Patents by Inventor Francesco Bertini
Francesco Bertini has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Patent number: 11959393Abstract: 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.Type: GrantFiled: November 10, 2021Date of Patent: April 16, 2024Assignees: General Electric Company, GE Avivo S.r.l.Inventors: Saurya Ranjan Ray, Francesco Bertini, Lyle Douglas Dailey, Jeffrey D. Clements, Jaikumar Loganathan, Simone Rosa Taddei
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Patent number: 11933193Abstract: A gas turbine engine comprising a set of circumferentially adjacent airfoils, the airfoils having an outer wall defining a pressure side and a suction side extending between a leading edge and a trailing edge to define a stream-wise direction, and between a root and a tip to define a span-wise direction, and a set of dimples provide on the outer wall of at least one of the airfoils, the set of dimples spaced in at least one of the stream-wise or span-wise directions.Type: GrantFiled: November 18, 2021Date of Patent: March 19, 2024Assignees: GE Avio S.r.l., General Electric CompanyInventors: Pratish Patil, Amit Goyal, Mahendran Manoharan, Francesco Bertini, Jaikumar Loganathan
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Patent number: 11905853Abstract: 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.Type: GrantFiled: April 13, 2021Date of Patent: February 20, 2024Assignee: GE AVIO S.r.l.Inventors: Alberto Buonvino, Luca Giacobone, Daniele Coutandin, Ernesto Sozio, Francesco Bertini
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Patent number: 11885233Abstract: 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).Type: GrantFiled: July 28, 2022Date of Patent: January 30, 2024Assignees: General Electric Company, GE Avio S.r.l.Inventors: Ernesto Sozio, Francesco Bertini, Jeffrey Donald Clements, Jonathan Ong, Lyle Douglas Dailey, Paul Hadley Vitt, Matteo Renato Usseglio
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Patent number: 11821334Abstract: 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.Type: GrantFiled: July 29, 2021Date of Patent: November 21, 2023Assignee: GE AVIO S.R.L.Inventors: Massimiliano Airaudo, Paolo Calza, Francesco Bertini, Matteo Renato Usseglio, Cristian Lizzer, Ernesto Sozio, Matteo Furfaro, Marco Thiene
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Publication number: 20230296024Abstract: 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.Type: ApplicationFiled: September 23, 2022Publication date: September 21, 2023Inventors: Francesco Bertini, Davide Torzo, Pratish Patil, John Joseph, Mahendran Manoharan, Ganesh Seshadri
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Publication number: 20230130213Abstract: 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).Type: ApplicationFiled: July 28, 2022Publication date: April 27, 2023Inventors: Ernesto Sozio, Francesco Bertini, Jeffrey Donald Clements, Jonathan Ong, Lyle Douglas Dailey, Paul Hadley Vitt, Matteo Renato Usseglio
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Patent number: 11434765Abstract: 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).Type: GrantFiled: January 14, 2021Date of Patent: September 6, 2022Assignees: General Electric Company, GE AVIO S.r.l.Inventors: Ernesto Sozio, Francesco Bertini, Jeffrey Donald Clements, Jonathan Ong, Lyle Douglas Dailey, Paul Hadley Vitt, Matteo Renato Usseglio
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Publication number: 20220243596Abstract: 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.Type: ApplicationFiled: November 10, 2021Publication date: August 4, 2022Inventors: Saurya Ranjan Ray, Francesco Bertini, Lyle Douglas Dailey, Jeffrey D. Clements, Jaikumar Loganathan, Simone Rosa Taddei
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Publication number: 20220220854Abstract: A gas turbine engine comprising a set of circumferentially adjacent airfoils, the airfoils having an outer wall defining a pressure side and a suction side extending between a leading edge and a trailing edge to define a stream-wise direction, and between a root and a tip to define a span-wise direction, and a set of dimples provide on the outer wall of at least one of the airfoils, the set of dimples spaced in at least one of the stream-wise or span-wise directions.Type: ApplicationFiled: November 18, 2021Publication date: July 14, 2022Inventors: Pratish Patil, Amit Goyal, Mahendran Manoharan, Francesco Bertini, Jaikumar Loganathan
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Publication number: 20220098987Abstract: 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.Type: ApplicationFiled: July 29, 2021Publication date: March 31, 2022Inventors: Massimiliano Airaudo, Paolo Calza, Francesco Bertini, Matteo Renato Usseglio, Cristian Lizzer, Ernesto Sozio, Matteo Furfaro, Marco Thiene
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Publication number: 20210381389Abstract: 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.Type: ApplicationFiled: April 13, 2021Publication date: December 9, 2021Inventors: Alberto Buonvino, Luca Giacobone, Daniele Coutandin, Ernesto Sozio, Francesco Bertini
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Patent number: 11125089Abstract: A turbomachinery apparatus includes: a turbine, including: a turbine component defining an arcuate flowpath surface; an array of axial-flow turbine airfoils extending from the flowpath surface, the turbine airfoils defining spaces therebetween; and a plurality of fences extending from the flowpath surface, in the spaces between the turbine airfoils, each fence having opposed concave and convex sides extending between a leading edge and a trailing edge, wherein the fences have a nonzero camber and a constant thickness, are axially located near the leading edges of adjacent turbine airfoils, and wherein at least one of a chord dimension of the fences and a span dimension of the fences is less than the corresponding dimension of the turbine airfoils.Type: GrantFiled: August 7, 2019Date of Patent: September 21, 2021Assignees: General Electric Company, GE Avio S.r.l.Inventors: Francesco Bertini, Aspi Rustom Wadia, Lyle D. Dailey, Andrea Arnone, Filippo Rubechini, Matteo Giovannini, Paul Hadley Vitt, Jeffrey Donald Clements
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Publication number: 20210270137Abstract: 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).Type: ApplicationFiled: January 14, 2021Publication date: September 2, 2021Inventors: Ernesto Sozio, Francesco Bertini, Jeffrey Donald Clements, Jonathan Ong, Lyle Douglas Dailey, Paul Hadley Vitt, Matteo Renato Usseglio
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Publication number: 20200362713Abstract: A turbomachinery apparatus includes: a turbine, including: a turbine component defining an arcuate flowpath surface; an array of axial-flow turbine airfoils extending from the flowpath surface, the turbine airfoils defining spaces therebetween; and a plurality of fences extending from the flowpath surface, in the spaces between the turbine airfoils, each fence having opposed concave and convex sides extending between a leading edge and a trailing edge, wherein the fences have a nonzero camber and a constant thickness, are axially located near the leading edges of adjacent turbine airfoils, and wherein at least one of a chord dimension of the fences and a span dimension of the fences is less than the corresponding dimension of the turbine airfoils.Type: ApplicationFiled: August 7, 2019Publication date: November 19, 2020Inventors: Francesco Bertini, Aspi Rustom Wadia, Lyle D. Dailey, Andrea Arnone, Filippo Rubechinni, Matteo Giovanni, Paul Hadley Vitt, Jeffrey Donald Clements
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Publication number: 20200049014Abstract: 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.Type: ApplicationFiled: March 6, 2018Publication date: February 13, 2020Inventors: Jeffrey Donald Clements, Paul Hadley Vitt, Francesco Bertini, Aspi Rustom Wadia, Ganesh Seshadri, Mahendran Manoharan, Ravikanth Avancha
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Patent number: 9506348Abstract: According to the method, a turbine aerofoil is made starting from a reference aerofoil, locally reducing the metallic exit angle at the trailing edge in two areas which substantially correspond, in use, to the position of the peaks of the secondary flows in the boundary layer.Type: GrantFiled: November 2, 2012Date of Patent: November 29, 2016Assignee: GE AVIO S.r.L.Inventor: Francesco Bertini
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Publication number: 20140298651Abstract: According to the method, a turbine aerofoil is made starting from a reference aerofoil, locally reducing the metallic exit angle at the trailing edge in two areas which substantially correspond, in use, to the position of the peaks of the secondary flows in the boundary layer.Type: ApplicationFiled: November 2, 2012Publication date: October 9, 2014Applicant: GE AVIO S.r.L.Inventor: Francesco Bertini