Patents by Inventor Romain Pierre CARIOU
Romain Pierre CARIOU 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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Publication number: 20240018872Abstract: The invention relates to a method for manufacturing a vane (11) of a turbine engine comprising a pressure-face wall (14) and a suction-face wall (15) spaced apart from one another, this vane (11) comprising a tip (S) with: a bottom wall (18) extending from the pressure-face wall (14) to the suction-face wall (15), each of which comprises a free edge (19, 21) extending beyond this bottom wall (18) to delimit, together with this bottom wall (18), a squealer shape (B); a partition wall (22) extending from the pressure-face wall (14) to the suction-face wall (15) and spaced apart from the bottom wall (18) to delimit, together with this bottom wall (18), a cavity (C) under the squealer tip; the method including: a moulding step to form at least the pressure-face wall (14), the suction-face wall (15) and the partition wall (22); —a step of forming the bottom wall (18) using an additive manufacturing method by adding metal material.Type: ApplicationFiled: December 8, 2021Publication date: January 18, 2024Applicant: SAFRANInventors: Leandre OSTINO, Romain Pierre CARIOU, Filippo PAGNONI, Sylvain PAQUIN, Adrien Bernard Vincent ROLLINGER
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Patent number: 11808167Abstract: A turbine engine blade includes an airfoil with a pressure-side wall and a suction-side wall which are connected upstream by a leading edge and downstream by a trailing edge. A cooling circuit has an internal cavity extending inside the airfoil and a plurality of outlet openings, each oriented substantially along a longitudinal axis X. Each outlet opening communicates with the cavity and is arranged in the vicinity of the trailing edge. A calibration device is arranged in the cavity and provided with calibration conduits arranged substantially opposite the outlet openings. The calibration conduits each include an oblong transverse section which is substantially perpendicular to the longitudinal axis.Type: GrantFiled: March 16, 2020Date of Patent: November 7, 2023Assignees: SAFRAN AIRCRAFT ENGINES, SAFRANInventors: Jérémy Jacques Attilio Fanelli, Romain Pierre Cariou, Vianney Simon, Ba-Phuc Tang
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Patent number: 11618071Abstract: A core for the foundry of an aeronautical part such as a turbine blade, the core being intended to be disposed in an inner housing defined by a mold, the core comprising a body intended to form the internal shape of the turbine blade, an impact portion, disposed on at least a portion of the periphery of the body so as to break a fluid jet when filling the inner housing with the fluid, the impact portion comprising a top and at least one deflection wall converging towards the top.Type: GrantFiled: April 12, 2019Date of Patent: April 4, 2023Assignee: SAFRANInventors: Adrien Bernard Vincent Rollinger, Ramzi Bohli, Ngadia Taha Niane, Alain Armel Le Hegarat, Romain Pierre Cariou, David Grange, Didier Maurice Marceau Guerche
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Patent number: 11499436Abstract: A turbine blade including a root carrying an impeller terminated by a tip in the form of a squealer tip. This impeller also includes a serpentine median circuit, including a first radial pipe collecting air at the root and that is connected by a first bend to a second radial pipe that is connected by a second bend to a third radial pipe, a cavity under the squealer tip running along the pressure side wall, extending from a central region of the tip to the trailing edge, and a radial central pipe collecting air at the root extending between at least two of the three pipes of the median circuit and directly supplying the cavity under the squealer tip.Type: GrantFiled: November 29, 2019Date of Patent: November 15, 2022Assignees: SAFRAN, SAFRAN AIRCRAFT ENGINESInventors: Léandre Ostino, Pierre Guillaume Auzillon, Romain Pierre Cariou, Thomas Olivier Michel Pierre De Rocquigny, Patrice Eneau, Adrien Bernard Vincent Rollinger, Vianney Simon, Michel Slusarz, Ba-Phuc Tang
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Patent number: 11421537Abstract: A turbine engine vane including a blade extending following a radial axis and a cooling circuit arranged inside the blade, the cooling circuit including a first cavity and a second cavity arranged downstream from the first cavity following a direction of circulation of a cooling fluid, the first and second cavities extend radially inside the blade and being separated at least partially by a radial partition having a radially external free end which delimits at least partially a passage connecting the first and second cavities, the radial partition connecting a first wall in contact with the outside environment of the blade to a second opposite wall substantially following a transversal axis, perpendicular to the radial axis, respectively in a connection zone. According to the invention, at least one connection zone presents a thickening having a substantially triangular general transversal cross-section.Type: GrantFiled: March 19, 2020Date of Patent: August 23, 2022Assignees: SAFRAN AIRCRAFT ENGINES, SAFRANInventors: Jeremy Jacques Attilio Fanelli, Romain Pierre Cariou, Thomas Olivier Michel Pierre De Rocquigny, Ba-Phuc Tang
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Publication number: 20220205365Abstract: A turbine vane includes a root carrying a blade terminated by a squealer tip, the blade having intrados and extrados walls, a leading edge, a trailing edge, and a tip wall delimiting a bottom of the squealer tip, by which the intrados wall is connected to the extrados wall. The blade also includes: a serpentine median circuit, including a first radial pipe that collects air at the root and is connected by a first bend to a second radial pipe that is connected by a second bend to a third radial pipe; a cavity under the squealer tip running along the extrados wall and extending from a central region of the squealer tip to the trailing edge; and a central radial pipe collecting air at the root and extending between at least two of the three pipes of the median circuit and directly supplying the cavity under the squealer tip.Type: ApplicationFiled: April 24, 2020Publication date: June 30, 2022Inventors: Léandre OSTINO, Pierre Guillaume AUZILLON, Michel SLUSARZ, Patrice ENEAU, Thomas Olivier Michel Pierre DE ROCQUIGNY, Romain Pierre CARIOU, Ba-Phuc TANG, Adrien Bernard Vincent ROLLINGER, Vianney SIMON
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Publication number: 20220178261Abstract: A turbine engine blade includes an airfoil with a pressure-side wall and a suction-side wall which are connected upstream by a leading edge and downstream by a trailing edge. A cooling circuit has an internal cavity extending inside the airfoil and a plurality of outlet openings, each oriented substantially along a longitudinal axis X. Each outlet opening communicates with the cavity and is arranged in the vicinity of the trailing edge. A calibration device is arranged in the cavity and provided with calibration conduits arranged substantially opposite the outlet openings. The calibration conduits each include an oblong transverse section which is substantially perpendicular to the longitudinal axis.Type: ApplicationFiled: March 16, 2020Publication date: June 9, 2022Applicant: SAFRAN AIRCRAFT ENGINESInventors: Jérémy Jacques Attilio FANELLI, Romain Pierre CARIOU, Vianney SIMON, Ba-Phuc TANG
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Patent number: 11248468Abstract: Aviation turbine blade (10) extending in the radial direction from a blade root (14) as far as an upper partition wall (26), said blade (10) comprising a plurality of inner cavities (C1-C10) defining at least one cooling circuit, each of said inner cavities (C1-C10) being defined by walls among inner walls (40, 42), a lower surface wall (22), an upper surface wall (24), the blade root (14) and the upper partition wall (26), said blade (10) being characterized in that it comprises at least one reinforcing beam (50, 60) disposed inside one of the inner cavities (C3, C8), and connecting the blade root (14) to the upper partition wall (26), said reinforcing beam (50, 60) is not connected to the inner walls (40, 42), the lower surface wall (22) and the upper surface wall (24).Type: GrantFiled: April 10, 2018Date of Patent: February 15, 2022Assignee: SAFRANInventors: Sylvain Paquin, Romain Pierre Cariou, Thomas Michel Flamme, Adrien Bernard Vincent Rollinger
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Patent number: 11236617Abstract: Blade for a turbine, comprising a blade root and an airfoil (13) extending radially outwards from the blade root (12), the airfoil (13) comprising a first internal cooling circuit including an intrados cavity (33, 36) extending radially along the intrados wall (16) and a first inner wall (47, 45) arranged between the intrados wall (16) and the extrados wall (18), an extrados cavity (34, 37) extending radially along the extrados wall (18) and a second inner wall (47, 43) arranged between the intrados wall (16) and the extrados wall (18). The first cooling circuit includes one inner through cavity (35, 38) defined between two through walls (59, 57, 55, 53) each extending between the intrados wall (16) and the extrados wall (18). The intrados cavity (33, 36), the extrados cavity (34, 37) and the inner through cavity (35, 38) are fluidly connected in series.Type: GrantFiled: April 10, 2018Date of Patent: February 1, 2022Assignee: SAFRANInventors: Thomas Michel Flamme, Romain Pierre Cariou, Sylvain Paquin, Adrien Bernard Vincent Rollinger
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Publication number: 20220025771Abstract: A turbine blade including a root carrying an impeller terminated by a tip in the form of a squealer tip. This impeller also includes a serpentine median circuit, including a first radial pipe collecting air at the root and that is connected by a first bend to a second radial pipe that is connected by a second bend to a third radial pipe, a cavity under the squealer tip running along the pressure side wall, extending from a central region of the tip to the trailing edge, and a radial central pipe collecting air at the root extending between at least two of the three pipes of the median circuit and directly supplying the cavity under the squealer tip.Type: ApplicationFiled: November 29, 2019Publication date: January 27, 2022Applicants: SAFRAN, SAFRAN AIRCRAFT ENGINESInventors: Léandre OSTINO, Pierre Guillaume AUZILLON, Romain Pierre CARIOU, Thomas Olivier Michel Pierre DE ROCQUIGNY, Patrice ENEAU, Adrien Bernard Vincent ROLLINGER, Vianney SIMON, Michel SLUSARZ, Ba-Phuc TANG
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Patent number: 11073025Abstract: An aviation turbine blade (10) includes at least a first lower surface cavity (C2) and a first upper surface cavity (C3), each adjacent to a first through-cavity (C1) and a second through-cavity (C4), the first upper surface cavity (C3) being adjacent to the upper surface wall (24), the first lower surface cavity (C2) being adjacent to the lower surface wall (22), each of the first and second through-cavities (C1, C4) extending from the lower surface wall (22) as far as the upper surface wall (24), the second through-cavity (C4) including a first inner wall (P1) extending from the upper surface wall (24) as far as the first through-cavity (C1), and a second inner wall (P2) extending from the lower surface wall (22) as far as the first through-cavity (C1). The first (P1) and second (P2) inner walls are not connected.Type: GrantFiled: April 10, 2018Date of Patent: July 27, 2021Assignee: SAFRANInventors: Sylvain Paquin, Romain Pierre Cariou, Thomas Michel Flamme, Adrien Bernard Vincent Rollinger
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Publication number: 20210138533Abstract: A core for the foundry of an aeronautical part such as a turbine blade, the core being intended to be disposed in an inner housing defined by a mold, the core comprising a body intended to form the internal shape of the turbine blade, an impact portion, disposed on at least a portion of the periphery of the body so as to break a fluid jet when filling the inner housing with the fluid, the impact portion comprising a top and at least one deflection wall converging towards the top.Type: ApplicationFiled: April 12, 2019Publication date: May 13, 2021Applicant: SAFRANInventors: Adrien Bernard Vincent ROLLINGER, Ramzi BOHLI, Ngadia Taha NIANE, Alain Armel LE HEGARAT, Romain Pierre CARIOU, David GRANGE, Didier Maurice Marceau GUERCHE
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Patent number: 10844733Abstract: An aviation turbine blade extending in the radial direction and presenting a pressure side and a suction side, including a plurality of pressure side cavities extending radially at the pressure side of the blade, a plurality of suction side cavities extending radially at the suction side of the blade, and at least one central cavity located in the central portion of the blade and surrounded by pressure side cavities and by suction side cavities, the blade further including a plurality of cooling circuits, in which at least a first cooling circuit comprises: a first cavity and a second cavity, the first and second cavities communicating with each other at a radially inner end and at a radially outer end of the blade.Type: GrantFiled: September 28, 2017Date of Patent: November 24, 2020Assignee: SAFRANInventors: Adrien Bernard Vincent Rollinger, Romain Pierre Cariou, Thomas Michel Flamme, Sylvain Paquin
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Publication number: 20200300095Abstract: A turbine engine vane including a blade extending following a radial axis and a cooling circuit arranged inside the blade, the cooling circuit including a first cavity and a second cavity arranged downstream from the first cavity following a direction of circulation of a cooling fluid, the first and second cavities extend radially inside the blade and being separated at least partially by a radial partition having a radially external free end which delimits at least partially a passage connecting the first and second cavities, the radial partition connecting a first wall in contact with the outside environment of the blade to a second opposite wall substantially following a transversal axis, perpendicular to the radial axis, respectively in a connection zone. According to the invention, at least one connection zone presents a thickening having a substantially triangular general transversal cross-section.Type: ApplicationFiled: March 19, 2020Publication date: September 24, 2020Inventors: Jeremy Jacques Attilio FANELLI, Romain Pierre CARIOU, Thomas Olivier Michel Pierre DE ROCQUIGNY, Ba-Phuc TANG
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Publication number: 20200157948Abstract: An aviation turbine blade (10) includes at least a first lower surface cavity (C2) and a first upper surface cavity (C3), each adjacent to a first through-cavity (C1) and a second through-cavity (C4), the first upper surface cavity (C3) being adjacent to the upper surface wall (24), the first lower surface cavity (C2) being adjacent to the lower surface wall (22), each of said first and second through-cavities (C1, C4) extending from the lower surface wall (22) as far as the upper surface wall (24), the second through-cavity (C4) including a first inner wall (P1) extending from the upper surface wall (24) as far as the first through-cavity (C1), and a second inner wall (P2) extending from the lower surface wall (22) as far as the first through-cavity (C1). The first (P1) and second (P2) inner walls are not connected.Type: ApplicationFiled: April 10, 2018Publication date: May 21, 2020Applicant: SAFRANInventors: Sylvain PAQUIN, Romain Pierre CARIOU, Thomas Michel FLAMME, Adrien Bernard Vincent ROLLINGER
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Publication number: 20200149405Abstract: Blade for a turbine, comprising a blade root and an airfoil (13) extending radially outwards from the blade root (12), the airfoil (13) comprising a first internal cooling circuit including an intrados cavity (33, 36) extending radially along the intrados wall (16) and a first inner wall (47, 45) arranged between the intrados wall (16) and the extrados wall (18), an extrados cavity (34, 37) extending radially along the extrados wall (18) and a second inner wall (47, 43) arranged between the intrados wall (16) and the extrados wall (18). The first cooling circuit includes one inner through cavity (35, 38) defined between two through walls (59, 57, 55, 53) each extending between the intrados wall (16) and the extrados wall (18). The intrados cavity (33, 36), the extrados cavity (34, 37) and the inner through cavity (35, 38) are fluidly connected in series.Type: ApplicationFiled: April 10, 2018Publication date: May 14, 2020Applicant: SAFRANInventors: Thomas Michel FLAMME, Romain Pierre CARIOU, Sylvain PAQUIN, Adrien Bernard Vincent ROLLINGER
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Publication number: 20200040741Abstract: Aviation turbine blade (10) extending in the radial direction from a blade root (14) as far as an upper partition wall (26), said blade (10) comprising a plurality of inner cavities (C1-C10) defining at least one cooling circuit, each of said inner cavities (C1-C10) being defined by walls among inner walls (40, 42), a lower surface wall (22), an upper surface wall (24), the blade root (14) and the upper partition wall (26), said blade (10) being characterized in that it comprises at least one reinforcing beam (50, 60) disposed inside one of the inner cavities (C3, C8), and connecting the blade root (14) to the upper partition wall (26), said reinforcing beam (50, 60) is not connected to the inner walls (40, 42), the lower surface wall (22) and the upper surface wall (24).Type: ApplicationFiled: April 10, 2018Publication date: February 6, 2020Applicant: SAFRANInventors: Sylvain PAQUIN, Romain Pierre CARIOU, Thomas Michel FLAMME, Adrien Bernard Vincent ROLLINGER
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Publication number: 20190211693Abstract: An aviation turbine blade extending in the radial direction and presenting a pressure side and a suction side, including a plurality of pressure side cavities extending radially at the pressure side of the blade, a plurality of suction side cavities extending radially at the suction side of the blade, and at least one central cavity located in the central portion of the blade and surrounded by pressure side cavities and by suction side cavities, the blade further including a plurality of cooling circuits, in which at least a first cooling circuit comprises: a first cavity and a second cavity, the first and second cavities communicating with each other at a radially inner end and at a radially outer end of the blade.Type: ApplicationFiled: September 28, 2017Publication date: July 11, 2019Applicant: SAFRANInventors: Adrien Bernard Vincent ROLLINGER, Romain Pierre CARIOU, Thomas Michel FLAMME, Sylvain PAQUIN