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公开(公告)号：US20210270137A1
公开(公告)日：2021-09-02
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
IPC: F01D5/14
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：US20210381389A1
公开(公告)日：2021-12-09
申请号：US17228778
申请日：2021-04-13
Applicant: GE Avio S.r.l.
Inventor： Alberto Buonvino , Luca Giacobone , Daniele Coutandin , Ernesto Sozio , Francesco Bertini
Abstract: An airfoil assembly defining a primary airflow path for a turbine engine comprising a platform, an airfoil extending from the platform and into at least a portion of the primary airflow path, a secondary airflow path comprising air from the primary airflow path, and a deflector provided within the secondary airflow path.
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公开(公告)号：US11821334B2
公开(公告)日：2023-11-21
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
CPC classification number: F01D5/187 , F01D5/143 , F05D2240/307 , F05D2250/185 , F05D2260/2212 , F05D2260/22141
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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Patent Agency Ranking
公开(公告)号：US20230130213A1
公开(公告)日：2023-04-27
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
IPC: F01D5/14
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：US11905853B2
公开(公告)日：2024-02-20
申请号：US17228778
申请日：2021-04-13
Applicant: GE Avio S.r.l.
Inventor： Alberto Buonvino , Luca Giacobone , Daniele Coutandin , Ernesto Sozio , Francesco Bertini
CPC classification number: F01D9/041 , F01D5/14 , F01D5/141 , F01D11/001 , F01D11/006 , F05D2220/32 , F05D2240/12 , F05D2240/30
Abstract: An airfoil assembly defining a primary airflow path for a turbine engine comprising a platform, an airfoil extending from the platform and into at least a portion of the primary airflow path, a secondary airflow path comprising air from the primary airflow path, and a deflector provided within the secondary airflow 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：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：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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