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公开(公告)号：US20220349350A1
公开(公告)日：2022-11-03
申请号：US17813453
申请日：2022-07-19
Applicant: GE Avio S.r.l.
Inventor： Juraj Hrubec , Davide Lauria
Abstract: A turbomachine engine according to aspects of the present disclosure is provided. The engine includes a fan assembly including a plurality of fan blades, and a core engine surrounded by an outer casing. The core engine includes a power output component operably connected to the fan assembly, a first input power source and a second input power source. The first input power source is counter-rotatable relative to the second input power source. The core engine includes a gear assembly operably connected to the power output component and configured to receive power from the first input power source and the second input power source.
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公开(公告)号：US11952948B2
公开(公告)日：2024-04-09
申请号：US17813453
申请日：2022-07-19
Applicant: GE Avio S.r.l.
Inventor： Juraj Hrubec , Davide Lauria
CPC classification number: F02C7/36 , F02C7/06 , F05D2260/40311
Abstract: A turbomachine engine according to aspects of the present disclosure is provided. The engine includes a fan assembly including a plurality of fan blades, and a core engine surrounded by an outer casing. The core engine includes a power output component operably connected to the fan assembly, a first input power source and a second input power source. The first input power source is counter-rotatable relative to the second input power source. The core engine includes a gear assembly operably connected to the power output component and configured to receive power from the first input power source and the second input power source.
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公开(公告)号：US20210270189A1
公开(公告)日：2021-09-02
申请号：US17150136
申请日：2021-01-15
Applicant: GE Avio S.r.l.
Inventor： Juraj Hrubec , Davide Lauria
Abstract: A turbomachine engine according to aspects of the present disclosure is provided. The engine includes a fan assembly including a plurality of fan blades, and a core engine surrounded by an outer casing. The core engine includes a power output component operably connected to the fan assembly, a first input power source and a second input power source. The first input power source is counter-rotatable relative to the second input power source. The core engine includes a gear assembly operably connected to the power output component and configured to receive power from the first input power source and the second input power source.
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公开(公告)号：US11408355B2
公开(公告)日：2022-08-09
申请号：US17150136
申请日：2021-01-15
Applicant: GE Avio S.r.l.
Inventor： Juraj Hrubec , Davide Lauria
Abstract: A turbomachine engine according to aspects of the present disclosure is provided. The engine includes a fan assembly including a plurality of fan blades, and a core engine surrounded by an outer casing. The core engine includes a power output component operably connected to the fan assembly, a first input power source and a second input power source. The first input power source is counter-rotatable relative to the second input power source. The core engine includes a gear assembly operably connected to the power output component and configured to receive power from the first input power source and the second input power source.
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公开(公告)号：US20210310417A1
公开(公告)日：2021-10-07
申请号：US17168368
申请日：2021-02-05
Applicant: GE Avio S.r.l.
Inventor： Juraj Hrubec , Ivan Golovin , Davide Lauria
Abstract: A gearbox for an engine includes a rotating element and a turbomachine, the turbomachine includes a shaft, and the rotating element is driven by the shaft across the gearbox. The gearbox includes a ring gear, a first sun gear and a second sun gear each configured to be driven by the shaft of the turbomachine, a first planet gear comprising a first gear portion and a second gear portion, and a second planet gear comprising a first gear portion and a second gear portion.
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Patent Agency Ranking
公开(公告)号：US11525370B2
公开(公告)日：2022-12-13
申请号：US17471576
申请日：2021-09-10
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Bojan Lukovic , Michael John Murray , Christian Michael Fernholz , Davide Lauria , Rocco Pellettieri , Steven Edward Nolte
IPC: F01D19/00
Abstract: An aspect of the present disclosure is directed to a method for mitigating rotor bow in a turbo machine. The method includes rotating a rotor over a first period of time; discontinuing rotation of the rotor for a second period of time; and iterating, over an overall period of time, rotation of the rotor over the first period of time and discontinuing rotation of the rotor for the second period of time.
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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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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：US11655767B2
公开(公告)日：2023-05-23
申请号：US17168368
申请日：2021-02-05
Applicant: GE Avio S.r.l.
Inventor： Juraj Hrubec , Ivan Golovin , Davide Lauria
CPC classification number: F02C7/36 , F16H1/46 , F16H57/082 , F05D2220/323 , F05D2240/60 , F05D2260/4031 , F05D2260/70 , F16H2057/085
Abstract: A gearbox for an engine includes a rotating element and a turbomachine, the turbomachine includes a shaft, and the rotating element is driven by the shaft across the gearbox. The gearbox includes a ring gear, a first sun gear and a second sun gear each configured to be driven by the shaft of the turbomachine, a first planet gear comprising a first gear portion and a second gear portion, and a second planet gear comprising a first gear portion and a second gear portion.
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公开(公告)号：US20220154594A1
公开(公告)日：2022-05-19
申请号：US17471576
申请日：2021-09-10
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Bojan Lukovic , Michael John Murray , Christian Michael Fernholz , Davide Lauria , Rocco Pellettieri , Steven Edward Nolte
IPC: F01D19/00
Abstract: An aspect of the present disclosure is directed to a method for mitigating rotor bow in a turbo machine. The method includes rotating a rotor over a first period of time; discontinuing rotation of the rotor for a second period of time; and iterating, over an overall period of time, rotation of the rotor over the first period of time and discontinuing rotation of the rotor for the second period of time.
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