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公开(公告)号：US20210087939A1
公开(公告)日：2021-03-25
申请号：US16936567
申请日：2020-07-23
Applicant: GE Avio S.r.l.
Abstract: A turbine engine with an outer rotor that circumscribes an inner rotor or inner stator. The outer rotor includes circumferentially arranged components with a radial outer end and radial inner end. Inner ends of confronting sides of adjacent components include at least one damper element to dampen the relative motion of the components or to provide at least a partial seal between adjacent components.
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公开(公告)号：US20220162961A1
公开(公告)日：2022-05-26
申请号：US17471621
申请日：2021-09-10
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Roberto Maddaleno , Antonio Giuseppe D'Ettole , Matteo Renato Usseglio , Alessandra Torri , Darek Tomasz Zatorski
Abstract: A turbomachine, a computing system for a turbomachine, and a method for overspeed protection are provided. The turbomachine includes a first rotor assembly interdigitated with a second rotor assembly together operably coupled to a gear assembly. A plurality of sensors is configured to receive rotor state data indicative of one or more of a speed, geometric dimension, or capacitance, or change thereof, or rate of change thereof, relative to the first rotor assembly or the second rotor assembly. A controller executes operations including receiving rotor state data from the plurality of sensors; comparing rotor state data to one or more rotor state limits; and contacting one or more of the first rotor assembly or the second rotor assembly to a contact surface adjacent to the respective first rotor assembly or the second rotor assembly if the rotor state data exceeds the rotor state limit.
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公开(公告)号：US20220128010A1
公开(公告)日：2022-04-28
申请号：US17469960
申请日：2021-09-09
Applicant: GE Avio S.r.l.
Abstract: A method for engine assembly is provided, the method including forming an interdigitated rotor assembly comprising an inner rotor assembly rotatable at a first speed different from an outer rotor assembly rotatable at a second speed; fastening a gear assembly to the interdigitated rotor assembly to form an interdigitated turbine assembly; and coupling the interdigitated turbine assembly to a gas generator, wherein coupling the interdigitated turbine assembly to the gas generator includes coupling a planet carrier assembly of the gear assembly to a static frame of the gas generator.
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公开(公告)号：US20210277832A1
公开(公告)日：2021-09-09
申请号：US17178371
申请日：2021-02-18
Applicant: GE Avio S.r.l.
Inventor： Roberto Maddaleno , Matteo Renato Usseglio , Darek Tomasz Zatorski
Abstract: Turbomachines and turbine sections of a turbomachine are provided. For example, a turbomachine comprises a turbine section having a turbine comprising a first plurality and a second plurality of turbine rotor blades, which are alternatingly spaced along an axial direction. At least one turbine blade of the first plurality of turbine blades is attached to a first support member assembly and at least one turbine blade of the second plurality of turbine blades is attached to a second support member assembly. The turbomachine further comprises a spool that connects the turbine with one or more components outside the turbine section, a first rotational support, and a gearbox. Both the first support member assembly and the second support member assembly are attached to the first rotational support and coupled to the gearbox such that the first and second pluralities of turbine rotor blades are rotatable with one another through the gearbox.
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公开(公告)号：US11946388B2
公开(公告)日：2024-04-02
申请号：US17863470
申请日：2022-07-13
Applicant: GE Avio S.r.l.
CPC classification number: F01D5/225 , F01D11/125 , F05D2220/32 , F05D2240/30 , F05D2240/55
Abstract: A turbine engine with an outer rotor that circumscribes an inner rotor. The outer rotor includes circumferentially arranged components with a radial outer end and radial inner end. Inner ends of confronting sides of adjacent components include at least one damper element to dampen the relative motion of the components or to provide at least a partial seal between adjacent components.
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Patent Agency Ranking
公开(公告)号：US11873725B2
公开(公告)日：2024-01-16
申请号：US17694956
申请日：2022-03-15
Applicant: GE Avio S.r.l.
Inventor： Roberto Maddaleno , Andrea Depalma , Antonio Giuseppe D'Ettole , Matteo Renato Usseglio , Christian Campanale
CPC classification number: F01D25/243 , F01D25/30 , F05D2240/70 , F05D2260/31
Abstract: A fastener cover for a flanged joint including first and second annular flanges extending about an axis, comprising: an annular, axially-extending, inboard wall; an annular, axially-extending outboard wall positioned radially outboard of the inboard wall; and a first radial wall interconnecting the inboard and outboard walls, wherein, collectively, the inboard and outboard walls and the first radial wall define a cavity for receiving a portion of a fastener; at least one fastener pocket including sidewalls extending axially away from the first radial wall and defining a tubular shape, which is closed off opposite the first radial wall by a floor plate having a clearance hole passing therethrough for accepting a shank of the fastener; and wherein the cover includes a balance weight receptacle for accepting at least one balance weight.
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公开(公告)号：US20230167745A1
公开(公告)日：2023-06-01
申请号：US17888539
申请日：2022-08-16
Applicant: GE Avio S.r.l
Inventor： Roberto Maddaleno , Matteo Renato Usseglio
IPC: F01D5/30
CPC classification number: F01D5/3053 , F01D5/3015 , F05D2220/32 , F05D2230/60 , F05D2240/30
Abstract: A rotating blade assembly for a turbine engine having a drive shaft, the rotating blade assembly comprising a disc, at least one blade assembly, and a retainer. The disc being operably coupled to the drive shaft and including a seat having at least a portion of a first through hole. The at least one blade assembly having an upper platform, a lower platform, a dovetail extending from the lower platform, and a blade extending between the upper platform and the lower platform. The retainer assembly securing the disc to the at least one blade assembly and comprising a hollow tubular element, a pin, and a fastener.
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公开(公告)号：US11692457B2
公开(公告)日：2023-07-04
申请号：US17471621
申请日：2021-09-10
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Roberto Maddaleno , Antonio Giuseppe D'Ettole , Matteo Renato Usseglio , Alessandra Torri , Darek Tomasz Zatorski
CPC classification number: F01D21/02 , F01D21/003 , F05D2260/40311 , F05D2260/902 , F05D2270/021 , F05D2270/304
Abstract: A turbomachine, a computing system for a turbomachine, and a method for overspeed protection are provided. The turbomachine includes a first rotor assembly interdigitated with a second rotor assembly together operably coupled to a gear assembly. A plurality of sensors is configured to receive rotor state data indicative of one or more of a speed, geometric dimension, or capacitance, or change thereof, or rate of change thereof, relative to the first rotor assembly or the second rotor assembly. A controller executes operations including receiving rotor state data from the plurality of sensors; comparing rotor state data to one or more rotor state limits; and contacting one or more of the first rotor assembly or the second rotor assembly to a contact surface adjacent to the respective first rotor assembly or the second rotor assembly if the rotor state data exceeds the rotor state limit.
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公开(公告)号：US20220333503A1
公开(公告)日：2022-10-20
申请号：US17694956
申请日：2022-03-15
Applicant: GE Avio S.r.l.
Inventor： Roberto Maddaleno , Andrea Depalma , Antonio Giuseppe D'Ettole , Matteo Renato Usseglio , Christian Campanale
Abstract: A fastener cover for a flanged joint including first and second annular flanges extending about an axis, comprising: an annular, axially-extending, inboard wall; an annular, axially-extending outboard wall positioned radially outboard of the inboard wall; and a first radial wall interconnecting the inboard and outboard walls, wherein, collectively, the inboard and outboard walls and the first radial wall define a cavity for receiving a portion of a fastener; at least one fastener pocket including sidewalls extending axially away from the first radial wall and defining a tubular shape, which is closed off opposite the first radial wall by a floor plate having a clearance hole passing therethrough for accepting a shank of the fastener; and wherein the cover includes a balance weight receptacle for accepting at least one balance weight.
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10.发明授权公开(公告)号：US11473439B1
公开(公告)日：2022-10-18
申请号：US17448621
申请日：2021-09-23
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Luca Giacobone , Matteo Renato Usseglio , Andrea Depalma , Roberto Maddaleno , Darek Tomasz Zatorski
Abstract: A gas turbine engine defining a longitudinal direction and a radial direction is provided. The gas turbine engine includes a turbine section comprising a stationary outer portion, a first rotating component, and a second rotating component, wherein the first rotating component includes an aft airfoil defining a hollow passageway and coupled to a radially extended first rotor portion, wherein the hollow passageway is in fluid communication with the stationary outer portion, wherein the second rotating component is coupled to a radially extended second rotor portion; and a seal assembly between a portion of the first rotating component and the second rotating component, the seal assembly defining a balance piston cavity therebetween, wherein the balance piston cavity is in fluid communication with the hollow passageway, wherein a flow of air is routed through the stationary outer portion and the hollow passageway to the balance piston cavity, and wherein a pressure of the flow of air within the balance piston cavity is controlled to provide an axial thrust that counteracts a thrust load on the second rotor portion.
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