Patents Assigned to SAFRAN
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Publication number: 20220286019Abstract: An aeronautical turbogenerator for hybrid electric propulsion includes a heat engine and an electrical generator coupled mechanically to the heat engine and including a rotor and a stator, the rotor extending in an axial direction and including a common magnetized rotor yoke comprising a plurality of permanent magnets defining at least three axially distributed movable annular rings, the stator including a magnetic stator yoke comprising a plurality of electrical windings defining axially and/or circumferentially distributed stationary sectors, at least two stationary sectors, one of which covers axially at least two movable annular rings, being arranged angularly so as not to mutually coincide and thus deliver at least two distinct and independent voltage levels.Type: ApplicationFiled: July 24, 2020Publication date: September 8, 2022Applicants: SAFRAN HELICOPTER ENGINES, SAFRANInventors: Loïs Pierre Denis VIVE, Christophe Ludovic Jean-Claude VIGUIER
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Publication number: 20220282408Abstract: A weaving installation includes a loom that receives a series of strands, and at least one device for measuring the diameter of a strand having a defined number of filaments. The device includes a diaphragm having an external ring forming a support on which a series of strips forming an iris are fixed. The strips are movable and allow a substantially circular space with variable dimensions to be defined at the center of the iris. The diaphragm is configured to adjust the dimensions of the space so as to allow a strand of the loom to pass through it, and to encircle the profile of the strand so as to allow the number of filaments in the strand to be determined.Type: ApplicationFiled: August 20, 2020Publication date: September 8, 2022Applicant: SAFRAN AIRCRAFT ENGINESInventors: François CHARLEUX, Steven Gérard Joseph BIENVENU
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Patent number: 11434943Abstract: A method for controlling a cylinder includes providing a cylinder having a piston, a servo valve and a measuring device having at least one first position sensor and one second position sensor, measurements are taken of the position of the piston in the cylinder body simultaneously with the first position sensor and the second position sensor, at least one first displacement speed of the piston is determined on the basis of the piston position measurements obtained with the first position sensor, at least one second displacement speed of the piston is determined on the basis of the piston position measurements obtained with the second position sensor, and each of the first and second determined displacement speeds of the piston are compared with a modelled or predetermined displacement speed of the piston, in such a way as to identify the most reliable position sensor.Type: GrantFiled: November 26, 2019Date of Patent: September 6, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Christophe Marc Alexandre Le Brun, Charles Ying, Alexis Ferrer Belloti Cardin
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Patent number: 11433336Abstract: A drive pinion of an air/oil separator of an accessory gearbox of a turbomachine, the air/oil separator being configured to be supplied at the input by an air flow to de-oil and to supply at the output, on the one hand, a de-oiled air flow and, on the other hand, an oil flow by centrifugation, the pinion being configured to drive the separator rotationally along an axis of rotation, the pinion being mounted facing a passage opening of the separator, the pinion comprising at least one guiding opening traversing the web plate defining at least one guiding surface inclined with respect to the axis of rotation in such a way as to guide along the axis an air flow to de-oil into the separator or a de-oiled air flow out of the separator via the guiding opening of the pinion.Type: GrantFiled: March 30, 2020Date of Patent: September 6, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Alexis Pereira, Thierry Kohn
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Patent number: 11434769Abstract: A tubular ventilation sleeve for a turbomachine distributor, in particular for an aircraft, the sleeve having a generally elongate shape along an axis (A-A) and including a perforated tubular wall around said axis, one of the axial ends of the sleeve being open and the other being closed by a bottom wall, wherein it further includes support beams when the sleeve is made by additive manufacturing, the beams extending inside the sleeve between the tubular wall and the bottom wall and having a longitudinal cross-section with a generally triangular shape, two sides of which are respectively connected to the tubular wall and the bottom wall and the last side of which is free and extends inside the sleeve, perforations in the tubular wall being provided between the support beams.Type: GrantFiled: March 16, 2020Date of Patent: September 6, 2022Assignees: SAFRAN AIRCRAFT ENGINES, SAFRAN HELICOPTER ENGINESInventors: Guillaume Klein, Matthieu Jean Luc Vollebregt, Thomas Joseph Lardellier, Guillaume Carrerot, Stephane Lavignotte
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Patent number: 11433989Abstract: The present invention relates to a force application device for a control stick of an aircraft, wherein the control stick comprises a control lever (1) rotating a shaft (A1) about a first axis (A), the device comprising a magnetic brake (5a) which comprises a magnetisable element (50a) mounted on the shaft and a magnetic transmitter (51a) which is opposite the magnetisable element and free to rotate about the first axis relative to the magnetisable element, the magnetic transmitter having an activated state in which the magnetic transmitter is supplied with current and generates a magnetic field in a volume occupied by the magnetisable element, and a deactivated state in which the magnetic transmitter is not supplied with current and does not generate a magnetic field, so as to prevent the magnetisable element from rotating about the shaft relative to the magnetic transmitter.Type: GrantFiled: May 6, 2020Date of Patent: September 6, 2022Assignee: SAFRAN ELECTRONICS & DEFENSEInventors: Rémi-Louis Lawniczak, Yannick Attrazic
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Patent number: 11434017Abstract: The invention relates to the field of fairings of aircraft propulsion units, and more particularly to an assembly comprising a longitudinal beam (31) configured to be mounted on a lateral of a turbofan (7) engine core (11), oriented parallel to a longitudinal axis (X) of the turbofan (7), an opening fairing (18) cowl (50) of the engine core (11) and a deployment mechanism (60) mounted on the longitudinal beam (31) to move the opening cowl (50) between an open position and a closed position.Type: GrantFiled: December 18, 2018Date of Patent: September 6, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Antoine Elie Hellegouarch, Quentin Matthias Emmanuel Garnaud, Marc Patrick Tesniere
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Patent number: 11434773Abstract: The invention relates to an assembly for a turbomachine extending along an axis (X) and comprising: —a ferrule (32) designed to define a fan duct (5) of a gas stream of the turbomachine, —a fan casing (2) radially surrounding the ferrule (32) and defining with the ferrule (32) the fan duct (5), —a rectifier (6) comprising a plurality of vanes (7) comprising a first vane (7a) and a second vane (7b) adjacent to the first vane (7a), the vanes defining between them a converging flow channel (13) designed to direct and accelerate the stream by means of an inlet section (14a) included in a plane non-perpendicular to the axis of the turbomachine and an outlet section included in a plane (14b) perpendicular to the axis (X) of the turbomachine, the first vane (7a) and the second vane (7b) each having an unducted downstream portion which forms a trailing edge.Type: GrantFiled: March 12, 2020Date of Patent: September 6, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventor: Florent Matthieu Jacques Nobelen
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Patent number: 11435263Abstract: A pylon for supporting an aircraft turbomachine, in particular for a test bench, the pylon having a generally elongated shape along an axis and including, at a first longitudinal end, first members for fixing to a turbomachine and, at a second longitudinal end, second members for fixing to a base plate, the pylon being traversed by at least one fluid pipe including a first end for connecting to the turbomachine and a second end for connecting to a fluid supply circuit, wherein the at least one pipe includes a movable portion movable in translation along the axis so as to be able to adjust the position along the axis of the first connecting end relative to the first longitudinal end. It also concerns a method of mounting an aircraft turbomachine on such a pylon.Type: GrantFiled: August 7, 2019Date of Patent: September 6, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Jacky Raphael Michel Derenes, Michael Daniel Joel Bertin, Etienne Romain Pascal Grenier
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Patent number: 11435433Abstract: A method for locating an element which can be transported by aircraft includes, for a first position of an aircraft: a) transmitting, from an antenna located in the aircraft, a first message intended for the transportable element; b) receiving, on the antenna, a second message transmitted by the transportable element upon receipt of the first message; c) obtaining a travel time of the first and second messages; d) determining a distance from the travel times; e) determining that the element is inside the aircraft if the distance is less than a value and that the element is outside the aircraft if the distance is greater than the value.Type: GrantFiled: June 19, 2020Date of Patent: September 6, 2022Assignee: SAFRAN ELECTRONICS & DEFENSEInventors: Louis Théophile Thirion, Nicolas Paris
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Patent number: 11435707Abstract: The proposed aircraft engine control system includes at least one servo-loop, and at least one state feedback control integrated into the servo-loop. The state feedback control includes a static compensator (M) and a state corrector loop (L) which are parametrized so as to decouple the states constituted by the operating parameters of the engine to be servo-controlled. The mono-variable regulators are then in turn parameterized so as to servo-control the operating parameters on the setpoints.Type: GrantFiled: August 9, 2018Date of Patent: September 6, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Christophe Marc Alexandre Le Brun, Bogdan Cristian Liacu
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Patent number: 11433453Abstract: A device (10) for manufacturing a metal alloy blank by centrifugal casting of a molten metal alloy, comprising a centrifugal casting wheel (20), the centrifugal casting wheel (20) being rotary about an axis of rotation (A) and comprising a mold (22) for receiving the molten metal alloy, the mold extending in a radial direction (R1) with respect to the axis of rotation (A). The device (10) comprises at least one magnet arranged in such a way as to induce an electric current in the mold (22) during the rotation of the centrifugal casting wheel (20) about the axis of rotation (A).Type: GrantFiled: November 6, 2018Date of Patent: September 6, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventor: Laurent Ferrer
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Patent number: 11434000Abstract: A propulsion system for an aircraft, comprising at least one rotor and a nacelle fairing extending around the at least one rotor with respect to an axis of rotation of the rotor, the nacelle fairing comprising: an upstream section forming an inlet section of the nacelle fairing; a downstream section, a downstream end of which forms an outlet section of the nacelle fairing; and an intermediate section connecting the upstream and downstream sections, wherein the downstream section comprises a radially inner wall and a radially outer wall made of a deformable shape memory material, and wherein the downstream end forming the outlet section has a pneumatic or hydraulic annular actuator extending around the axis of rotation and configured to deform radially under a predetermined control pressure so as to vary an outer diameter of the outlet section between a minimum diameter and a maximum diameter.Type: GrantFiled: April 10, 2020Date of Patent: September 6, 2022Assignee: SAFRANInventors: Jean-Louis Robert Guy Besse, Ye-Bonne Karina Maldonado
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Patent number: 11434826Abstract: An acoustic absorption cell including a bottom wall extending in a plane orthogonal to an axial direction, an enclosure including a first axial end secured to the bottom wall, and an acoustic horn extending inside the enclosure between a first opening of the horn and a second opening of the horn smaller than the first opening, the horn being secured to a second axial end of the enclosure opposite the first axial end, and the first and second openings of the horn each extending in a plane orthogonal to the axial direction. The horn includes at least one retaining arm protruding from the horn inside the enclosure and fixed to the bottom wall or to the enclosure.Type: GrantFiled: September 9, 2019Date of Patent: September 6, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Georges Jean Xavier Riou, Jeremy Paul Francisco Gonzalez, Jacky Novi Mardjono
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Patent number: 11435279Abstract: A method for analysing a bonding between two aeronautical parts. The method includes the steps of a) applying a release agent to a first surface to be bonded of a first part and to a second surface to be bonded of a second part, b) applying an adhesive to at least one of the first and second surfaces and positioning these surfaces on top of each other, the adhesive forming an adhesive film after polymerisation, c) separating the parts from each other and removing the adhesive film in one piece, d) analysing the adhesive film. The invention also relates to a method for bonding two aeronautical parts.Type: GrantFiled: May 4, 2021Date of Patent: September 6, 2022Assignees: SAFRAN, SAFRAN AIRCRAFT ENGINESInventors: Pierre-Antoine Bossan, Thierry Patrick Chauvin, Lauren Chin, Cali Lapenta, Philippe Gallois
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Publication number: 20220274716Abstract: An aircraft auxiliary power unit is equipped with a charging compressor. A method determines a surge parameter indicative of a risk that the charging compressor will display the phenomenon known as surge. A method and a system control a relief valve of this charging compressor. The method for determining the surge parameter includes calculating this surge parameter Ppomp as being the sum of a first term T1 and of a second term T2, the first term T1 being calculated on the basis of a first pressure P1 measured downstream of a diffuser of the charging compressor, and of a second pressure P2 measured upstream of the diffuser, the second term T2 being calculated on the basis of a third pressure P3 measured upstream of the diffuser and of an ambient pressure Psamb indicative of a pressure of an ambient environment.Type: ApplicationFiled: July 31, 2020Publication date: September 1, 2022Applicant: SAFRAN POWER UNITSInventors: David Francis Pierre ORMIERES, Louis Jean-Paul Fabien PERROT-MINOT
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Publication number: 20220276743Abstract: A tactile interface including a touch pad and a support, the touch pad being hingedly attached to the support between the extended active position and a retracted inactive position, in which the pad is folded back towards the support wherein the support constitutes a drawer which is movable in a casing between a pulled-out position in which the interface is in the active position and an inserted position in which the interface is in the retracted position.Type: ApplicationFiled: July 9, 2020Publication date: September 1, 2022Applicant: SAFRAN ELECTRONICS & DEFENSE COCKPIT SOLUTIONSInventor: Thomas Thorpe
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TOOL AND METHOD FOR DISASSEMBLING AND MOVING A TRV-TYPE TURBINE CASING OF AN AIRCRAFT TURBINE ENGINE
Publication number: 20220275735Abstract: A TRV-type turbine casing includes inner and outer annular shrouds that extend one inside the other and about the same axis and are connected together by arms. A tool for disassembling and moving the casing has a lower carriage for moving the tool, and an upper plate to be attached to the turbine casing. The plate is supported by the carriage and includes first members that cooperate with a first annular flange of one of the shrouds to support the casing and axially immobilize the casing relative to the tool. The plate further includes second members that cooperate with a second annular flange of the other shroud in order to prevent and/or guide the rotation of the casing about the axis.Type: ApplicationFiled: July 16, 2020Publication date: September 1, 2022Applicant: SAFRAN AIRCRAFT ENGINESInventors: Sébastien Georges CISTAC, Olivier Jean CAUDRON -
Publication number: 20220279441Abstract: Systems, processes and methods are described for increasing the reliability of packet delivery while reducing end-to-end latency and power consumption in a low power wireless network. The packet is forwarded during a transmit timeslot utilizing link layer broadcast transmissions. A preset number of retransmission timeslots are provided to retransmit the packet. To reduce energy consumption for recipients, a recipient can enter a sleep mode after receiving the packet for the remaining retransmit timeslots.Type: ApplicationFiled: July 30, 2020Publication date: September 1, 2022Applicant: Safran Passenger Innovations, LLCInventors: Sushmit Bhattacharjee, Steven Lemaire, Tinku Rasheed
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Publication number: 20220275732Abstract: A bellcrank for a variable adjustment device for an aircraft turbomachine, is articulated respectively to a control housing, to a synchronization bar, to a piston stem of an actuator and to a turnbuckle. The bellcrank includes a part for articulation to the control housing which includes, on the one hand, a tab and, on the other hand, a tubular portion spaced apart from the tab, the tab and the tubular portion including orifices that are aligned and are configured to receive a common axis of articulation of the control housing.Type: ApplicationFiled: August 20, 2020Publication date: September 1, 2022Applicant: SAFRAN AIRCRAFT ENGINESInventors: Clélia Antoinette Barbier-Neveu, Erick Jacques Boston, Yann Thierry Robert