Patents by Inventor Léandre OSTINO
Léandre OSTINO 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: 11795828Abstract: A blade for a turbomachine intended to be disposed about an axis while extending radially between a radially outer end and a radially inner end, the blade having at least one cooling cavity opening out to the radially outer end of the blade and to the radially inner end of the blade, the blade having at least a first tubular liner and at least a second tubular liner each engaged in the cavity, the radially outer end of the first liner opening out to the radially outer end of the blade, and the radially inner end of the second liner opening out to the radially inner end of the blade.Type: GrantFiled: March 16, 2020Date of Patent: October 24, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Matthieu Simon, Jean-Luc Bacha, Paul Danre, Léandre Ostino
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Patent number: 11773727Abstract: A blade of a turbomachine turbine, including a platform and a vane, including a cooling area extending along the trailing edge, with three distinct types of orifices, wherein the blade includes, at the root of the blade, a first type of orifices formed in the thickness of the trailing edge fillet, at the top of the blade, a third type of orifice formed in the thickness of at least one of the lower surface and upper surface walls, and in the middle of the blade, a second type of orifice formed in the thickness of at least one of the lower surface and upper surface walls. The lower surface wall, the upper surface wall and the trailing edge fillet define a dihedral with a radially changing radius and spacing.Type: GrantFiled: March 9, 2021Date of Patent: October 3, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Leandre Ostino, Filippo Pagnoni
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Patent number: 11753945Abstract: A turbomachine turbine blade, includes a platform, a vane, a cooling cavity supplying a plurality of cooling outlets provided along the trailing edge, two radially adjacent cooling outlets defining therebetween a rib. At least one cooling hole is formed in the thickness of at least one rib and/or in the thickness of a portion of the trailing edge fillet located in the axial extension of at least one rib, so as to ensure fluid communication for a cooling flow between the inside and the outside of the blade for cooling the at least one rib.Type: GrantFiled: March 9, 2021Date of Patent: September 12, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Léandre Ostino, Erwan Daniel Botrel
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Publication number: 20230123944Abstract: A blade of a turbomachine turbine, including a platform and a vane, including a cooling area extending along the trailing edge, with three distinct types of orifices, wherein the blade includes, at the root of the blade, a first type of orifices formed in the thickness of the trailing edge fillet, at the top of the blade, a third type of orifice formed in the thickness of at least one of the lower surface and upper surface walls, and in the middle of the blade, a second type of orifice formed in the thickness of at least one of the lower surface and upper surface walls. The lower surface wall, the upper surface wall and the trailing edge fillet define a dihedral with a radially changing radius and spacing.Type: ApplicationFiled: March 9, 2021Publication date: April 20, 2023Applicant: SAFRAN AIRCRAFT ENGINESInventors: Leandre OSTINO, Filippo PAGNONI
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Publication number: 20230098861Abstract: A turbomachine turbine blade, includes a platform, a vane, a cooling cavity supplying a plurality of cooling outlets provided along the trailing edge, two radially adjacent cooling outlets defining therebetween a rib. At least one cooling hole is formed in the thickness of at least one rib and/or in the thickness of a portion of the trailing edge fillet located in the axial extension of at least one rib, so as to ensure fluid communication for a cooling flow between the inside and the outside of the blade for cooling the at least one rib.Type: ApplicationFiled: March 9, 2021Publication date: March 30, 2023Inventors: Léandre OSTINO, Erwan Daniel BOTREL
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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: 11389860Abstract: A hollow turbomachine turbine blade including rising cavities communicating with a squealer tip of the blade through standard dust removal holes intended to remove dust and through inclined cooling bores intended to cool a barrier of the squealer tip by leading to a pressure side face of the blade, at least one rising cavity including a tip with no dust removal hole and an inclined cooling bore formed in its lateral wall and intended to cool the squealer tip barrier is enlarged to have a diameter at least equal to the standard diameter of a dust removal hole and thus also serve as a dust removal hole, so that the air flow extracted for cooling the blade is reduced, at least one of the cavities positioned facing the tip of one of the rising cavities having an increased volume corresponding to at least a volume deducted from the tip of the rising cavity.Type: GrantFiled: October 11, 2018Date of Patent: July 19, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Leandre Ostino, Matthieu Simon
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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: 20220170371Abstract: An aircraft turbine engine blade includes at least one inner cavity for circulating a ventilation air flow and having a wall with first projecting elements oriented in a first direction and forming air flow disrupters, and at least a second projecting element oriented in a second direction different from the first direction. The second projecting element and at least one of the first projecting elements overlap each other in one area. At least one of the first projecting elements overlaps the second projecting element and has a height (H2, H4?) which is greater than that of the second projecting element in the area and greater than that of the other first projecting elements of the wall, in order to retain its disruptive function along the entire length thereof.Type: ApplicationFiled: March 11, 2020Publication date: June 2, 2022Applicant: SAFRAN AIRCRAFT ENGINESInventors: Michel SLUSARZ, Pierre Guillaume AUZILLON, Patrice ENEAU, Léandre OSTINO
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Publication number: 20220170377Abstract: A blade for a turbomachine intended to be disposed about an axis while extending radially between a radially outer end and a radially inner end, the blade having at least one cooling cavity opening out to the radially outer end of the blade and to the radially inner end of the blade, the blade having at least a first tubular liner and at least a second tubular liner each engaged in the cavity, the radially outer end of the first liner opening out to the radially outer end of the blade, and the radially inner end of the second liner opening out to the radially inner end of the blade.Type: ApplicationFiled: March 16, 2020Publication date: June 2, 2022Applicant: SAFRAN AIRCRAFT ENGINESInventors: Matthieu SIMON, Jean-Luc BACHA, Paul DANRE, Léandre OSTINO
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Patent number: 11286788Abstract: In order to limit the air flow required to cool its blade member, a blade for an aircraft turbomachine turbine includes, in its blade member, a main passage configured to collect a main air flow from an air inlet and to circulate it in the blade member, and a side passage located between the main passage and the pressure-side wall, while being separated from the main passage, wherein the side passage is configured to collect a side air flow from the air inlet and to circulate it in the blade member, the main passage having at least three portions connected together end-to-end to form a coil, the side passage being located between each of these portions and the pressure-side wall.Type: GrantFiled: May 18, 2018Date of Patent: March 29, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Leandre Ostino, Patrice Eneau, Charlotte Marie Dujol
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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: 11199100Abstract: A turbine blade includes a root and an airfoil extending from a base, through which it is connected to the root, to a tip. The airfoil includes an intrados wall and an extrados wall, connected by a leading edge and by a trailing edge with a cooling circuit. The cooling circuit includes a conduit with a duct and a manifold prolonging this conduit. The conduit collects air from the blade root to supply the duct and the manifold that is located downstream from the duct and that supplies the slits in the trailing edge with air. The duct supplies air to one end of the manifold close to the tip. The manifold is separated from the duct by a partition including a portion close to the tip that is curved to be concave when seen from the trailing edge.Type: GrantFiled: May 15, 2020Date of Patent: December 14, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Léandre Ostino, Vianney Simon, Vincent Keciyan
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Publication number: 20210187594Abstract: A hollow turbomachine turbine blade including rising cavities communicating with a squealer tip of the blade through standard dust removal holes intended to remove dust and through inclined cooling bores intended to cool a barrier of the squealer tip by leading to a pressure side face of the blade, at least one rising cavity including a tip with no dust removal hole and an inclined cooling bore formed in its lateral wall and intended to cool the squealer tip barrier is enlarged to have a diameter at least equal to the standard diameter of a dust removal hole and thus also serve as a dust removal hole, so that the air flow extracted for cooling the blade is reduced, at least one of the cavities positioned facing the tip of one of the rising cavities having an increased volume corresponding to at least a volume deducted from the tip of the rising cavity.Type: ApplicationFiled: October 11, 2018Publication date: June 24, 2021Applicant: SAFRAN AIRCRAFT ENGINESInventors: Leandre OSTINO, Matthieu SIMON
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Patent number: 11035235Abstract: A turbine blade of a turbine engine such as a turbojet engine, comprising: a root supporting a blade and extending in a wingspan direction, ending in a vertex, the blade comprising a leading edge and a trailing edge, with a pressure side wall and a suction side wall separated from one another and connecting the leading edge (17) to the trailing edge, the blade also comprising: cooling ducts in which air collected at the blade root circulates; first and second inner side recesses running along the pressure side wall in order to form a heat shield spaced apart from one another along the pressure side wall; and at least one duct extending from the pressure side wall to the suction side wall between the first and second side recesses.Type: GrantFiled: October 18, 2017Date of Patent: June 15, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Charlotte Marie Dujol, Sébastien Serge Francis Congratel, Patrice Eneau, Léandre Ostino, Michel Slusarz
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Publication number: 20200362705Abstract: A turbine blade includes a root and an airfoil extending from a base, through which it is connected to the root, to a tip. The airfoil includes an intrados wall and an extrados wall, connected by a leading edge and by a trailing edge with a cooling circuit. The cooling circuit includes a conduit with a duct and a manifold prolonging this conduit. The conduit collects air from the blade root to supply the duct and the manifold that is located downstream from the duct and that supplies the slits in the trailing edge with air. The duct supplies air to one end of the manifold close to the tip. The manifold is separated from the duct by a partition including a portion close to the tip that is curved to be concave when seen from the trailing edge.Type: ApplicationFiled: May 15, 2020Publication date: November 19, 2020Inventors: Léandre OSTINO, Vianney SIMON, Vincent KECIYAN
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Publication number: 20200173290Abstract: In order to limit the air flow required to cool its blade member, a blade for an aircraft turbomachine turbine includes, in its blade member, a main passage configured to collect a main air flow from an air inlet and to circulate it in the blade member, and a side passage located between the main passage and the pressure-side wall, while being separated from the main passage, wherein the side passage is configured to collect a side air flow from the air inlet and to circulate it in the blade member, the main passage having at least three portions connected together end-to-end to form a coil, the side passage being located between each of these portions and the pressure-side wall.Type: ApplicationFiled: May 18, 2018Publication date: June 4, 2020Applicant: SAFRAN AIRCRAFT ENGINESInventors: Leandre OSTINO, Patrice ENEAU, Charlotte Marie DUJOL
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Publication number: 20190376394Abstract: A turbine blade of a turbine engine such as a turbojet engine, comprising: a root supporting a blade and extending in a wingspan direction, ending in a vertex, the blade comprising a leading edge and a trailing edge, with a pressure side wall and a suction side wall separated from one another and connecting the leading edge (17) to the trailing edge, the blade also comprising: cooling ducts in which air collected at the blade root circulates; first and second inner side recesses running along the pressure side wall in order to form a heat shield spaced apart from one another along the pressure side wall; and at least one duct extending from the pressure side wall to the suction side wall between the first and second side recesses.Type: ApplicationFiled: October 18, 2017Publication date: December 12, 2019Inventors: Charlotte Marie DUJOL, Sébastien Serge Francis CONGRATEL, Patrice ENEAU, Léandre OSTINO, Michel SLUSARZ