Beaujard
Antoine Beaujard, Vaux-Le-Penil FR
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20140314556 | Method of Fabricating a Turbine or Compressor Guide Vane Sector Made of Composite Material for a Turbine Engine, and a Turbine or a Compressor Incorporating Such Guide Vane Sectors - Single-airfoil vanes each having an inner platform, an outer platform, and an airfoil are obtained by three-dimensionally weaving a fiber blank in a single piece, by shaping the fiber blank to obtain a single-piece fiber preform, and by densifying the preform with a matrix to obtain a vane of composite material forming a single piece with inner and outer platforms incorporated therein. A plurality of vanes is assembled together at an intermediate stage of densification to form a multi-airfoil composite material guide vane sector for a turbine nozzle or a compressor diffuser and the assembled-together vanes are bonded together. | 10-23-2014 |
20140356151 | HOLLOW-BLADE TURBINE VANE MADE FROM COMPOSITE MATERIAL, TURBINE OR COMPRESSOR INCLUDING A NOZZLE OR GUIDE VANE ASSEMBLY FORMED BY SUCH BLADES, AND TURBOMACHINE COMPRISING SAME - A turbine engine vane is made of composite material comprises a hollow airfoil with an internal passage extending along its entire length, an inner platform, and an outer platform. The airfoil is extended on the outside of the outer platform by an upstream attachment portion and a downstream attachment portion for mounting the vane in a casing. The attachment portions are formed by an attachment extending from the outer longitudinal ends of the pressure side wall and the suction side wall of the airfoil with continuity of the fiber reinforcing texture of the composite material between the walls and the attachment tabs. | 12-04-2014 |
Antoine Jean-Philippe Beaujard, Moissy-Cramayel Cedex FR
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20150226084 | METHOD OF FABRICATING A COMPOSITE MATERIAL CASING FOR A GAS TURBINE ENGINE, AND A CASING OBTAINED THEREBY - A method of fabricating a composite material casing for a gas turbine engine, the method including making an outer shroud including a platform and a flange, making an inner shroud of smaller diameter than the outer shroud and including a platform and a flange, making a plurality of casing arms, each including a blade that is terminated at each radial end by a respective platform, arranging a plurality of openings in the respective platforms of the shrouds, each opening serving to receive a platform of a casing arm, and assembling the casing arms with the outer shroud and with the inner shroud by inserting the platforms of the casing arms in the openings of the shrouds. A composite material casing is obtained by such a method. | 08-13-2015 |
Antoine Jean-Philippe Beaujard, Vaux Le Penil FR
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20120251309 | CMC TURBINE NOZZLE ADAPTED TO SUPPORT A METALLIC TURBINE INTERNAL CASING BY AN AXIAL CONTACT - Composite material turbine nozzle blade including an airfoil ( | 10-04-2012 |
20120251314 | CMC TURBINE NOZZLE ADAPTED TO SUPPORT A METALLIC TURBINE INTERNAL CASING BY A RADIAL CONTACT - Composite material turbine nozzle blade including an airfoil ( | 10-04-2012 |
20130136605 | DEVICE FOR LOCKING A ROOT OF A ROTOR BLADE - A device for locking a root of a rotor blade in a groove in a rotor disk of a turbomachine including: a circular ring sector configured to be mounted, transversely to the axis of the turbomachine, in a groove in the rotor disk; at least one locking wedge, which is rigidly secured and perpendicular to the ring sector, and extends parallel to the axis of the ring sector so as to hold the root of the blade radially in the groove; and at least one locking tooth extending from the ring sector radially with respect to the axis of the ring sector, so as to prevent the root of the blade from moving axially in the groove. | 05-30-2013 |
20140234118 | TURBINE ENGINE COMPRISING A METAL PROTECTION FOR A COMPOSITE PART - A gas turbine engine including at least a first composite part configured for mounting in a second metal part of the engine, the first composite part including an interface surface configured to be in surface contact with the second metal part, the engine including a metal protection removably mounted on the first composite part and configured to cover the interface surface. | 08-21-2014 |
Antoine Jean-Philippe Beaujard, Moissy-Cramayel FR
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20130101429 | TURBOMACHINE BLADE OR VANE HAVING COMPLEMENTARY ASYMMETRICAL GEOMETRY - A turbomachine blade is made of composite material. The blade includes a first portion constituting at least an airfoil exhibiting two faces each connecting a leading edge to a trailing edge, the first portion forming a single part with at least one second portion present only on one of the faces of the airfoil. The second portion constitutes a portion of at least one of the following elements: a flowpath delimiting outer portion of an inner platform, an inner portion of an inner platform, a flowpath delimiting inner portion of an outer platform, and an outer portion of an outer platform. Portions of fiber reinforcements corresponding to the first and the second portions of the blade are at least partially mutually imbricated. Yarns of the first portion of the fiber reinforcement penetrate into the second portion of the fiber reinforcement. | 04-25-2013 |
20130108422 | COMPOSITE MATERIAL TURBOMACHINE ENGINE BLADE OR VANE, COMPRESSOR STATOR SEGMENT OR TURBINE NOZZLE SEGMENT INCORPORATING SUCH VANES AND METHOD FOR MANUFACTURING SAME | 05-02-2013 |
20130243604 | TURBOMACHINE BLADES OR VANES HAVING COMPLEMENTARY EVEN/ODD GEOMETRY - A turbomachine blade made of composite material including a fiber reinforcement obtained by three-dimensional weaving of yarns and densified by a matrix, comprises a first portion constituting an airfoil and a blade root. The first portion constitutes a single part with at least one second portion constituting a blade inner platform, said blade then lacking a blade anti-tilting wall, or a blade anti-tilting wall, said blade then lacking a blade inner platform. The first portion also constitutes a single part with at least one third portion constituting a blade outer platform spoiler plate, said blade then lacking a blade outer platform wiper plate, or a blade outer platform wiper plate, said blade then lacking a blade outer platform spoiler plate. | 09-19-2013 |
20140030076 | TURBINE ENGINE BLADE OR VANE MADE OF COMPOSITE MATERIAL, TURBINE NOZZLE OR COMPRESSOR STATOR INCORPORATING SUCH VANES AND METHOD OF FABRICATING SAME - A method for fabricating turbine engine blade or vane made of composite material includes: performing three-dimensional weaving to make a single-piece fiber blank; shaping the fiber blank to obtain a single-piece fiber preform having a first portion forming a preform for at least a blade/vane airfoil, at least one second portion forming a preform for an inner part of a blade/vane inner platform or for an outer part of a blade/vane outer platform, and at least one third portion forming a preform for an outer part of a blade/vane inner platform or for an inner part of a blade/vane outer platform; and densifying the fiber preform with a matrix to obtain a composite material blade, and forming a single piece with an inner and/or outer platform(s) incorporated therein. | 01-30-2014 |
Antoine Jean-Philippe Beaujard, Melun FR
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20140147264 | TURBINE ENGINE STATOR WHEEL AND A TURBINE OR A COMPRESSOR INCLUDING SUCH A STATOR WHEEL - A turbine nozzle comprises a plurality of composite material vanes, each vane comprising an inner platform, an outer platform with attachment tabs on the outside, and at least one airfoil extending between the inner and outer platforms and secured thereto. The attachment tabs of the vanes are engaged on a metal assembly ring supporting all of the vanes, extending continuously along the outer platforms of adjacent vanes, and forming a distinct assembly part between the vanes and a turbine casing. | 05-29-2014 |
20150047370 | METHOD FOR HOLDING AN ADAPTER PIECE ON A TUBULAR HOUSING OF A TURBO ENGINE, AND CORRESPONDING ADAPTER PIECE AND HOLDING SYSTEM - An adapting part is designed to be held on a casing of a turbo-engine, partially covering the casing. The adapting part includes, in the extension of one of its axial ends, a first connector to engage with a first complementary connector associated with the casing to form a sliding connection. The adapting part also includes, at its other axial end, a second connector to be secured to a second complementary connector associated with the casing to form a rigid connection. | 02-19-2015 |
Flonrence Beaujard, Plaisance Du Touch FR
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20100026524 | PROCESS AND APPARATUS FOR AIDING IN THE CONCEPTION OF TEXTS FOR A PILOT OR A CONDUCTOR - The method for aiding in the design of a text to be displayed to a user is provided with: | 02-04-2010 |
Jean-Philippe Beaujard, Plaisance Du Touch FR
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20150134194 | SYSTEM AND METHOD FOR FAULT DIAGNOSIS OF AIRCRAFT - An aircraft failure diagnostic method and system includes a group of at least one smart mobile device, mobile in relation to the on-board equipment of an aircraft. The smart mobile device transmits a request for measurement data to an on-board equipment, following a tree structure of measurement data to be acquired. A piece of measurement data received from the on-board equipment by a smart mobile device causes passage to a later step in the tree structure of measurement data requests or interactive maintenance document. The interactive maintenance document is generated by automatically extracting inferences, data to be measured, measurements achievable on the on-board equipment, and measurements requiring a tool not included in the on-board equipment from an aircraft technical documentation. | 05-14-2015 |
Karen Beaujard, Metz FR
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20110018178 | METHOD AND DEVICE FOR BLOWING GAS ON A RUNNING STRIP - The present invention relates to a method for acting on the temperature of a travelling strip ( | 01-27-2011 |
20140047729 | METHOD AND DEVICE FOR BLOWING GAS ON A RUNNING STRIP - The present invention relates to a method for acting on the temperature of a travelling strip ( | 02-20-2014 |
Olivier Beaujard, Paris FR
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20090312006 | CUSTOMISATION OF A RADIO COMMUNICATION TERMINAL - A method is provided for definitive customization or customization for a predetermined duration related to a subscription of a radio communication terminal possessing an operating mode requiring the association with the terminal of a customization data set specific to a radio communication network, so as to allow the terminal to be linked with the radio communication network. The method includes the following steps: obtaining carrier information pertaining to carriers received by the terminal; and selecting a customization data set for the terminal, from a plurality of customization data sets, as a function of a selection criterion applied to the carrier information obtained. | 12-17-2009 |