Patents Assigned to SAFRAN AIRCRAFTS ENGINES
  • Separation nozzle for aeronautic turbomachine
    Patent number: 11982195
    Abstract: A splitter between a primary flow and a secondary flow of a dual flow turbomachine includes a single-piece structure including an outer annular wall, an inner annular wall, a radial annular wall and an inner annular baffle, defining a first cavity between the outer annular wall and the inner annular baffle, and a second cavity between the inner annular wall, the radial annular wall and the inner annular baffle.
    Type: Grant
    Filed: April 14, 2020
    Date of Patent: May 14, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Damien Daniel Sylvain Lourit, Adrien Jacques Philippe Fabre, Pierre Jean-Baptiste Metge
  • Device for distributing oil from a rolling bearing for an aircraft turbine engine
    Patent number: 11982197
    Abstract: Device for distributing oil from a rolling bearing (8) for an aircraft turbine engine, comprising: —a rolling bearing (8), —an oil distributor ring (5) and —an annular track (26) of a dynamic seal (22), characterised in that it further comprises a nut (16) screwed on to a thread (5d) of the distributor ring and bearing axially against an axial end of the inner ring so as to clamp it axially, and in that the annular track is configured to bear axially against the distributor ring and comprises rotating locking elements (27) engaging with the additional elements (28) of the nut.
    Type: Grant
    Filed: March 22, 2021
    Date of Patent: May 14, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Christophe Marcel Lucien Perdrigeon, Didier Gabriel Bertrand Desombre, Regis Eugene Henri Servant
  • Device and a method for fabricating a three-dimensional part by selectively melting a powder bed
    Patent number: 11980943
    Abstract: A device for fabricating a three-dimensional part by selectively melting a powder bed, the device including a first tank for containing a first powder and provided with a first powder dispenser valve, a second tank for containing a second different powder and provided with a second powder dispenser valve, a first and a second monitoring device for monitoring the quantity of first powder delivered by the first valve and the quantity of second powder delivered by the second valve, a mixer chamber in communication with the first and second valves and including a third powder dispenser valve, and a mixer for mixing the powder particles in the chamber, a support for receiving the powder delivered by the third valve and on which the parts is to be fabricated, a powder spreader for spreading powder on the support, and a heater member for locally melting the powder spread on the support.
    Type: Grant
    Filed: July 22, 2021
    Date of Patent: May 14, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Jean-Baptiste Mottin, Guillaume Fribourg
  • Device for distributing oil from a rolling bearing for an aircraft turbine engine
    Patent number: 11982316
    Abstract: Devices for distributing oil to a rolling bearing for an aircraft turbine engine include a rolling bearing including two rings, respectively an inner ring and an outer ring, an oil distribution ring configured to be mounted on a turbine engine shaft, said distribution ring including a first outer cylindrical surface for mounting the inner ring of the bearing, an oil recovery scoop supplying a lubricating circuit of the bearing, and an annular track of a dynamic seal. The distribution ring and the track are formed by a single-piece body, and the lubricating circuit is formed in said body and extends into the distribution ring and the track.
    Type: Grant
    Filed: August 17, 2020
    Date of Patent: May 14, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Christophe Marcel Lucien Perdrigeon, Régis Eugène Henri Servant, Guillaume François Jean Bazin
  • System for controlling the pitch setting of a propeller vane for an aircraft turbine engine
    Patent number: 11981418
    Abstract: A system for controlling the pitch setting of a propeller blade for an aircraft turbine engine is provided. The system generally including a blade having an airfoil connected to a root; a cup having an annular wall extending about a pitch axis of the blade and a lower axial end enclosed by a bottom wall; a locking ring that extends around the root and inside the cup; a safety element that ensures the retention of the root relative to the cup. The at least one safety element can have a generally elongate shape and can pass through aligned holes in the bottom wall of the cup and in the free end of the root.
    Type: Grant
    Filed: July 15, 2021
    Date of Patent: May 14, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Clément Cottet, Vivien Mickaël Courtier, Vincent Joudon, Régis Eugène Henri Servant
  • Turbomachine rotary assembly comprising an annular clamping part
    Patent number: 11982188
    Abstract: A rotary assembly for a turbomachine including a rotor including at least two consecutive rotor stages provided with a plurality of blades and an annular rotor shroud connecting the two consecutive rotor stages, a stator including: at least one stator stage provided between the two consecutive rotor stages including a plurality of vanes, a turbomachine stator vane root, an annular clamping part and an annular support of abradable material, the root extending radially and being clamped axially between the annular support of abradable material and the annular clamping part, A space separates a radially internal end of the root and the annular support of abradable material. A turbojet engine including a rotary assembly as previously.
    Type: Grant
    Filed: March 19, 2021
    Date of Patent: May 14, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Simon Jean-Marie Bernard Cousseau, Nicolas Xavier Trappier, Maxime Aurelien Rotenberg
  • DEVICE FOR CENTERING AND GUIDING A SHAFT OF AN AIRCRAFT TURBINE ENGINE
    Publication number: 20240151238
    Abstract: A device for centering and guiding a shaft of an aircraft turbine engine is provided. The device includes an outer ring of a rolling bearing extending about an axis and having orifices, an annular bearing support extending about the axis and at least partially about the ring, the support having orifices and a series of studs for connecting the ring to the support. The studs can be distributed about the axis and extend parallel to the axis. The ends of first studs can be engaged without clearance in the orifices, and ends of second studs can be engaged with clearances in the orifices of the ring and/or of the support, the clearances being configured so that the device has different stiffnesses in at least two directions perpendicular to the axis.
    Type: Application
    Filed: March 9, 2022
    Publication date: May 9, 2024
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Paul Ghislain Albert LEVISSE, Emmanuel Fabrice Marie BARET, Julien Fabien Patrick BECOULET, Alexandre Jean-Marie TAN-KIM
  • Blade for a turbomachine fan, comprising an identification medium, and method for reading such an identification medium
    Patent number: 11976567
    Abstract: A blade for a turbomachine fan, the blade being made from a composite material containing a plurality of longitudinal conductive fibres embedded in an electrically non-conductive matrix, the blade having at least one fastening region to which an identification medium for identifying the blade is fastened, the fastening region containing longitudinal fibres oriented along a preferred fibre axis, the identification medium contains an item of identification data for identifying the blade and at least one radio antenna having at least one communication lobe configured so as to receive a read request and transmit the item of identification data in return, the communication lobe being oriented along a radio axis that is angularly offset from the preferred fibre axis by less than 45°, preferably by less than 22.5°.
    Type: Grant
    Filed: June 25, 2020
    Date of Patent: May 7, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Tony Alain Roger Joël Lhommeau, Dimitri Germinal Soteras, Clément René Roger Sirot, Alain Laurent Christian Vitalis
  • BLADE COMPRISING A STRUCTURE MADE OF COMPOSITE MATERIAL AND ASSOCIATED MANUFACTURING METHOD
    Publication number: 20240141917
    Abstract: The present invention relates to a blade comprising: a structure of aerodynamic profile comprising two mutually opposite skins; and a spar comprising a fibrous reinforcement obtained by three-dimensional weaving and densified by the matrix, the spar comprising a blade root portion extending outside the structure of aerodynamic profile and an airfoil portion arranged inside the structure of aerodynamic profile between the two skins. Moreover, within the blade root portion, the fibrous reinforcement of the spar comprises a non-debound region and at least two debound regions extending radially from the non-debound region so as to form at least four separate branches.
    Type: Application
    Filed: February 24, 2022
    Publication date: May 2, 2024
    Applicant: Safran Aircraft Engines
    Inventor: Vincent JOUDON
  • TURBOJET ENGINE REAR PORTION HAVING AN AUGMENTED A9/A8 NOZZLE AREA RATIO
    Publication number: 20240141852
    Abstract: A rear portion of a convergent-divergent nozzle turbojet engine includes a device for controlling the position of a divergent flap relative to that of a convergent flap, including a first connecting rod having a first end portion hinged to the convergent flap and an opposite second end portion, a second connecting rod having a first end portion hinged to the divergent flap and an opposite second end portion, and a third connecting rod having a first end portion hinged to a synchronization ring and an opposite second end portion. The second end portion of the first connecting rod is hinged to the second end portion of the second connecting rod and/or to the second end portion of the third connecting rod, and the second end portion of the third connecting rod is hinged to the second end portion of the second connecting rod.
    Type: Application
    Filed: February 14, 2022
    Publication date: May 2, 2024
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Thierry KOHN, Dimitri Thomas KRAJKA
  • Fastening for a turbomachine combustion chamber
    Patent number: 11971174
    Abstract: A turbomachine has the upstream portion of the annular combustion chamber is fixed to the outer housing via individual pins with a swivel connection. The swivel connection is established between the pin and a part of the outer housing. The pin is slidable radially, or with a radial component, by a slide established between the pin and a tubular part of the outer annular shroud and/or the annular wall of the chamber bottom.
    Type: Grant
    Filed: May 14, 2020
    Date of Patent: April 30, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Dan-Ranjiv Joory, Jacques Marcel Arthur Bunel, Benjamin Frantz Karl Villenave
  • Assembly between an aircraft pylon and a turbomachine
    Patent number: 11970280
    Abstract: The invention relates to an assembly between an aircraft pylon (30) and a turbomachine (20) of longitudinal axis (X), the pylon (30) and the turbomachine (20) each comprising front and rear longitudinal regions, the assembly comprising a rear support (40) configured to connect the rear region of the turbomachine (20) to the rear region of the pylon (30), the assembly being characterized in that the rear support (40) comprises a sliding pivot connection arranged between the rear region of the turbomachine (20) and the rear region of the pylon (30), so as to allow the turbomachine (20) only translational and rotational movements along and about the longitudinal axis (X) and along and about a vertical axis (Z) and a rotational movement about a transverse axis (Y).
    Type: Grant
    Filed: January 5, 2021
    Date of Patent: April 30, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Guillaume Glemarec, Guilhem Seize, Eric Francois Michel Maingre, Jean-Baptiste Vignes
  • Core for high-temperature shaping of a metal part and manufacturing, regeneration and shaping process
    Patent number: 11970955
    Abstract: A metal core for hot-forming a titanium-based alloy metal component is disclosed. The metal core has on an outer surface, intended to come into contact with the metal component, a layer of metal carbonitride-enriched material. The metal core comprises a nickel- or cobalt-based alloy. The metal core comprising a steel coating having an outer surface intended to come into contact with the metal component, the steel coating having a layer of metal carbonitride-enriched material. Processes for manufacturing and regenerating the metal core and a process for hot-forming a metal component using the metal core are also disclosed.
    Type: Grant
    Filed: June 18, 2020
    Date of Patent: April 30, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Gilles Charles Casimir Klein, Dominique Michel Serge Magnaudeix
  • Arrangement for an aircraft turbine engine having improved lubrication, the arrangement comprising a shaft rotatably coupled to a following member by means of splines
    Patent number: 11970983
    Abstract: An arrangement for an aircraft turbine engine, including a shaft and a follower element rotatably coupled to the shaft by a spline connection, the arrangement including upstream and downstream connections for radially centring the follower element relative to the shaft; means for spraying a lubricant into a collection cavity; a passage for receiving lubricant, which passage opens into the collection cavity and into a cavity for lubricating the splines which is partially defined by the upstream and downstream radial centring connections; and a passage for discharging lubricant, which passage opens into the cavity for lubricating the splines and outside the arrangement.
    Type: Grant
    Filed: April 23, 2021
    Date of Patent: April 30, 2024
    Assignees: SAFRAN AIRCRAFT ENGINES, SAFRAN TRANSMISSION SYSTEMS
    Inventors: Matthieu Bruno François Foglia, Serge René Morreale, Adrien Louis Simon
  • TURBOMACHINE DISTRIBUTOR COMPRISING A GAS REINTRODUCTION DUCT WITH A TANGENTIAL COMPONENT
    Publication number: 20240133311
    Abstract: A distributor for a turbine of a turbomachine. The distributor includes a radially inner platform, a blade and a root which is coated with a track made of an abradable material. According to the invention, the distributor includes a leakage gas reintroduction duct. The duct includes an inlet through the track made of an abradable material, an outlet opening through a downstream surface of the root, and a duct intermediate portion which extends from the inlet up to the outlet. The duct intermediate portion is orientated with a tangential component.
    Type: Application
    Filed: February 14, 2022
    Publication date: April 25, 2024
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Jérôme Claude George LEMONNIER, Franck Davy BOISNAULT, Antoine Bruno VAN NOORT
  • GUIDE VANES ASSEMBLY WITH POSITION-MAINTAINING DEVICE
    Publication number: 20240133306
    Abstract: A turbine engine nozzle extending about an axis and including a vane assembly mounted between an outer shroud and an inner shroud; and a position retaining device configured to be placed in an elastically prestressed state between the inner shroud and an inner platform of the vane assembly to apply a stress on the vane assembly towards the outer shroud. The contact between the inner shroud and the inner platform is obtained by one same surface of the position retaining device.
    Type: Application
    Filed: February 8, 2022
    Publication date: April 25, 2024
    Applicants: SAFRAN AIRCRAFT ENGINES, SAFRAN CERAMICS
    Inventors: Sébastien Serge Francis CONGRATEL, Aurélien GAILLARD, Matthieu Arnaud GIMAT, Clément JARROSSAY, David René Pierre LE CAIR
  • DISTRIBUTED PROPULSION WITH OFFSET PROPULSION MODULES
    Publication number: 20240133339
    Abstract: A propulsion unit including: a gas generator including a compressor, a combustion chamber, a turbine, at least two compressed-air propulsion modules, each propulsion module including: a fan, a compressed-air turbine configured to drive the rotation of the fan, a manifold allowing the respective turbines of the compressed-air propulsion modules to be supplied with compressed air, wherein the manifold is configured to collect and mix: at least a portion of the flow that has passed through the combustion chamber of the gas generator, typically as it leaves the turbine, and at least one bypass flow, the bypass flow being a flow of air which is not passed through the combustion chamber of the gas generator.
    Type: Application
    Filed: October 13, 2020
    Publication date: April 25, 2024
    Applicants: INSTITUT SUPERIEUR DE L'AERONAUTIQUE ET DE L'ESPAC, SAFRAN, SAFRAN AIRCRAFT ENGINES
    Inventors: Patrick GONIDEC, Miguel Angel AGUIRRE, Sébastien DUPLAA, Bernard ROBIC, Benoit RODRIGUEZ, Nicolas Jérôme Jean TANTOT
  • TURBOJET ENGINE NOZZLE RING FOR AN AIRCRAFT
    Publication number: 20240133302
    Abstract: The turbomachine subassembly comprises:—at least one tow-pressure nozzle ring, the nozzle ring comprising a root (38) integral with the nozzle ring;—a clamp (40) configured so as to fasten the root to a casing of the turbomachine; and—at least two pads (150) interposed between the root and the clamp, each pad being assembled in a form-fitting manner with one of either the root or the clamp.
    Type: Application
    Filed: February 18, 2022
    Publication date: April 25, 2024
    Applicant: Safran Aircraft Engines
    Inventors: Alice Marie CLEMENT, Paul GRANDIN, Clément MARCHAND, Vijeay PATEL, Mireya SANCHEZ GOMEZ
  • ACCESSORY GEARBOX FOR AN AIRCRAFT TURBINE ENGINE COMPRISING A VERY LOW-SPEED ENGINE AND USE METHOD
    Publication number: 20240133346
    Abstract: An accessory gearbox for an aircraft turbine engine having a radial shaft connecting a high-pressure body of the turbine engine to a gear train having at least one mixed shaft coupled to a high-speed device. The accessory gearbox has a clutch system having a low-speed motor mounted thereon and configured to mate with the mixed shaft such that: in an engaged position of the clutch, the low-speed motor is coupled to the mixed shaft so as to drive the high-pressure body at low speed when the turbine engine is stationary and, in a disengaged position of the clutch, the low-speed motor is decoupled from the mixed shaft so as to be protected when the turbine engine is in operation.
    Type: Application
    Filed: February 24, 2022
    Publication date: April 25, 2024
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventor: Frédéric Dautreppe
  • METHOD AND DEVICE FOR GENERATING AN ALARM FOR MONITORING AN OIL FILTER IN AN AIRCRAFT
    Publication number: 20240131457
    Abstract: A method for generating an alarm is implemented by an alarm-generating device installed in an aircraft. It comprises: a step of obtaining information delivered by a sensor of said device and representative of an oil flow rate inside an oil filter of the aircraft; a step of obtaining a temperature delivered by a sensor of said device and representative of a temperature of the oil inside said filter; a step of obtaining a differential pressure at said filter; and a step of generating an alarm if the differential pressure exceeds an alarm threshold obtained on the basis of said information and of said temperature.
    Type: Application
    Filed: February 18, 2022
    Publication date: April 25, 2024
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Jean-Louis MULLER, Thibault Maxime Adrien MALLET