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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：US20210087936A1
公开(公告)日：2021-03-25
申请号：US17025536
申请日：2020-09-18
Applicant: GE Avio S.r.l.
Inventor： Antonio Giuseppe D'Ettole
Abstract: A shroud assembly for a rotary component of a gas turbine engine defining a central axis extending along an axial direction, a radial direction extending perpendicular to the axial direction, and a circumferential direction perpendicular to both the central axis and the radial direction. The shroud assembly includes a plurality of tip shrouds, and each of the plurality of tip shrouds includes a shroud band. Further, each tip shroud of the plurality of tip shrouds is coupled to one of the plurality of rotor blades at a tip end. The plurality of tip shrouds includes a first tip shroud defining a first length in a first direction and a second tip shroud defining a second length in the first direction. Moreover, the second length is different than the first length.
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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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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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5.发明公开公开(公告)号：US20240110504A1
公开(公告)日：2024-04-04
申请号：US17955713
申请日：2022-09-29
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Ranganayakulu Alapati , Peeyush Pankaj , Sanjeev Sai Kumar Manepalli , Bhaskar Nanda Mondal , Thomas Moniz , N V Sai Krishna Emani , Shishir Paresh Shah , Anil Soni , Praveen Sharma , Randy T. Antelo , Antonio Giuseppe D'Ettole
CPC classification number: F02C3/067 , F02C3/10 , F05D2220/323 , F05D2240/24
Abstract: A gas turbine engine includes a fan located at a forward portion of the gas turbine engine, and a compressor section and a turbine section arranged in serial flow order. The compressor section and the turbine section together define a core airflow path. A rotary member is rotatable with the fan and with a low pressure turbine of the turbine section. The low pressure turbine includes a rotating drum to which a first airfoil structure is connected and extends radially inward toward the rotary member. A torque frame connects the rotating drum to the rotary member and transfers torque from the first airfoil structure mounted to the rotating drum to the rotary member. The torque frame includes an inner disk mounted to the rotary member, an outer ring and a second airfoil structure formed separately from the outer ring and connected thereto by a releasable connecting structure. The second airfoil structure extends radially inward from the outer ring toward the inner disk.
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Patent Agency Ranking
6.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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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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9.发明授权公开(公告)号：US12247516B2
公开(公告)日：2025-03-11
申请号：US17955713
申请日：2022-09-29
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Ranganayakulu Alapati , Peeyush Pankaj , Sanjeev Sai Kumar Manepalli , Bhaskar Nanda Mondal , Thomas Moniz , N V Sai Krishna Emani , Shishir Paresh Shah , Anil Soni , Praveen Sharma , Randy T. Antelo , Antonio Giuseppe D'Ettole
Abstract: A gas turbine engine includes a fan located at a forward portion of the gas turbine engine, and a compressor section and a turbine section arranged in serial flow order. The compressor section and the turbine section together define a core airflow path. A rotary member is rotatable with the fan and with a low pressure turbine of the turbine section. The low pressure turbine includes a rotating drum to which a first airfoil structure is connected and extends radially inward toward the rotary member. A torque frame connects the rotating drum to the rotary member and transfers torque from the first airfoil structure mounted to the rotating drum to the rotary member. The torque frame includes an inner disk mounted to the rotary member, an outer ring and a second airfoil structure formed separately from the outer ring and connected thereto by a releasable connecting structure. The second airfoil structure extends radially inward from the outer ring toward the inner disk.
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10.发明申请公开(公告)号：US20230112829A1
公开(公告)日：2023-04-13
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
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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