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公开(公告)号：US20180355740A1
公开(公告)日：2018-12-13
申请号：US15997421
申请日：2018-06-04
Applicant: GE Avio S.r.l.
Inventor： Matteo Renato Usseglio , Enrico Ganzitti
CPC classification number: F01D9/042 , F01D11/005 , F01D25/246 , F05D2240/15 , F05D2240/57
Abstract: An apparatus for turbine engine including a turbine section with at least one turbine stage having a stationary vane assembly and a rotating blade assembly with combustion gases flowing through the turbine stage in a fore to aft direction. An interface is formed between a portion of the outer casing and a portion of the stationary vane assembly defining a leak flow path (LFP) where a seal is placed to retard combustion gases in the leak path.
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公开(公告)号：US11885233B2
公开(公告)日：2024-01-30
申请号：US17876009
申请日：2022-07-28
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Ernesto Sozio , Francesco Bertini , Jeffrey Donald Clements , Jonathan Ong , Lyle Douglas Dailey , Paul Hadley Vitt , Matteo Renato Usseglio
CPC classification number: F01D5/141 , F04D29/324 , F04D29/544 , F05D2220/32 , F05D2240/30
Abstract: A turbine engine with at least a compressor section, combustor section, turbine section and a set of airfoils. The airfoils include geometric characteristics to create a high contraction ratio (CR), a low blade turning (BT) at a radially inward location the airfoil, a low solidity, or a low aspect ratio (AR).
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公开(公告)号：US20230374935A1
公开(公告)日：2023-11-23
申请号：US17747497
申请日：2022-05-18
Inventor： Paul Hadley Vitt , Lyle Douglas Dailey , Matteo Renato Usseglio , Andreas Peters
CPC classification number: F02C3/067 , F02C6/00 , F02C7/36 , F05D2220/76
Abstract: A turbine section for a gas turbine engine defines a radial direction and includes a low-pressure (LP) turbine that includes a first plurality of LP turbine blades that includes a first stage having first stage LP turbine blades that rotate in a first direction at a first speed, a second plurality of LP turbine blades that includes a plurality of stages of LP turbine blades disposed downstream of the first stage LP turbine blades that rotate in a second direction opposite the first direction at a second speed, a first LP turbine spool connected to the first plurality of LP turbine blades on an inner side of the first plurality of LP turbine blades in the radial direction, and a second LP turbine spool connected to the second plurality of LP turbine blades on an inner side of the second plurality of LP turbine blades in the radial direction
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公开(公告)号：US11434765B2
公开(公告)日：2022-09-06
申请号：US17148635
申请日：2021-01-14
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Ernesto Sozio , Francesco Bertini , Jeffrey Donald Clements , Jonathan Ong , Lyle Douglas Dailey , Paul Hadley Vitt , Matteo Renato Usseglio
Abstract: A turbine engine with at least a compressor section, combustor section, turbine section and a set of airfoils. The airfoils include geometric characteristics to create a high contraction ratio (CR), a low blade turning (BT) at a radially inward location the airfoil, a low solidity, or a low aspect ratio (AR).
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公开(公告)号：US11414994B2
公开(公告)日：2022-08-16
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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Patent Agency Ranking
公开(公告)号：US20220098987A1
公开(公告)日：2022-03-31
申请号：US17388143
申请日：2021-07-29
Applicant: GE Avio S.r.l.
Inventor： Massimiliano Airaudo , Paolo Calza , Francesco Bertini , Matteo Renato Usseglio , Cristian Lizzer , Ernesto Sozio , Matteo Furfaro , Marco Thiene
Abstract: A turbine blade including an airfoil portion extending between a leading edge and a trailing edge, a base portion positioned below the airfoil portion, the base portion including an outwardly-extending wing positioned below the airfoil portion, and an aero-brake feature positioned between the outwardly-extending wing and the airfoil portion and extending outward from the base portion, where the aero-brake feature is structurally configured to disrupt axial airflow across the turbine blade.
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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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18.发明申请公开(公告)号：US20210047933A1
公开(公告)日：2021-02-18
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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19.发明授权公开(公告)号：US11885237B2
公开(公告)日：2024-01-30
申请号：US18080849
申请日：2022-12-14
Applicant: GE Avio S.r.l.
Inventor： Matteo Renato Usseglio , Antonio Giuseppe D'Ettole , Andrea Depalma
CPC classification number: F01D5/20 , F01D5/022 , F01D5/06 , F01D5/225 , F01D5/323 , F05D2220/32 , F05D2260/30
Abstract: A turbomachine having an engine centerline and a first rotor. The first rotor having a first annular drum and being connected to a first plurality of blades. At least one blade of the first plurality of blades having a blade root, a blade tip, a first arm, a second arm and a first seal. The first arm extending from the blade root and having a radial retention hook. The second arm extending from the blade tip.
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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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