Patents Assigned to SAFRAN
  • METHOD FOR COMPRESSING A SEQUENCE OF IMAGES DISPLAYING SYNTHETIC GRAPHICAL ELEMENTS OF NON-PHOTOGRAPHIC ORIGIN
    Publication number: 20230047115
    Abstract: Method for compressing a sequence of images comprising a first image and a second image, the method comprising the steps of: generating a first descriptor comprising parameters for displaying a computer-generated graphical element in the first image, the graphical element being of non-photographic origin, and the display parameters not comprising pixel values; processing the second image so as to determine an event which gave rise to a potential variation in the parameters for displaying the graphical element between the first image and the second image; generating a second descriptor comprising an event code indicating the determined event.
    Type: Application
    Filed: December 10, 2020
    Publication date: February 16, 2023
    Applicants: SAFRAN DATA SYSTEMS, INSTITUT MINES-TELECOM
    Inventors: Marco CAGNAZZO, Attilio FIANDROTTI, Christophe RUELLAN
  • ASSEMBLY FOR A TURBINE ENGINE
    Publication number: 20230047952
    Abstract: An assembly for a turbomachine extending along an axis includes a combustion chamber having, at its downstream end, a downstream flange having a radially extending part. The assembly further includes a distributor disposed downstream of the combustion chamber and having a platform from which at least one vane extends radially. The platform includes an upstream flange extending radially and delimiting, with the radial part of the downstream flange disposed opposite it. An annular space for the circulation of cooling air opens into the combustion chamber at its radially internal end and has, at its radially external end, means of sealing attached to the distributor.
    Type: Application
    Filed: January 20, 2021
    Publication date: February 16, 2023
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Paul Olivier DANRE, Jean-Luc BACHA, Julie Laure Antoinette BUREL, Julien Michel TAMIZIER, Christophe Bernard TEXIER
  • METHOD FOR GENERATING A TRAINING SEQUENCE CONSISTING OF A PLURALITY OF OFDM SYMBOLS
    Publication number: 20230046353
    Abstract: Method for generating an OFDM training sequence, device and computer program product. The OFDM training sequence consists of at least two OFDM symbols, and the OFDM training sequence comprises at least two OFDM sub-carriers, the method comprising a step of partitioning the OFDM sub-carriers into at least two separate groups comprising at least one sub-carrier, a number of groups being smaller than a number of sub-carriers. The method comprises steps, carried out independently for each group, of generating an elementary sequence associated with a group by combining the sub-carriers of the group, the elementary sequence having a duration equal to a duration of one of the at least two symbols.
    Type: Application
    Filed: December 24, 2020
    Publication date: February 16, 2023
    Applicant: SAFRAN DATA SYSTEMS
    Inventor: Guillaume DUPONCHEL
  • TURBOMACHINE STATOR ASSEMBLY COMPRISING AN INNER SHROUD HAVING UPSTREAM AND DOWNSTREAM PORTIONS ASSEMBLED BY AXIAL TRANSLATION
    Publication number: 20230051167
    Abstract: A stator wheel for a turbomachine turbine. This wheel includes an inner shroud formed by an upstream portion and a downstream portion configured to be assembled with the blades by axial translation in a respective direction.
    Type: Application
    Filed: January 14, 2021
    Publication date: February 16, 2023
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Aurelien GAILLARD, Sebastien Serge Francis CONGRATEL, Clement JARROSSAY, Pascal Cedric TABARIN, Nicolas Paul TABLEAU
  • SPLINED SHAFT
    Publication number: 20230051474
    Abstract: A splined shaft includes splines evenly distributed over the periphery, wherein the splines being spaced apart from each other. At least one portion of the splines are spaced apart by a modified pitch p with respect to the nominal pitch pn of the splines. The ratio of the absolute value of the difference between the modified pitch and the nominal pitch, to the nominal pitch, i.e. |pn?p|/pn, is different from zero, for example between 0.5 and 5%.
    Type: Application
    Filed: August 10, 2022
    Publication date: February 16, 2023
    Applicant: SAFRAN TRANSMISSION SYSTEMS
    Inventors: Juan-Luis MARCOS IZQUIERDO, Quentin Pierre Henri PIGOTT
  • DOOR THRUST REVERSER COMPRISING A DEFLECTOR FOR REDIRECTING AN AIR FLOW IN THE UPSTREAM DIRECTION
    Publication number: 20230046876
    Abstract: A thrust reverser including a stationary structure, a lower door and an upper door. This reverser includes at least one deflector configured to be able to redirect forward from the stationary structure a portion of fluid exiting the reverser according to a trajectory oriented towards a lateral opening extending between the stationary structure and the upper door. Such a deflector makes it possible to improve the control of the air current lines acting on a tail unit and in particular on a control surface of an aircraft equipped with such a reverser when the latter is in thrust reversal configuration, thereby making it possible to improve the controllability of this aircraft.
    Type: Application
    Filed: December 18, 2020
    Publication date: February 16, 2023
    Applicant: SAFRAN NACELLES
    Inventors: Sebastien Laurent Marie PASCAL, Laurent Georges VALLEROY, Paul FERREY
  • ACTUATOR WITH OFFSET SUPPLY PORT
    Publication number: 20230045934
    Abstract: An actuator includes a body and at least a first offset connection port that is connected to the body by a first duct projecting from the body. The first connection port is mechanically connected to the body at least by first and second struts. The first strut and the second strut extend from the first connection port, respectively, to a first segment of the body and to a second segment of the body that is axially spaced apart from the first segment. An undercarriage includes such an actuator as its locking or unlocking actuator.
    Type: Application
    Filed: January 20, 2021
    Publication date: February 16, 2023
    Applicant: SAFRAN LANDING SYSTEMS
    Inventors: Yves COURTOIS DE LOURMEL, Sébastien MESSE, Jean-Baptiste KAMIS, Arnaud LE BRETON, Nicolas NGUYEN
  • IMPROVED DEVICE FOR DETECTING COOLING ABNORMALITIES FOR AN AIRCRAFT TURBINE ENGINE
    Publication number: 20230052526
    Abstract: A turbine rotor for aircraft turbine engine includes a mobile disc supporting mobile blades, the mobile disc including a plurality of slots into which are inserted the roots of the mobile blades a passage being formed between the bottom of the slots and the roots of the mobile blades inserted into the slots. The rotor also includes a circulation channel configured to allow circulation of fluid, the circulation channel including the passage, and a calibration device configured to allow the flow of a first fluid flow rate in the circulation channel when the temperature within the channel is less than a predetermined temperature threshold value, and to change state so as to allow the flow of a second fluid flow rate, greater than the first flow rate, in the channel, when the temperature within the channel is greater than or equal to said predetermined threshold value.
    Type: Application
    Filed: January 15, 2021
    Publication date: February 16, 2023
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Eddy Stephane Joel FONTANEL, Matthieu Etienne ATTALI, Gerrard Philippe GAUTHIER, Wilfried Lionel SCHWEBLEN
  • HOT ISOSTATIC PRESSING HEAT TREATMENT OF BARS MADE FROM TITANIUM ALUMINIDE ALLOY FOR LOW-PRESSURE TURBINE BLADES FOR A TURBOMACHINE
    Publication number: 20230046116
    Abstract: Disclosed is a method for the heat treatment of at least one bar made from titanium aluminide alloy for manufacturing at least one low-pressure turbine blade for a turbomachine, comprising hot isostatic pressing of the bar, characterised in that the hot isostatic pressing (121) is followed, after a temperature transition phase, by a step of heat treatment (122) of the bar at a temperature in the immediate vicinity of the eutectoid temperature of the alloy, the temperature being suitable for the formation of an alloy microstructure with a volume fraction of at least 90% single-phase grains ? and a volume fraction of at most 10% of lamellar grains ?+?, the step being followed by a controlled cooling step (123).
    Type: Application
    Filed: January 29, 2021
    Publication date: February 16, 2023
    Applicant: Safran Aircraft Engines
    Inventors: Damien PONSEN, Guillaume Paul MARTIN, Volker GÜTHER
  • Printed circuit board incorporating a current divider bridge
    Patent number: 11579173
    Abstract: A printed circuit includes a first track, a second track, and at least one insulating layer extending between the first track and the second track. The printed circuit further includes a first through assembly of at least one first plated through hole and a second through assembly of at least one second plated through hole. Each first plated through hole and each second plated through hole connect together the first track and the second track by extending through the insulating layer. The first through assembly and the second through assembly respectively form a first branch and a second branch of a current divider bridge.
    Type: Grant
    Filed: June 26, 2019
    Date of Patent: February 14, 2023
    Assignee: SAFRAN ELECTRONICS & DEFENSE
    Inventors: Patrice Chetanneau, François Guillot
  • Oil collector for a mechanical reduction gear of an aircraft turbomachine
    Patent number: 11578664
    Abstract: An oil collector for a mechanical reduction gear of a turbomachine, in particular for an aircraft, the reduction gear including a body having two opposite lateral faces configured to extend in part around planet gears of the reduction gear, the collector further including an internal oil circulation cavity connected firstly to oil inlets located on the faces, and on the other hand to at least one oil outlet, characterised in that at least one of the faces comprises includes columns and rows of several inlets each having a recess with a progressively increasing cross-section, each recess being delimited by walls, at least some of the walls having a hydrodynamic profile.
    Type: Grant
    Filed: July 14, 2020
    Date of Patent: February 14, 2023
    Assignee: SAFRAN TRANSMISSION SYSTEMS
    Inventors: Mathieu Jean Charrier, Boris Pierre Marcel Morelli, Jean-Pierre Serey
  • Inductive power transmission in aircraft seats
    Patent number: 11577636
    Abstract: Described are aircraft passenger seat assemblies with a passenger seat, a component with an outer surface attached the passenger seat. An inductive wireless power unit with a coil assembly is included with the aircraft passenger seat assembly, and the coil assembly is positioned within the component. A portion of the outer surface of the component covers the coil assembly. Wires connecting the coil assembly to a power supply are hidden from view within the aircraft passenger seat assembly.
    Type: Grant
    Filed: June 21, 2019
    Date of Patent: February 14, 2023
    Assignee: Safran Seats USA LLC
    Inventors: Mark E. Noske, C. Michael Parker
  • Method for assembling a beam and a structural element of an airplane seat
    Patent number: 11578744
    Abstract: The present invention essentially relates to a method for assembling a beam and a structural element of an aircraft seat, characterised in that it comprises: a step of producing at least one recess in an inner face of a beam passage area of the structural element, a step of inserting the beam into the beam passage area, and a step of deforming the beam such that a deformed portion of the beam penetrates into the recess of the beam passage area.
    Type: Grant
    Filed: November 18, 2019
    Date of Patent: February 14, 2023
    Assignee: Safran Seats
    Inventors: Florent Yvon, Jérémy Cailleteau
  • Control device and method of sectors for the assembly of the turbine stators of a turbine
    Patent number: 11580633
    Abstract: A control device controls sectors for the assembly of turbine stators of a turbine. Each turbine stator is formed of an assembly of sectors juxtaposed to one another, and each sector has a reference. The control device includes an automated system for identifying the sector with means for reading the sector reference, a database of the references of the sectors that form the turbine stators of the turbine, and means for associating the read reference of the sector with a determined turbine stator of the turbine.
    Type: Grant
    Filed: November 4, 2021
    Date of Patent: February 14, 2023
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Enguerrand Frédéric De Agostini, Carlos Alves De Matos, Florian Chauvel, Baptiste Eparvier, Mathias Gagliardo, Abner Wysidi
  • Process for depositing a coating on short fibres by calefaction
    Patent number: 11578003
    Abstract: A process for depositing a coating on short fibres of carbon or silicon carbide from a coating precursor, the short fibres having a length of between 50 ?m and 5 mm, the process including at least heating the short fibres by placing a mixture including the fibres and a liquid phase of the coating precursor in a microwave field so as to bring the surface of the fibres to a temperature allowing the coating on the fibres from the coating precursor to be formed by calefaction.
    Type: Grant
    Filed: December 18, 2018
    Date of Patent: February 14, 2023
    Assignees: SAFRAN CERAMICS, CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE, UNIVERSITE DE BORDEAUX
    Inventors: Arnaud Delehouze, Fanny Petibon
  • NACELLE AIR OUTLET FOR AIRCRAFT TURBOJET ENGINE COMPRISING A STRAIGHTENING DEVICE FOR FACILITATING A REVERSE THRUST PHASE
    Publication number: 20230038787
    Abstract: Disclosed is an air outlet of a nacelle for an aircraft turbojet engine, the nacelle forming a solid of revolution about a longitudinal axis, the air outlet having a straightening device having a plurality of flaps mounted circumferentially and protruding, each flap being mounted pivoting around a pivot axis, forming, with respect to the longitudinal axis, an angle of convergence in a radial plane, between a closed position, in which each flap extends along the pivot axis in the aerodynamic prolongation of the trailing edge in order to support a thrust phase and a deployed position, in which each flap extends in a deployed plane forming an angle of deployment with respect to the closed position about the pivot axis, so as to support a reverse thrust phase.
    Type: Application
    Filed: January 14, 2021
    Publication date: February 9, 2023
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Philippe Gérard Chanez, Daniel-Ciprian Mincu
  • NAVIGATION METHOD AND SYSTEM
    Publication number: 20230043214
    Abstract: Navigation device including an inertial navigation system coupled with a satellite navigation system, the information supplied by the satellite positioning system being used for adjusting the inertial navigation system, characterised in that the device further comprises means for measuring signals coming from base stations of a wireless cellular network, the satellite navigation system and the means for measuring signals coming from base stations of the wireless cellular network are coupled with each other by a tight coupling to form a satellite navigator and/or base-station navigator implementing an estimator with simultaneous localisation and mapping, and in that the satellite navigation system and the means for measuring signals coming from base stations of the wireless cellular network are coupled to the inertial navigation system by a loose coupling for adjusting the inertial navigation system.
    Type: Application
    Filed: January 26, 2021
    Publication date: February 9, 2023
    Applicants: SAFRAN ELECTRONICS & DEFENSE, M3 SYSTEMS
    Inventors: Philippe ELIE, Vincent BISGAMBIGLIA, Elie AMANI, Marc POLLINA
  • ASSEMBLY FOR A TURBINE ENGINE
    Publication number: 20230038378
    Abstract: An assembly for a turbine engine extending along an axis, includes a stator, a low-pressure compressor shaft, a low-pressure compressor comprising a rotor comprising a drum rotatably coupled to the shaft of the low-pressure compressor, and a fan comprising a disk rotatably coupled to the shaft of the low-pressure compressor. The drum has a radially internal part rotatably coupled to the shaft of the low-pressure compressor and a radially external part fixed to the radially internal part by means of detachable fixing means. A first axial retention means is configured to axially and detachably retain the disk of the fan relative to the shaft of the low-pressure compressor. A second axial retention means is configured to axially and detachably retain the radially internal part of the drum relative to the shaft of the low-pressure compressor.
    Type: Application
    Filed: January 6, 2021
    Publication date: February 9, 2023
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Philippe Gérard Edmond JOLY, Jean-Marc Claude PERROLLAZ, Laurent JABLONSKI
  • CONTROL ASSEMBLY FOR A BREATHING MASK OF AN AIRCRAFT CREW MEMBER
    Publication number: 20230041231
    Abstract: A control unit for an aircraft crew member's breathing mask, includes a support, a mode-selection knob pivotally mounted on a holder between at least a first position, a second position and a third position. A controller supplies a breathing cavity in three modes of operation depending on the position of the mode-selection knob. A locking/unlocking system includes an operating member moveable between a locking position and an unlocking position. The locking position blocks the rotation of the mode-selection knob from the second position to the third position, and the unlocking position allows rotation of the mode-selection knob from the second position to the third position.
    Type: Application
    Filed: December 8, 2020
    Publication date: February 9, 2023
    Applicant: SAFRAN AEROTECHNICS
    Inventors: Jérémy JACOTEY, Didier LAMOURETTE, Serge MOREIRA
  • BLADE COMPRISING A COMPOSITE MATERIAL STRUCTURE AND ASSOCIATED MANUFACTURING METHOD
    Publication number: 20230044779
    Abstract: The present invention relates to a blade (7) comprising: —a composite material structure (17), —a blade root fastening portion (9) further comprising a shoulder (10) extending into the recess from the wall—a base (18) arranged in the recess and comprising a support member configured to abut against the shoulder (10) of the blade root fastening portion (9) and a passage (39) formed in the support member, the sections (23) of the blade root portion (22) of the composite material structure extending through the passage (39), and—a blocking part (19) arranged in the recess between the two sections (23) of the blade root portion (22) such that each section of the blade root portion (23) is pressed against the support member by the blocking part (19).
    Type: Application
    Filed: January 19, 2021
    Publication date: February 9, 2023
    Applicant: Safran Aircraft Engines
    Inventors: Vincent JOUDON, Vivien Mickaël COURTIER, Clément Pierre POSTEC