Patents by Inventor Pierre Guillaume Auzillon
Pierre Guillaume Auzillon 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).
-
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
-
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
-
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
-
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
-
Patent number: 10385700Abstract: A turbomachine turbine blade includes a suction face, a pressure face, a leading edge and a trailing edge as well as a squealer at the tip thereof. The squealer tip includes at least one internal rib that extends from a point of attachment of the rim of the squealer on the suction-face side to a point of attachment of the rim of the squealer on the pressure-face side, and includes a portion for absorbing the load of leakage flows which extends from the suction face and a deflector-forming portion which extends the load absorber portion with an inflection and guides the leakage flows toward the pressure face.Type: GrantFiled: August 3, 2015Date of Patent: August 20, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Pierre Guillaume Auzillon, Remi Philippe Oswald Olive, Marjolaine Marie-Anne Pierre
-
Patent number: 9890652Abstract: A rotating assembly for a turbine engine, comprising a disc having an outer periphery having alternating slots and teeth, blades radially extending from the disc and roots of which are axially engaged in the slots, with spaces called slot cavities being provided between the roots of the blades and the slots, platforms laterally extending from the blades and circumferentially arranged end-to-end, so as to form spaces called inter-blade cavities, and a downstream annular shroud, comprising an outer annular sealing lip opposite the downstream ends of the platforms. The downstream shroud further comprises an intermediate annular sealing lip opposite the downstream faces of the teeth of the disc, radially between the slot cavities and the inter-blade cavities.Type: GrantFiled: September 29, 2015Date of Patent: February 13, 2018Assignee: SNECMAInventors: Maurice Guy Judet, Pierre Guillaume Auzillon, Matthieu Simon
-
Publication number: 20170226871Abstract: A turbomachine turbine blade includes a suction face, a pressure face, a leading edge and a trailing edge as well as a squealer at the tip thereof. The squealer tip includes at least one internal rib that extends from a point of attachment of the rim of the squealer on the suction-face side to a point of attachment of the rim of the squealer on the pressure-face side, and includes a portion for absorbing the load of leakage flows which extends from the suction face and a deflector-forming portion which extends the load absorber portion with an inflection and guides the leakage flows toward the pressure face.Type: ApplicationFiled: August 3, 2015Publication date: August 10, 2017Applicant: Safran Aircraft EnginesInventors: Pierre Guillaume AUZILLON, Remi Philippe Oswald OLIVE, Marjolaine Marie-Anne PIERRE
-
Publication number: 20160090855Abstract: A rotating assembly for a turbine engine, comprising a disc having an outer periphery having alternating slots and teeth, blades radially extending from the disc and roots of which are axially engaged in the slots, with spaces called slot cavities being provided between the roots of the blades and the slots, platforms laterally extending from the blades and circumferentially arranged end-to-end, so as to form spaces called inter-blade cavities, and a downstream annular shroud, comprising an outer annular sealing lip opposite the downstream ends of the platforms. The downstream shroud further comprises an intermediate annular sealing lip opposite the downstream faces of the teeth of the disc, radially between the slot cavities and the inter-blade cavities.Type: ApplicationFiled: September 29, 2015Publication date: March 31, 2016Applicant: SnecmaInventors: Maurice Guy Judet, Pierre Guillaume Auzillon, Matthieu Simon