Patents Assigned to SAFRAN
  • Publication number: 20240200509
    Abstract: A propulsion system includes a drive shaft, a drive turbine including a drive turbine rotor having a turbine disk and turbine blades, and a fan section. The turbine disk has an inner surface, an outer surface, a bore radius, and a rim radius. One or more of the turbine blades includes a root fixed to the turbine disk in a respective slot, a stilt connected to the root and including a platform, and an airfoil connected to the platform and extending within a flowpath. The flowpath includes an outer radius and an inner radius. The drive shaft has a limit speed. The bore radius, the rim radius, the outer radius, the inner radius, and the limit speed satisfy a given relationship.
    Type: Application
    Filed: December 15, 2023
    Publication date: June 20, 2024
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Baptiste Dorian LAWNICZEK, Didier René André ESCURE, Alexandre Thanh Nhan NGUYEN
  • Publication number: 20240198611
    Abstract: This automaton for applying a patch to a draping surface (15) comprises a gripper (24) capable of grasping the patch and depositing it on the draping surface (15), and a heating system (25) for directly heating the draping surface (15).
    Type: Application
    Filed: May 6, 2022
    Publication date: June 20, 2024
    Applicant: SAFRAN NACELLES
    Inventors: Benjamin Provost, Clément Rolland, Maxime Lebegue, Renaud Venture
  • Publication number: 20240200508
    Abstract: A thrust reverser device for an aircraft turbojet engine nacelle an electro-hydrostatic actuation system that includes a motor pump and a first actuation assembly. The first actuation assembly includes a series of at least two actuators configured to be attached to a movable cover of the thrust reverser and to move the movable cover or covers between a retracted position and a deployed position relative to the nacelle. The first electro-hydraulic actuation system further includes a volumetric flow divider with an inlet connected to the motor pump and at least two outlets, wherein each outlet is connected to an actuator. The volumetric flow divider is configured to receive a fluid and to supply the fluid to the actuators with an equal flow rate.
    Type: Application
    Filed: April 11, 2022
    Publication date: June 20, 2024
    Applicant: SAFRAN LANDING SYSTEMS
    Inventor: Jean-Baptiste KAMIS
  • Publication number: 20240199202
    Abstract: An aircraft has an upper portion and a lower portion provided with a first and second axle. The first axle is provided with a braked wheel and the second axle is provided with a motorized wheel. A landing gear of the aircraft includes a main arm pivoting with respect to the strut on which the first axle is fixed. The second axle is fixed on the strut, and a main actuator moves the first axle between a remote position and a close position with respect to the upper portion. In the close position, the braked and motorized wheels are simultaneously in contact against a running plane, and in the remote position, the braked wheels are in contact against the running plane while the motorized wheel is at a distance from the running plane.
    Type: Application
    Filed: May 25, 2022
    Publication date: June 20, 2024
    Applicant: SAFRAN LANDING SYSTEMS
    Inventors: Florent FORTIER, Sébastien DUBOIS, Philippe HENRION
  • Publication number: 20240200507
    Abstract: A thrust reverser including doors, a rear shell ring and an actuation system for synchronising the pivoting of the doors and the translation of the rear shell ring.
    Type: Application
    Filed: April 21, 2022
    Publication date: June 20, 2024
    Applicant: SAFRAN NACELLES
    Inventors: Laurent Georges VALLEROY, Romain GARDEL, Loïc CHAPELAIN (Deceased)
  • Publication number: 20240200499
    Abstract: A propulsion system includes a drive shaft, a drive turbine including a drive turbine stator and a drive turbine rotor, the rotor being connected to the drive shaft and including a turbine disk and turbine blades, and a fan section including a fan rotor and a fan stator, the drive shaft being connected to the fan rotor. The turbine disk has an inner surface, an outer surface delimiting slots distributed about a longitudinal axis, one or more of the turbine blades including a root fixed to the turbine disk in a respective slot. A bore width of the inner surface, and a rim radius of the outer surface of the turbine disk, and a limit speed of the drive shaft are defined in relation to each other.
    Type: Application
    Filed: December 15, 2023
    Publication date: June 20, 2024
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Baptiste Dorian LAWNICZEK, Didier René André ESCURE, Alexandre Thanh Nhan NGUYEN
  • Publication number: 20240200493
    Abstract: The invention relates to an acoustic insulation assembly for an auxiliary power unit having a centrifugal compressor (1), comprising a ring-shaped casing (8) for an air inlet (3) and comprising a plurality of reinforcing arms (9) connecting its inner walls, a plurality of removable mechanical acoustic insulation parts (10), each mechanical part (10) being ring-shaped and comprising attachment means (11) intended to engage with the casing (8), such that the mechanical part (10) and the flow surface of the casing (8), defined by a pair of reinforcing arms (9), overlie one another.
    Type: Application
    Filed: June 30, 2022
    Publication date: June 20, 2024
    Applicant: SAFRAN POWER UNITS
    Inventors: Laurent Stéphane Tardy, Jaime Georges Paul Culla
  • Patent number: 12015868
    Abstract: Optronic equipment for assisting with piloting an aircraft includes a first set of three cameras arranged on the aircraft to generate a panoramic strip from data transmitted by the three cameras of the first set and a second set of three cameras arranged on the aircraft to generate a panoramic strip from data transmitted by the three cameras of the second set, at least one of the cameras that occupies an extreme position on the aircraft relative to the cameras of the first and second sets being arranged so as to have a field of view that is greater horizontally than vertically.
    Type: Grant
    Filed: September 10, 2019
    Date of Patent: June 18, 2024
    Assignee: SAFRAN ELECTRONICS & DEFENSE
    Inventors: Louis Massie, Emmanuel Kling, Michel Vaissiere, Thomas Devichi
  • Patent number: 12012201
    Abstract: An assembly for an aircraft turbine engine is provided. The assembly generally includes an un-ducted propeller blade of which the root has a bulbous portion; a system for setting the pitch of the blade about a pitch setting axis, the pitch setting system including a cup, configured to be placed inside the outer casing, has a flared open top end for axial insertion of the root and in which the root of the blade can be axially affixed by a locking member; and at least one radial retention prong in a radial space reserved between the wall of the cup and the root.
    Type: Grant
    Filed: July 15, 2021
    Date of Patent: June 18, 2024
    Assignee: Safran Aircraft Engines
    Inventors: Clément Cottet, Vivien Mickaël Courtier, Vincent Joudon, Thierry Georges Paul Papin
  • Patent number: 12014867
    Abstract: A connection system for exchanging electrical signals includes a first symmetrical connector and a second symmetrical connector. Each symmetrical connector has at least one magnetic core provided with at least one turn. The symmetrical connectors are produced in a substrate made of insulating material so as to form a half of a coupling transformer. At least one half of the coupling transformer of each connector is arranged opposite one another so as to be able to exchange a magnetic flux. The electrical signals are emitted by the first connector in the form of a magnetic flux, and the second connector generates the electrical signals on receiving the magnetic flux.
    Type: Grant
    Filed: May 20, 2021
    Date of Patent: June 18, 2024
    Assignee: SAFRAN ELECTRONICS & DEFENSE
    Inventors: François Guillot, Patrice Chetanneau, Pascal Spoor
  • Patent number: 12012214
    Abstract: A hybrid propulsion system for a vertical take-off and landing aircraft comprising at least one combustion engine driving an electricity generator, at least one electrical energy storage assembly associated with each electricity generator and defining, with each electricity generator, an energy branch, a plurality of electric motors actuating a same plurality of rotors providing together the propulsion and/or the lift of the aircraft, and an electrical power and distribution unit supplying power to the plurality of electric motors from the electricity generator and/or from the electrical energy storage assembly according to a pre-established flight phase, the system including at least two energy branches having an asymmetric configuration and each supplying power selectively, by means of the electrical power and distribution unit, all or part of the plurality of electric motors, and in that the electricity generators of the combustion engines have between them a power ratio comprised between.
    Type: Grant
    Filed: May 5, 2020
    Date of Patent: June 18, 2024
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Romain Jean Gilbert Thiriet, Stéphane Meyer Beddok
  • Patent number: 12012231
    Abstract: The invention relates to a method for monitoring at least one aircraft engine, said method including an acquisition (100) according to the first and second sets of measurements of respectively endogenous and exogenous variables. The method also includes: a normalization (200) of the measurements of the first set relative to the measurements of the second set, a generation (300) of a current model representative of the evolution of the behavior of the engine based on the normalized measurements, a detection (400) of potential abnormality in the behavior of the engine based on a comparison of the current model with a reference model, a generation (500) of a maintenance message, a transmission (600) of said ground message, the acquisition, normalization, generation of a current model, the detection and generation of a maintenance message being made on board the aircraft.
    Type: Grant
    Filed: March 16, 2020
    Date of Patent: June 18, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Guillaume Rémi Bonnet, Josselin Xavier Coupard
  • Patent number: 12012867
    Abstract: A fibrous texture intended to form the fibrous reinforcement of a turbomachine part, includes first yarns bonded with second yarns, and at least one vibration damping element of viscoelastic material present in a recess defined by a second de-bonding zone, the de-bonding zone separating, on a portion of the texture, a first surface part of the texture from a second part of the texture formed by a three-dimensional fabric in which the first yarns are bonded with the second yarns, the first surface part of the texture being formed by a unidimensional layer of first yarns or being formed by a two-dimensional fabric in which the first yarns are bonded with the second yarns.
    Type: Grant
    Filed: November 29, 2019
    Date of Patent: June 18, 2024
    Assignee: SAFRAN
    Inventors: Bruno Jacques Gérard Dambrine, Dominique Marie Christian Coupe, Bastien Tranquart
  • Patent number: 12012869
    Abstract: The invention relates to a turbomachine part comprising a substrate consisting of a metal material, or a composite material, and also comprising a layer of a coating for protection against the infiltration of CMAS-type compounds, at least partially covering the surface of the substrate, the protective coating layer comprising a plurality of elementary layers including elementary layers of a first assembly of elementary layers inserted between elementary layers of a second assembly of elementary layers, each elementary layer of the first assembly and each elementary layer of the second assembly comprising an anti-CMAS compound, and each contact zone between an elementary layer of the first assembly and an elementary layer of the second assembly forming an interface conducive to the spreading of cracks along said interface.
    Type: Grant
    Filed: December 26, 2018
    Date of Patent: June 18, 2024
    Assignee: SAFRAN
    Inventors: Luc Bianchi, Aurélien Joulia, André Hubert Louis Malie, Benjamin Dominique Roger Joseph Bernard
  • Patent number: 12013027
    Abstract: A planet carrier for a speed reduction gear of a turbomachine has a main axis X and includes a cage carrier with an annular row of axial fingers around the axis X, which carry first connecting elements. The carrier further includes a cage having at its periphery housings and second connecting elements that are mounted in the housings and that cooperate with the first connecting elements to form connections between the cage carrier and the cage, which allow at least one degree of freedom. The cage comprises two shells that are axially fastened to each other and separated from each other by a plane. The housings are formed respectively in the shells.
    Type: Grant
    Filed: June 23, 2022
    Date of Patent: June 18, 2024
    Assignee: SAFRAN TRANSMISSION SYSTEMS
    Inventor: Guillaume Pierre Mouly
  • Patent number: 12012230
    Abstract: The invention relates to the field of aeronautical propulsion, and more specifically to an emptying and monitoring device and method for emptying and monitoring a fluid drained from an aircraft engine. The emptying and monitoring device comprises at least one first intake passage for receiving, directly from the aircraft, fluid drained from the engine, and a first quality sensor assembly for detecting at least one quality parameter of the fluid drained from the engine, having been admitted through the first intake passage.
    Type: Grant
    Filed: June 7, 2019
    Date of Patent: June 18, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Alméric Pierre Louis Garnier, Josselin Xavier Coupard
  • Publication number: 20240195317
    Abstract: An electrical module configured to be connected to a power shaft of a turbine engine of an aircraft. The electrical module being configured to draw off power from/inject power into the power shaft. The electrical module comprising an electric machine comprising a machine housing in which a stator and a rotor is mounted, configured to be mechanically connected to the power shaft, the machine housing having a cylindrical shape extending along a cylinder axis, a first electric converter mounted in a first housing, a second electric converter mounted in a second housing, the second converter being independent of the first converter, the first housing and the second housing each being in the shape of a half-cylinder extending along the cylinder axis so as to form a cylindrical assembly that is mounted as an extension of the machine housing of the electric machine to limit the size of the electrical module.
    Type: Application
    Filed: April 11, 2022
    Publication date: June 13, 2024
    Applicant: SAFRAN ELECTRICAL & POWER
    Inventors: Philippe DELBOSC, Benoit MICHAUD, Udo MULLER, Remi GONCALVES, Samir NEHME
  • Publication number: 20240191673
    Abstract: A guide assembly for an aircraft propulsion unit, the guide assembly having a first element and at least one guide element attached to the first element. The guide element includes a bottom wall, two lateral walls connected together by the bottom wall, and an opening defined between the bottom wall and the lateral walls. The opening is configured to receive at least partly a second element configured to move relative to the guide element. The guide element can further include at least one pair of gripping tongues cooperating with holding members of the first element to retain the guide element on the first element.
    Type: Application
    Filed: September 20, 2023
    Publication date: June 13, 2024
    Applicant: SAFRAN NACELLES
    Inventors: Pierre PELLERIN, Cedric François Pierre RENAULT
  • Publication number: 20240191629
    Abstract: A nickel-based superalloy including, in weight percentages, 5.5 to 7.5% of aluminum, 1.0 to 4.0% of tantalum, 0.50 to 3.0% of titanium, 3.0 to 7.0% of cobalt, 8.0 to 12.0% of chromium, 0 to 2.5% of molybdenum, 0 to 3.0% of tungsten, 0.50 to 2.8% of rhenium, 0.05 to 0.25% of hafnium, 0 to 0.15% of silicon, the remainder consisting of nickel and unavoidable impurities.
    Type: Application
    Filed: March 25, 2022
    Publication date: June 13, 2024
    Applicant: SAFRAN
    Inventors: Jérémy RAME, Edern MENOU
  • Publication number: 20240189908
    Abstract: A method for manufacturing a metal alloy part for an aircraft turbine engine, the method including the steps of: (a) producing a blank of the part by additive manufacturing by laser fusion on a powder bed, and (b) abrasively machining the blank to obtain the part, the machining being carried out by vibratory finishing by immersing the blank in an abrasive composition contained in a tank subjected to a vibratory movement, the abrasive composition having an abrasive element formed by alumina particles, a carrying element formed by copper particles, and a liquid.
    Type: Application
    Filed: March 21, 2022
    Publication date: June 13, 2024
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Arnaud TUREL, Mickaël VOIRON