Patents Assigned to SAFRAN
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Publication number: 20230018527Abstract: A three-phase rotary transformer includes a first, a second and a third primary coil respectively associated with a first, a second and a third secondary coil. The second primary and secondary coils each include a first and a second sub-coil. Each of the first and third coils are housed with a respective sub-coil of the second coil respectively in a first and in a second housing of a slot of a magnetic body. For each slot, the housing corresponding to a sub-coil, has an axial dimension greater than an axial dimension of the housing corresponding to the corresponding coil.Type: ApplicationFiled: November 19, 2020Publication date: January 19, 2023Applicants: SAFRAN AIRCRAFT ENGINES, SAFRAN ELECTRICAL & POWERInventors: Cedric Arnaud Henri DUVAL, Rachid BELFKIRA
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Publication number: 20230014208Abstract: In an electromechanical actuation chain for controlling the movement of mobile loads of an aircraft turbine engine, from a control unit, one or more of these mobile loads being actuated by an electromechanical actuator, there is provided for control of this movement a single Ethernet controller having deterministic control that uses an Ethernet bus to control a set of converters acting selectively on the electromechanical actuators.Type: ApplicationFiled: December 1, 2020Publication date: January 19, 2023Applicant: SAFRAN AIRCRAFT ENGINESInventors: Nicolas Bertrand Georges DE BLOIS, Clément DUPAYS
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Publication number: 20230013057Abstract: The invention relates to a blade pivot with adjustable orientation for a turbomachine fan hub, comprising a stud having means for retaining a fan blade root and coupling means for the transmission of a torsional torque, a rolling bearing for absorbing the centrifugal forces having an inner bushing mounted in transverse abutment against an external radial portion of the stud, a ring for radially retaining the stud relative to the rolling bearing housed in an annular groove formed in the stud, a plurality of clamping parts each mounted in transverse abutment against the retaining ring and in radial abutment against the inner bushing of the rolling bearing, and a clamping nut screwed onto an outer thread of the stud to come into conical abutment against the clamping parts such that said clamping parts ensure a clamping of the inner bushing of the rolling bearing on the stud and a clampingType: ApplicationFiled: December 3, 2020Publication date: January 19, 2023Applicant: SAFRAN AIRCRAFT ENGINESInventors: Vincent François Georges MILLIER, Olivier BELMONTE
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Patent number: 11555454Abstract: A triple-flow turbomachine for an aircraft, including a power transmission module including a torque input connected to a turbine shaft, a first torque output of a gearbox connected to a main shaft for rotatably driving a main fan propeller, and a second torque output of a planet gear connected to a secondary shaft for rotatably driving a secondary fan propeller. The planet gear is independent of the gearbox and arranged downstream of the gearbox.Type: GrantFiled: January 25, 2022Date of Patent: January 17, 2023Assignee: SAFRAN TRANSMISSION SYSTEMSInventor: Guillaume Pierre Mouly
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Method for calibrating a photodetector array, a calibration device, and an associated imaging system
Patent number: 11557063Abstract: A method for calibrating a photodetector array supplying a video stream includes: a determination step, wherein an offset table is determined for each current image of the video stream based on at least two corrections from among the following: a first correction from a comparison of the current image to a corresponding predetermined reference table; a second correction from a calculation of a column error of the current image; and a third correction from a high-pass temporal filtering of the video stream; and a calculation step, wherein a current value of an offset table, equal to a sum between a previous value of the offset table and a weighted sum of at least two corrections, is calculated, with each coefficient of the offset table being associated with a respective photodetector of the array.Type: GrantFiled: December 23, 2021Date of Patent: January 17, 2023Assignee: SAFRAN ELECTRONICS & DEFENSEInventor: Yves Michels -
Patent number: 11554878Abstract: An aircraft undercarriage including electrical equipment (2, 3) fastened to a portion (1) of the undercarriage and a lightning protection device (10) comprising at least one shield fastened to said portion (1) of the undercarriage by fastener means so as to extend in register with the electrical equipment (2, 3) in a position that is spaced apart therefrom, the shield comprising at least a first plate (11) made of electrically conductive material that is arranged to absorb a major portion of the heat energy that is generated by the passage of a lightning wave and to discharge the electric charge of the lightning wave. An aircraft fitted with such an undercarriage.Type: GrantFiled: April 25, 2019Date of Patent: January 17, 2023Assignee: SAFRAN LANDING SYSTEMSInventors: Jérôme Gui, Alexandre Avenet, Pierre Pizana, Yvain Serignac
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Patent number: 11555405Abstract: A device for holding (101) at least one cooling tube (120) of a turbomachine casing (10) cooling system (100), the holding device including a fixing frame (104), a holding member (160) being configured to hold two cooling tubes (120), and a connection assembly (140) between the holding member (160) and a fixing frame (104), extending on either side of the frame, the connection assembly (160) comprising a connection part (150) extending through an opening (108) of the fixing frame from an outer portion (141) to the inner portion (142) of the connection assembly, the inner portion (142) being disposed between two cooling tubes (120) and secured to the holding member (160) while the outer portion (141) comprises a resilient return member (170) urged in compression towards the fixing frame by the connection part (150).Type: GrantFiled: December 5, 2019Date of Patent: January 17, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Simon Nicolas Morliere, Nicolas Jean-Marc Marcel Beauquin, Stéphane Pierre Guillaume Blanchard, Gaëlle Inès Méganne Moreaux
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Patent number: 11554534Abstract: A method of a coating by additive manufacturing on a turbomachine casing includes depositing on an internal surface of the turbomachine casing a filament of an abradable material to create a three-dimensional scaffold of filaments. A filamentary material deposition system is positioned from the internal surface of the casing; a first layer of the coating is deposited over 360?; a rotation of the filamentary material deposition system is carried out by a first predetermined angle and the filamentary material deposition system is positioned from the deposited layer; a second layer of coating is deposited on the first coating layer, on a sector of the casing; a displacement is carried out corresponding to the first sector already covered, then for the following sectors until 360° is covered; and after having carried out a rotation of the filamentary material deposition system.Type: GrantFiled: December 6, 2018Date of Patent: January 17, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Norman Bruno Andre Jodet, Jeremy Paul Francisco Gonzalez, Jacky Novi Mardjono, Arnaud Dubourg, Edith-Roland Fotsing, Annie Ross, Daniel Therriault
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Patent number: 11555406Abstract: A turbine engine blade having an aerodynamic surface extending a first direction between a leading edge and a trailing edge and in a second direction, perpendicular to the first direction, between a root of the blade and a tip of the blade, the aerodynamic surface being made of a fiber-reinforced organic matrix composite material, and a metallic structural reinforcement bonded by an adhesive joint to the leading edge whose shape it follows and which has over its entire height a substantially V-shaped section with a base extended by two lateral flanks having a thinned profile at free ends directed toward the trailing edge, the adhesive joint being locally supplemented below the free ends of the lateral flanks by an elastomeric polymer introduced in the form of solid particles into the adhesive joint and adhered to the aerodynamic surface and/or the free ends of the lateral flanks during a polymerization phase.Type: GrantFiled: July 24, 2019Date of Patent: January 17, 2023Assignee: Safran Aircraft EnginesInventors: Vincent Joudon, Franck Bernard Léon Varin
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Patent number: 11555408Abstract: Counter-rotating turbine (C) of a turbomachine (10) extending about an axis (X) and comprising an inner rotor configured to rotate about the axis of rotation (X), and comprising an inner drum on which an inner movable blading (22) is fixed, an outer rotor configured to rotate about the axis of rotation (X) in a direction opposite to the inner rotor, and comprising an outer drum (50) on which an outer movable blading (20) is fixed, the outer movable blading (20) comprising at least one fixing rod (212) extending through an orifice (51) of the outer drum (50), the outer movable blading (20) being fixed to the outer drum (50) via a clamping means (100) fixed to the fixing rod (212) from an outer face of the outer drum (50), a set ring (80) being disposed around the fixing rod (50) in the orifice (51) of the outer drum (50).Type: GrantFiled: April 3, 2020Date of Patent: January 17, 2023Assignee: Safran Aircraft EnginesInventors: Patrick Jean Laurent Sultana, Clément Charles Jérémy Coiffier, Olivier Renon, Laurent Cédric Zamai
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Publication number: 20230007929Abstract: A propulsion system includes a drive shaft movable about an axis of rotation, a fan, a fan shaft that drives the fan, and a reduction device coupling the drive shaft and the fan shaft. The reduction device has first and second reduction stages and includes a sun gear, centered on the axis and driven by the drive shaft, a ring gear that is coaxial with the sun gear and that drives the fan shaft about the axis, and planet gears distributed circumferentially about the axis between the sun gear and the ring gear. Each planet gear includes a first portion meshed with the sun gear and a second portion meshed with the ring gear. A diameter of the first portion is different from a diameter of the second portion, and the first portion of the planet gears extend between the second portion of the planet gears and the fan.Type: ApplicationFiled: December 11, 2020Publication date: January 12, 2023Applicants: SAFRAN AIRCRAFT ENGINES, SAFRAN TRANSMISSION SYSTEMSInventors: Caroline Marie FRANTZ, Gilles Alain Marie CHARIER, Adrien Louis SIMON
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Publication number: 20230008954Abstract: Rolling bearing with three contact points, wherein the inner raceway, the third contact point being located in a sector of the outer raceway delimited by a proximal end of the outer raceway on the one hand, and by the rolling plane on the other hand, characterized in that the outer ring comprises a drain provided in the outer raceway, and opening from an outer surface of the outer ring, said drain opening eccentrically on the outer raceway with respect to the rolling plane, in a sector of the outer raceway delimited by the rolling plane on the one hand, and a distal end of the outer raceway on the other hand, the drain and the third contact point being disjoint.Type: ApplicationFiled: December 15, 2020Publication date: January 12, 2023Applicant: SAFRAN HELICOPTER ENGINESInventors: Benjamin Nicolas FULLERINGER, Damien Paul Antonin LECOUVREUR, Laurent Jean CRABOS
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Publication number: 20230010959Abstract: A regulator assembly for an aircrew breathing mask includes a support and a mode selection knob mounted with the ability to pivot on the support. The selection knob is able to pivot between at least a first position, a second position and a third position. The mask further includes regulator designed to supply a breathing cavity at least in three modes of operation according to the position of the mode selection knob. At least one locking/unlocking device locks and unlocks the rotation of the mode selection knob towards the third position. The locking/unlocking device comprising has an operating member that pivots between a position in which the rotation of the mode selection knob is locked, and a position in which the rotation of the mode selection knob is unlocked.Type: ApplicationFiled: December 8, 2020Publication date: January 12, 2023Applicant: SAFRAN AEROTECHNICSInventors: Jérémy JACOTEY, Didier LAMOURETTE, Serge MOREIRA
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Publication number: 20230010552Abstract: An antenna in a system is provided and includes a first device and at least one second mobile device, where the first device communicates with the second device(s). In an acquisition mode, for each antenna of an antenna system, a first item of communication quality information is obtained, and the antenna the first item of information of which is the highest is selected. In a pursuit mode, if the selected antenna is sectoral, a second item of communication quality information is obtained, and the antenna the second item of information of which is the highest is selected. For each antenna, a third item of communication quality is obtained if the selected antenna is the omnidirectional antenna, and from the third items of information, the antenna the third item of information of which is the highest is selected.Type: ApplicationFiled: December 18, 2020Publication date: January 12, 2023Applicant: SAFRAN ELECTRONICS & DEFENSEInventor: Eric TODESCHINI
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Patent number: 11549176Abstract: A process for densifying annular porous substrates by chemical vapour infiltration, includes providing a plurality of unit modules including a support plate on which is formed a stack of substrates, the support plate including a central gas inlet opening communicating with an internal volume formed by the central passages of the stacked substrates and gas outlet openings distributed angularly around the central opening, and a thermal mass cylinder disposed around the stack of substrates having a first end integral with the support plate and a second free end, forming stacks of unit modules in the chamber of a densification furnace, and injecting into the stacks of unit modules a gas phase including a gas precursor of a matrix material to be deposited within the porosity of the substrates.Type: GrantFiled: July 24, 2019Date of Patent: January 10, 2023Assignee: SAFRAN CERAMICSInventors: Franck Lamouroux, Rémy Dupont, William Ros
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Patent number: 11548624Abstract: A method of moving a door of a well for an aircraft undercarriage during sequences of deploying or retracting the undercarriage includes: using a temporary mechanical connection between the door and the undercarriage that is effective when the undercarriage is close to its retracted position, causing the door to be opened by the undercarriage while the undercarriage is being deployed and causing the door to be closed by the undercarriage while the undercarriage is being retracted, but releasing the door from the undercarriage when the undercarriage is close to its deployed position, and using a door actuator acting on the door to close and open the door when the undercarriage is in its deployed position and the temporary mechanical connection is interrupted.Type: GrantFiled: June 18, 2019Date of Patent: January 10, 2023Assignee: SAFRAN LANDING SYSTEMSInventors: Yannick Senechal, Vincent Pascal, Thierry Blanpain, Aurélien Doux
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Patent number: 11549577Abstract: An improved serviceability gearing element generally includes a support having a plurality of obstacles for co-operating with teeth of a neighboring gearing element. The gearing element further includes a pin, a roller mounted to move in rotation about the pin via a rotary guide, blocking bearings shaped substantially to prevent the roller from moving in translation along the pin, and one or more fasteners for fastening at least one of the blocking bearings to the support.Type: GrantFiled: March 21, 2018Date of Patent: January 10, 2023Assignee: SAFRAN LANDING SYSTEMSInventors: Gilles Eluard, Stéphane Lambre
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Patent number: 11549448Abstract: The invention relates to a method for controlling the speed and the power of a turbine engine propeller, wherein at least two operating modes are implemented: —one operating mode, called “speed mode”, in which the pitch (?) of the propeller is controlled as a function of the desired propeller speed, while the fuel flow is controlled as a function of the desired torque; the other operating mode, called “? mode”, in which the fuel flow is controlled as a function of the desired propeller speed, the pitch (?) of the propeller being set to a limit angle (?min) that limits the pitch of the propeller in the two operating modes, the pitch angle (?min(t)) being continuously computed and updated during a flight on the basis of parameters relating to the flight conditions estimated in real time.Type: GrantFiled: February 7, 2018Date of Patent: January 10, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventor: Cedrik Djelassi
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Patent number: 11549462Abstract: A turbojet engine nacelle having a cascade-type thrust reverser includes a movable frame surrounding a cold air flow path, guided axially by longitudinal rails fixed to an intermediate casing surrounding the cold air flow path and supporting cascades of thrust-reversal guide vanes and mobile rear cowls. The nacelle has a passage of ancillaries opening radially towards the outside of the movable frame, in a zone with no bearing structure passing radially across the cold air flow path. The movable frame is cut in an axial plane at the passage for the passage of ancillaries, and each edge of the cut of the movable frame is connected to the intermediate casing by a slide rail fitted on a longitudinal rail arranged each on one side of this passage.Type: GrantFiled: May 27, 2020Date of Patent: January 10, 2023Assignees: Safran Nacelles, SAFRAN AIRCRAFT ENGINESInventors: Sébastien Michel Thierry Guillemant, Pierre Caruel, Olivier Kerbler, Alexis Heau, Mathieu Lerouvreur, Antoine Elie Hellegouarch
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Patent number: 11549394Abstract: The disclosure provides devices for cooling a turbine casing for a turbomachine and methods of using the same. The devices extend around an axis (X) and include air-distribution means configured to take in air and convey it to the casing. The air-distribution means include a first ramp and a second ramp extending circumferentially about the axis (X), each ramp having air ejection orifices intended to be directed towards the casing in order to cool it The devices further include adjustment means capable of adjusting the flow rate of air ejected at the level of the first ramp with respect to the flow rate of air ejected at the level of the second ramp.Type: GrantFiled: December 3, 2019Date of Patent: January 10, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Julian Nicolas Girardeau, Maxime Aurélien Rotenberg