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公开(公告)号：US11591971B2
公开(公告)日：2023-02-28
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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公开(公告)号：US20230019363A1
公开(公告)日：2023-01-19
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
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：US20200247529A1
公开(公告)日：2020-08-06
申请号：US16481937
申请日：2018-01-24
Applicant: GE Avio S.r.l.
Inventor： Davide Lauria , Alessio Gargioli , Simone Castellani , Marco Garabello
Abstract: The present disclosure is directed to a turbine engine (10) defining an axial direction, a radial direction, a circumferential direction, a first end (99) and a second end (98) opposite of the first end (99) along the axial direction. The turbine engine includes a propeller assembly (14) proximate to the first end including a plurality of blades (42) arranged in the circumferential direction disposed around an axial centerline (12), and a feathering mechanism (60) including a hollow piston rod (19). The feathering mechanism rotates the plurality of blades about a pitch axis (13) extended in the radial direction from the axial centerline. The turbine engine further includes a housing (45) proximate to the second end disposed in adjacent arrangement with the propeller assembly in the axial direction. The axial centerline is defined through the propeller assembly and the housing. The turbine engine further includes a beta tube assembly (100) extended through the hollow piston rod and at least partially through the housing in coaxial alignment with the axial centerline. The beta tube assembly defines an at least partially hollow walled pipe (101) extended along the axial direction. The beta tube assembly further defines a plurality of grooves (111, 112) extended along the axial direction proximate to the housing. A first groove (111) extends at least partially in the circumferential direction and along the axial direction to at least partially define a helix (114) corresponding to a rotatable range of the plurality of blades about the pitch axis, and a second groove (112) extends in the axial direction.
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Patent Agency Ranking
公开(公告)号：US20190389562A1
公开(公告)日：2019-12-26
申请号：US16481708
申请日：2018-01-26
Applicant: GE Avio S.r.l.
Inventor： Marco Garabello , Paolo Altamura , Gian Mario Bragallini , Davide Lauria
Abstract: The present disclosure is directed to a system 100 for feathering a propeller assembly 14, wherein the system is disposed within a housing 47 of the propeller assembly. The system 100 includes a sleeve 110 defining an outer wall 111 and one or more sleeve tabs 115 extended outward in a radial direction along at least a circumferential portion of the sleeve, wherein the one or more sleeve tabs is separated from the outer wall in an axial direction. The system 100 further includes a retainer 120 defining one or more retainer tabs 125 extended inward in the radial direction, wherein the one or more retainer tabs is disposed between the outer wall 111 and the one or more sleeve tabs 115 of the sleeve 110 along the axial direction. Still further, the system includes a beta tube assembly 130 extended through the sleeve along the axial direction, wherein the beta tube assembly defines one or more internal walls 131, wherein the one or more internal walls defines a hydraulic fluid transfer cavity 132 in fluid communication with one or more hydraulic fluid transfer orifices 133.
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公开(公告)号：US20230184174A1
公开(公告)日：2023-06-15
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 , Salvalore Garofalo
CPC classification number: F02C7/36 , F02C7/32 , B64D2027/026
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：US11161598B2
公开(公告)日：2021-11-02
申请号：US16481708
申请日：2018-01-26
Applicant: GE Avio S.r.l.
Inventor： Marco Garabello , Paolo Altamura , Gian Mario Bragallini , Davide Lauria
Abstract: A system for feathering a propeller assembly disposed within a housing of the propeller assembly has a sleeve defining an outer wall and one or more sleeve tabs extended outward in a radial direction along at least a circumferential portion of the sleeve, wherein the one or more sleeve tabs is separated from the outer wall in an axial direction, a retainer defining one or more retainer tabs extended inward in the radial direction, wherein the one or more retainer tabs is disposed between the outer wall and the one or more sleeve tabs of the sleeve along the axial direction, and a beta tube assembly extended through the sleeve along the axial direction. The beta tube assembly defines one or more internal walls. The one or more internal walls defines a hydraulic fluid transfer cavity in fluid communication with one or more hydraulic fluid transfer orifices.
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公开(公告)号：US11161597B2
公开(公告)日：2021-11-02
申请号：US16481937
申请日：2018-01-24
Applicant: GE Avio S.r.l.
Inventor： Davide Lauria , Alessio Gargioli , Simone Castellani , Marco Garabello
Abstract: The present disclosure is directed to a turbine engine (10) defining an axial direction, a radial direction, a circumferential direction, a first end (99) and a second end (98) opposite of the first end (99) along the axial direction. The turbine engine includes a propeller assembly (14) proximate to the first end including a plurality of blades (42) arranged in the circumferential direction disposed around an axial centerline (12), and a feathering mechanism (60) including a hollow piston rod (19). The feathering mechanism rotates the plurality of blades about a pitch axis (13) extended in the radial direction from the axial centerline. The turbine engine further includes a housing (45) proximate to the second end disposed in adjacent arrangement with the propeller assembly in the axial direction. The axial centerline is defined through the propeller assembly and the housing. The turbine engine further includes a beta tube assembly (100) extended through the hollow piston rod and at least partially through the housing in coaxial alignment with the axial centerline. The beta tube assembly defines an at least partially hollow walled pipe (101) extended along the axial direction. The beta tube assembly further defines a plurality of grooves (111, 112) extended along the axial direction proximate to the housing. A first groove (111) extends at least partially in the circumferential direction and along the axial direction to at least partially define a helix (114) corresponding to a rotatable range of the plurality of blades about the pitch axis, and a second groove (112) extends in the axial direction.
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公开(公告)号：US20190383331A1
公开(公告)日：2019-12-19
申请号：US16482065
申请日：2018-01-26
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 shaft assembly (95) for a turbine engine (10), wherein the turbine engine includes a fan or propeller assembly (14) and an engine core (20), and further wherein the fan or propeller assembly includes a gearbox (45), and wherein the engine core includes one or more rotors (32). The shaft assembly (95) includes a flexible shaft (100) defining a first end (101) and a second end (102) along the axial direction, wherein the first end is connected to the engine core (20) and the second end is connected to the gearbox (45), and wherein a plurality of splines (110) is defined at the second end (102) and coupled to a spline interface (46) at the gearbox (45); and a coupling (120) extended at least partially in the radial direction and coupled to the engine core and the flexible shaft.
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