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11.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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公开(公告)号：US20210032999A1
公开(公告)日：2021-02-04
申请号：US16935458
申请日：2020-07-22
Applicant: GE Avio S.r.l.
Inventor： Antonio Giusseppe D'Ettole , Andrea Depalma , Roberto Maddaleno , Luca Giacobone , Matteo Renato Usseglio
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 tip and a root. The root of each of the circumferentially arranged components can terminate at an inner platform, where the collection of inner platforms can define an inner band.
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公开(公告)号：US11661893B2
公开(公告)日：2023-05-30
申请号：US17454129
申请日：2021-11-09
Applicant: GE Avio S.r.l.
CPC classification number: F02C7/36 , F02C7/06 , F05D2230/72 , F05D2260/40311 , F05D2260/98
Abstract: A method of servicing a gas turbine engine, the method including preparing the gas turbine engine for service; installing a shaft protection cover to an aft end of a fan shaft of the gas turbine engine; installing an oil collector drum at least partially around a gearbox of the gas turbine engine; and removing at least a portion of the gearbox from the gas turbine engine.
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Patent Agency Ranking
14.发明授权公开(公告)号：US11549379B2
公开(公告)日：2023-01-10
申请号：US16988817
申请日：2020-08-10
Applicant: GE Avio S.r.l.
Inventor： Matteo Renato Usseglio , Antonio Giuseppe D'Ettole , Andrea Depalma
Abstract: A blade for a turbomachine includes a blade root portion for securing the blade to a rotatable annular outer drum rotor. The blade root portion includes one or more radial retention features for radially retaining each of the blade root portions within the rotatable annular outer drum rotor. Further, at least one of the radial retention feature(s) includes at least one sealing member integrated therewith.
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公开(公告)号：US20220364473A1
公开(公告)日：2022-11-17
申请号：US17863470
申请日：2022-07-13
Applicant: GE Avio S.r.l.
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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公开(公告)号：US20220146043A1
公开(公告)日：2022-05-12
申请号：US17454129
申请日：2021-11-09
Applicant: GE Avio S.r.l.
Abstract: A method of servicing a gas turbine engine, the method including preparing the gas turbine engine for service; installing a shaft protection cover to an aft end of a fan shaft of the gas turbine engine; installing an oil collector drum at least partially around a gearbox of the gas turbine engine; and removing at least a portion of the gearbox from the gas turbine engine.
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公开(公告)号：US11156109B2
公开(公告)日：2021-10-26
申请号：US16987747
申请日：2020-08-07
Applicant: GE Avio S.r.l.
Inventor： Andrea Depalma , Antonio Giuseppe D'Ettole , Matteo Renato Usseglio
Abstract: A turbomachine includes a rotatable annular outer drum rotor connected to a first plurality of blades. Each of the first plurality of blades includes a blade root portion secured to the rotatable annular outer drum rotor. Each of the blade root portions includes one or more structural radial retention features for radially retaining each of the blade root portions within the rotatable annular outer drum and one or more axial retention features for axially retaining each of the blade root portions within the rotatable annular outer drum.
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公开(公告)号：US20210047930A1
公开(公告)日：2021-02-18
申请号：US16988833
申请日：2020-08-10
Applicant: GE Avio S.r.l.
Inventor： Andrea Depalma , Antonio Giuseppe D'Ettole , Matteo Renato Usseglio
Abstract: A turbomachine includes a rotatable annular outer drum rotor connected to a first plurality of blades. The rotatable annular outer drum rotor is constructed of, at least, a first drum segment and a second drum segment. The turbomachine further includes a retaining ring arranged and secured between the first and second drum segments of the rotatable annular outer drum rotor for radially retaining each of the first plurality of blades via their respective blade root portions within the rotatable annular outer drum rotor.
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