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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：US20240254884A1
公开(公告)日：2024-08-01
申请号：US18635858
申请日：2024-04-15
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Francesco Bertini , Davide Torzo , Pratish Patil , John Joseph , Mahendran Manoharan , Ganesh Seshadri
IPC: F01D5/14
CPC classification number: F01D5/142 , F05D2220/323 , F05D2240/12 , F05D2240/30
Abstract: Aerodynamically mistuned airfoils for unsteady loss reductions are disclosed herein. An example apparatus disclosed herein includes a disk, a first airfoil coupled to the disk, the first airfoil having a first geometry, and a second airfoil coupled to the disk adjacent to the first airfoil, the second airfoil having a second geometry different than the first geometry, the first airfoil and the second airfoil produce non-uniform wake passing times during operation of the disk.
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公开(公告)号：US20240254882A1
公开(公告)日：2024-08-01
申请号：US18594594
申请日：2024-03-04
Applicant: GE Avio S.r.l. , General Electric Company
Inventor： Saurya Ranjan Ray , Francesco Bertini , Lyle Douglas Dailey , Jeffrey D. Clements , Jaikumar Loganathan , Simone Rosa Taddei
IPC: F01D5/14
CPC classification number: F01D5/141 , F05D2240/301 , F05D2240/305 , F05D2240/306 , F05D2250/181 , F05D2250/711 , F05D2250/712
Abstract: An airfoil assembly has a platform and an airfoil. The platform has an upstream edge, a downstream edge, and a surface extending between the upstream edge and the downstream edge. At least a portion of the surface extends circumferentially along a surface baseline defined by a constant radial distance from the rotational axis. The airfoil has an outer wall. The outer wall extends between a root and a tip, and between a leading edge and a trialing edge. The airfoil assembly includes a fence provided along the outer wall.
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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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Patent Agency Ranking
公开(公告)号：US20230296024A1
公开(公告)日：2023-09-21
申请号：US17951653
申请日：2022-09-23
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Francesco Bertini , Davide Torzo , Pratish Patil , John Joseph , Mahendran Manoharan , Ganesh Seshadri
IPC: F01D5/14
CPC classification number: F01D5/142 , F05D2220/323 , F05D2240/12 , F05D2240/30
Abstract: Aerodynamically mistuned airfoils for unsteady loss reductions are disclosed herein. An example apparatus disclosed herein includes a disk, a first airfoil coupled to the disk, the first airfoil having a first geometry, and a second airfoil coupled to the disk adjacent to the first airfoil, the second airfoil having a second geometry different than the first geometry, the first airfoil and the second airfoil produce non-uniform wake passing times during operation of the disk.
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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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公开(公告)号：US20250146418A1
公开(公告)日：2025-05-08
申请号：US19013045
申请日：2025-01-08
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Jeffrey Donald Clements , Paul Hadley Vitt , Francesco Bertini , Aspi Rustom Wadia , Ganesh Seshadri , Mahendran Manoharan , Ravikanth Avancha
Abstract: A turbomachinery apparatus 10 includes: a turbine 22, including: a turbine component 36 defining at least one arcuate flowpath surface 40; an array of axial-flow turbine airfoils 46 extending from the flowpath surface, the turbine airfoils defining spaces therebetween; and a plurality of splitter airfoils 146 extending from the at least one flowpath surface, in the spaces between the turbine airfoils, each splitter airfoil having opposed pressure and suction sides extending between a leading edge and a trailing edge, wherein the splitter airfoils have a thickness ratio which is less than a thickness ratio of the turbine airfoils.
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公开(公告)号：US20220243596A1
公开(公告)日：2022-08-04
申请号：US17523505
申请日：2021-11-10
Applicant: GE Avio S.r.l. , General Electric Company
Inventor： Saurya Ranjan Ray , Francesco Bertini , Lyle Douglas Dailey , Jeffrey D. Clements , Jaikumar Loganathan , Simone Rosa Taddei
IPC: F01D5/14
Abstract: An airfoil assembly for a turbine engine comprising an outer band, an inner band radially spaced inwardly from the outer band to define an annular region, and multiple airfoils circumferentially spaced within the annular region. Each corresponding airfoil of the multiple airfoils can project from a surface at a root and can further include an outer wall defining a pressure side and a suction side. A projection can extend upwardly from the surface on the pressure side and a valley can extend into the surface on the suction side to define a contour in the surface.
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