告)号：US20190390604A1
公开(公告)日：2019-12-26
申请号：US16482024
申请日：2018-01-24
Applicant: GE Avio S.r.l.
Inventor： Marco Garabello , Paolo Altamura , Gian Mario Bragallini
IPC: F02C7/32 , F16D1/06 , F16C19/26 , F16C33/58 , F16C35/063
Abstract: The present disclosure is directed to a shaft assembly (95) for a turbine engine (10), wherein the turbine engine (10) defines an axial direction and a radial direction, wherein the turbine engine (10) includes a fan or propeller assembly (14) and an engine core (20), and further wherein the fan or propeller assembly (14) includes a gearbox (45). The turbine engine (10) includes a coupling shaft (100), a spacer (150), a sleeve (200), and a nut (250) in adjacent radial arrangement. The coupling shaft (100) is connected at a first end (97) to the engine core (20) and coupled at a second end (96) to the gearbox (45). The coupling shaft (100) defines an annular surface (103) extended along the axial direction and a groove (104) extended in a circumferential direction. The spacer (150) defines a first portion (151) extended inward in the radial direction and a second portion (152) extended in the axial direction. The first portion (151) is disposed in the groove (104) of the coupling shaft (100). The sleeve (200) defines a threaded portion (202) comprising a plurality of sleeve threads (204) defined outwardly in the radial direction. The threaded portion (202) extends along the axial direction and is disposed outward of the (spacer 150) in the radial direction. The nut (250) defines a plurality of nut threads (252) defined inwardly in the radial direction. The plurality of nut threads (252) of the nut (250) is configured to mate with the plurality of sleeve threads (204) of the sleeve (200). The (nut 250) defines a radial portion (254) extended inward in the radial direction. The radial portion (254) is adjacent to at least a portion of the sleeve (200) and at least a portion of the spacer (150) in the axial direction.
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公开(公告)号：US11982201B2
公开(公告)日：2024-05-14
申请号：US17644411
申请日：2021-12-15
Applicant: GE Avio S.r.l.
Inventor： Marco Garabello , Simone Iurlaro , Salvatore Garofalo , Alessio Gargioli , Giuseppe Argentieri
CPC classification number: F01D5/026 , F02C7/36 , F02C9/00 , F16C1/02 , F16D3/06 , F16H1/28 , F16H57/0025 , F05D2220/324 , F05D2220/325 , F05D2220/326 , F05D2220/327 , F05D2230/60 , F05D2240/62 , F05D2260/40311 , F05D2260/96 , F05D2270/07 , F16C2360/23
Abstract: An engine assembly defining an axial direction (A) and including a gearbox, an engine core including at least one rotor, and a flexible coupling shaft having a first end and a second end along the axial direction (A). The first end of the flexible coupling shaft is connected to the engine core and the second end of the flexible coupling shaft is connected to the gearbox. A damper system is positioned at the second end of the flexible coupling shaft. The damper system is configured to reduce vibrations to the flexible coupling shaft during operation of the engine assembly.
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公开(公告)号：US20230121607A1
公开(公告)日：2023-04-20
申请号：US17565592
申请日：2021-12-30
Applicant: GE Avio S.r.l.
Inventor： Simone Iurlaro , Alessio Gargioli , Marco Garabello , Salvatore Garofalo , Enrica Gilardi , Ottavia Pica , Giuseppe Argentieri
Abstract: An aircraft engine component (100) may include a wall (200) comprising an aluminum alloy and/or a magnesium alloy, and a protective coating (108) covering the wall (200). The protective coating (108) may include a prime layer (206), a silicone elastomer layer (208), and an abrasion resistant layer (210). The prime layer (206) may at least partially cover a surface (202) of the wall (200). The prime layer (206) may include a silane coupling agent and an organic titanate. The silicone elastomer layer (208) may at least partially cover the prime layer (206). The silicone elastomer layer (208) may include one or more filler materials dispersed in a matrix of cross-linked silicone polymers. The abrasion resistant layer (210) may at least partially cover the silicone elastomer layer (208). The abrasion resistant layer (210) may include a fiber-reinforced elastomeric material.
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