Patents by Inventor Alexandre Branco

Alexandre Branco 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: 12366173
    Abstract: A fan casing for an aircraft turbomachine includes an annular body extending around an axis and equipped with an annular attachment flange at each of its axial ends. The casing further includes an annular coating made from abradable material, wherein the body is made from a composite material, and further includes an annular stiffener that is arranged inside the body and that carries the coating. The stiffener includes an annular ring, a radially outer face of which is separated radially from the body and a radially inner face of which receives the coating. The stiffener further includes annular attachment tabs configured to the wall to the body.
    Type: Grant
    Filed: January 30, 2020
    Date of Patent: July 22, 2025
    Assignee: SAFRAN
    Inventors: Clément Bourolleau, Vincent Pascal Fiore, Anwer Siraj, Alexandre Branco, Serge Domingues
  • Publication number: 20250122813
    Abstract: A method for producing casing for an aircraft turbine engine includes a first step of manufacturing an annular shell having an axis A made of a composite material in a mold that includes an annular cavity that receives the preform. A resin is injected into the cavity and subsequently polymerized. During a second step, at least one axial abutment means is arranged inside the shell, and during a third step, the annular cartridge made of an abradable material is arranged inside the annular shell in contact with the axial abutment means. A fourth step includes bonding the annular cartridge to the first inner annular surface. The first and second steps are simultaneous, and the at least one axial abutment means is molded with the preform in the mold.
    Type: Application
    Filed: September 14, 2022
    Publication date: April 17, 2025
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Vincent Pascal FIORE, Clément BOUROLLEAU, Alexandre BRANCO, Serge Emmanuel DOMINGUES
  • Patent number: 12270348
    Abstract: Discharge valve of an aircraft turbomachine, including a discharge gate intended to be mounted pivotably about an axis between a position for closing an air passage orifice and an open position of said orifice, the orifice being formed in an intermediate casing of the turbomachine, the discharge valve including a sealing device having a seal configured to be movably mounted on the intermediate casing and a movement system configured to move the seal between a first position in which the seal is intended to bear against the discharge gate when the gate is in a closure position, and a second position in which the seal is retracted with respect to the air passage orifice when the discharge gate is in an open position.
    Type: Grant
    Filed: January 21, 2022
    Date of Patent: April 8, 2025
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Azath Mohamed, Alexandre Branco, Thierry Georges Paul Papin, Virginie Martine Collin
  • Publication number: 20240295177
    Abstract: A housing for an aircraft turbomachine, including an annular casing extending around an axis A and having an internal annular surface, the housing also including an annular abradable support cartridge that is fixed against the internal annular surface, the abradable support cartridge has a reinforced coating including a fibrous texture reinforcement embedded in a resin matrix, the fibrous texture reinforcement including a stack of fibrous texture plies, wherein the stack of plies includes at least one ply made of Kevlar® or of glass fibres.
    Type: Application
    Filed: June 29, 2021
    Publication date: September 5, 2024
    Inventors: Clement BOUROLLEAU, Clementine ARNOLD, Alexandre BRANCO, Serge DOMINGUES, Thomas DUPAYS, Vincent Pascal FIORE, Baptiste LEBLON, Anwer SIRAJ
  • Publication number: 20240102422
    Abstract: Discharge valve of an aircraft turbomachine, including a discharge gate intended to be mounted pivotably about an axis between a position for closing an air passage orifice and an open position of said orifice, the orifice being formed in an intermediate casing of the turbomachine, the discharge valve including a sealing device having a seal configured to be movably mounted on the intermediate casing and a movement system configured to move the seal between a first position in which the seal is intended to bear against the discharge gate when the gate is in a closure position, and a second position in which the seal is retracted with respect to the air passage orifice when the discharge gate is in an open position.
    Type: Application
    Filed: January 21, 2022
    Publication date: March 28, 2024
    Inventors: Azath MOHAMED, Alexandre BRANCO, Thierry Georges Paul PAPIN, Virginie Martine COLLIN
  • Patent number: 11753957
    Abstract: A method for detecting at least one roughness in a face of an abradable layer in a fan casing is provided. The method includes a step of depositing on the abradable layer a first coating and a second coating covering the first coating. The first and second coatings have respective thicknesses (N1, N2) and a physical appearance that differ from one another. Local appearance of the first coating is indicative of a need for a localized touch-up, and local disappearance of the first coating and the second coating is indicative of a need for a localized replacement of the abradable layer.
    Type: Grant
    Filed: April 10, 2020
    Date of Patent: September 12, 2023
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Clément Bourolleau, Alexandre Branco, Serge Domingues, Vincent Fiore, Anwer Siraj
  • Patent number: 11702961
    Abstract: A gas turbine fan casing made of composite material with a fibrous reinforcement includes a plurality of superimposed turns of a strip-shaped fibrous texture having a three-dimensional weaving between a plurality of layers of warp yarns and a plurality of layers of weft yarns, the fibrous reinforcement being densified by a matrix. The fibrous texture includes at least one lateral section of variable thickness in which the weft yarns have a size or a count different from the size or the count of the weft yarns of the plurality of layers of weft yarns present in the remainder of the fibrous texture.
    Type: Grant
    Filed: January 17, 2020
    Date of Patent: July 18, 2023
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Clément Bourolleau, Alexandre Branco, Serge Domingues, Vincent Pascal Fiore, Anwer Siraj
  • Patent number: 11613378
    Abstract: A cockpit suitable for being installed in a pilot's cabin of an aircraft, the cockpit comprising a floor, a plurality of interior furniture items and a dashboard configured to receive a plurality of devices for commanding and/or controlling the aircraft, the cockpit comprising a securing system which connects the dashboard solely to the floor and/or to the plurality of interior furniture items.
    Type: Grant
    Filed: December 3, 2019
    Date of Patent: March 28, 2023
    Assignee: AIRBUS ATLANTIC
    Inventors: Christian Bergeret, Gilles Andrieu, Alexandre Branco
  • Patent number: 11577854
    Abstract: Disclosed is an instrument panel designed to be integrated into an aircraft cockpit, the instrument panel comprising a main structure, extending longitudinally and having a concave shape defining a cavity, this cavity being configured to receive a plurality of navigation command and/or control units, and at least one inner wall, configured to delimit at least two recesses each intended to receive at least one of the plurality of navigation command and/or control units, the instrument panel being characterized in that the main structure is made from a single piece made from a composite material.
    Type: Grant
    Filed: December 3, 2019
    Date of Patent: February 14, 2023
    Assignee: STELIA AEROSPACE
    Inventors: Christian Bergeret, Gilles Andrieu, Alexandre Branco
  • Publication number: 20220195881
    Abstract: A method for detecting at least one roughness in a face of an abradable layer in a fan casing is provided. The method includes a step of depositing on the abradable layer a first coating and a second coating covering the first coating. The first and second coatings have respective thicknesses (N1, N2) and a physical appearance that differ from one another. Local appearance of the first coating is indicative of a need for a localized touch-up, and local disappearance of the first coating and the second coating is indicative of a need for a localized replacement of the abradable layer.
    Type: Application
    Filed: April 10, 2020
    Publication date: June 23, 2022
    Inventors: Clément Bourolleau, Alexandre Branco, Serge Domingues, Vincent Fiore, Anwer Siraj
  • Publication number: 20220120196
    Abstract: A gas turbine fan casing made of composite material with a fibrous reinforcement includes a plurality of superimposed turns of a strip-shaped fibrous texture having a three-dimensional weaving between a plurality of layers of warp yarns and a plurality of layers of weft yarns, the fibrous reinforcement being densified by a matrix. The fibrous texture includes at least one lateral section of variable thickness in which the weft yarns have a size or a count different from the size or the count of the weft yarns of the plurality of layers of weft yarns present in the remainder of the fibrous texture.
    Type: Application
    Filed: January 17, 2020
    Publication date: April 21, 2022
    Inventors: Clément BOUROLLEAU, Alexandre BRANCO, Serge DOMINGUES, Vincent Pascal FIORE, Anwer SIRAJ
  • Publication number: 20220099108
    Abstract: A fan casing for an aircraft turbomachine includes an annular body extending around an axis and equipped with an annular attachment flange at each of its axial ends. The casing further includes an annular coating made from abradable material, wherein the body is made from a composite material, and further includes an annular stiffener that is arranged inside the body and that carries the coating. The stiffener includes an annular ring, a radially outer face of which is separated radially from the body and a radially inner face of which receives the coating. The stiffener further includes annular attachment tabs configured to the wall to the body.
    Type: Application
    Filed: January 30, 2020
    Publication date: March 31, 2022
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Clément BOUROLLEAU, Vincent Pascal FIORE, Anwer SIRAJ, Alexandre BRANCO, Serge DOMINGUES
  • Publication number: 20220048641
    Abstract: A cockpit suitable for being installed in a pilot's cabin of an aircraft, the cockpit comprising a floor, a plurality of interior furniture items and a dashboard configured to receive a plurality of devices for commanding and/or controlling the aircraft, the cockpit comprising a securing system which connects the dashboard solely to the floor and/or to the plurality of interior furniture items.
    Type: Application
    Filed: December 3, 2019
    Publication date: February 17, 2022
    Applicant: STELIA AEROSPACE
    Inventors: Christian Bergeret, Gilles Andrieu, Alexandre Branco
  • Publication number: 20220017233
    Abstract: Disclosed is an instrument panel designed to be integrated into an aircraft cockpit, the instrument panel comprising a main structure, extending longitudinally and having a concave shape defining a cavity, this cavity being configured to receive a plurality of navigation command and/or control units, and at least one inner wall, configured to delimit at least two recesses each intended to receive at least one of the plurality of navigation command and/or control units, the instrument panel being characterized in that the main structure is made from a single piece made from a composite material.
    Type: Application
    Filed: December 3, 2019
    Publication date: January 20, 2022
    Applicant: STELIA AEROSPACE
    Inventors: Christian Bergeret, Gilles Andrieu, Alexandre Branco
  • Patent number: 10982560
    Abstract: The invention relates to a blade (16), in particular a fan blade, for resurfacing an abradable coating (26) on an internal surface of a turbine engine case (18) intended to surround the blade. The comprises a root (20) and an airfoil (24) having a tip opposite the root, said root comprising a housing (32) for the storage or passage of a polymerisable refill resin. The airfoil comprises longitudinal channels (34), the first ends of said channels being connected to the housing and the opposite ends opening at the aforementioned tip.
    Type: Grant
    Filed: April 10, 2017
    Date of Patent: April 20, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Michael Isemene, Alexandre Branco
  • Publication number: 20190120074
    Abstract: The invention relates to a blade (16), in particular a fan blade, for resurfacing an abradable coating (26) on an internal surface of a turbine engine case (18) intended to surround the blade. The comprises a root (20) and an airfoil (24) having a tip opposite the root, said root comprising a housing (32) for the storage or passage of a polymerisable refill resin. The airfoil comprises longitudinal channels (34), the first ends of said channels being connected to the housing and the opposite ends opening at the aforementioned tip.
    Type: Application
    Filed: April 10, 2017
    Publication date: April 25, 2019
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Michael Isemene, Alexandre Branco
  • Patent number: 8959895
    Abstract: An exhaust-gas aftertreatment device is provided, comprising a control unit for controlling a diaphragm pump that draws a urea/water solution out of a circuit and pumps it, via a pressure filter, to a metering unit comprising an atomizing nozzle for atomizing the urea/water solution into an exhaust-gas stream. The metering unit may also comprise a metering valve, including an atomizing nozzle, a pressure and temperature sensor, a heating means and a return baffle.
    Type: Grant
    Filed: March 27, 2012
    Date of Patent: February 24, 2015
    Assignee: Cummins Ltd.
    Inventors: Friedrich Zapf, Heico Stegmann, Andreas Lannig, Klaus Lang, Christian Schmidt, Alexandre Branco
  • Patent number: 8938949
    Abstract: The invention relates to an SCR exhaust gas aftertreatment device, particularly for diesel motor internal combustion engines having a very large exhaust gas volume and/or divided exhaust gas trains. In order to be able to manufacture this SCR exhaust gas aftertreatment device in a cost-efficient manner, also for a high mixing degree of exhaust gas and AUS, it is proposed that a plurality of metering units (D1, D2, Dn) is provided, each of which has an atomizing nozzle, which nozzle-injects the aqueous urea solution into the exhaust gas train. In this case, the pressure existing in a common line for all metering units (D1, D2, Dn) can be determined by means of a pressure sensor.
    Type: Grant
    Filed: July 30, 2010
    Date of Patent: January 27, 2015
    Assignee: Cummins Ltd.
    Inventors: Alexandre Branco, Heico Stegmann, Friedrich Zapf
  • Publication number: 20140111205
    Abstract: The device for holding and adjusting individual permanent magnets included in a spectroscopy or a magnetic resonant imaging system comprises, for each individual permanent magnet: a first rigid fork of non-magnetic material that laterally clamps in fixed manner the individual permanent magnet; and a second rigid fork of non-magnetic material that engages the first fork via a slideway system and that is provided with means for radially adjusting the first fork relative to a stationary support to which the second fork is attached. The device enables fine adjustment to be made after assembling a magnetized structure that is constituted by rings of individual magnets.
    Type: Application
    Filed: October 22, 2013
    Publication date: April 24, 2014
    Applicant: Commissariat A L'Energie Atomique Et Aux Energies Alternatives
    Inventors: Sandrine Cazaux, Alexandre Branco
  • Publication number: 20120180460
    Abstract: An exhaust-gas aftertreatment device is provided, comprising a control unit for controlling a diaphragm pump that draws a urea/water solution out of a circuit and pumps it, via a pressure filter, to a metering unit comprising an atomizing nozzle for atomizing the urea/water solution into an exhaust-gas stream. The metering unit may also comprise a metering valve, including an atomizing nozzle, a pressure and temperature sensor, a heating means and a return baffle.
    Type: Application
    Filed: March 27, 2012
    Publication date: July 19, 2012
    Applicant: Hilite Germany GmbH
    Inventors: Friedrich Zapf, Heico Stegmann, Andreas Lannig, Klaus Lang, Christian Schmidt, Alexandre Branco