Patents Assigned to SAFRAN NACELLES
  • Thrust inverter with optimized opening and closing system
    Patent number: 11286880
    Abstract: A thrust reverser includes two thrust reverser elements movable between a retracted position in which the thrust reverser is inactive and a deployed position in which the thrust reverser is active, a cylinder for deploying the thrust reverser elements, and a single-acting cylinder for retracting the thrust reverser elements.
    Type: Grant
    Filed: April 25, 2019
    Date of Patent: March 29, 2022
    Assignee: Safran Nacelles
    Inventors: Pierre Caruel, Regis Giard, Denis Guillois, Philippe Vancon
  • AIRCRAFT PROPULSION UNIT
    Publication number: 20220082064
    Abstract: An aircraft propulsion unit including a nacelle and a turbojet engine. The aircraft propulsion unit includes an external envelope, at least one fan casing, at least one actuator, and at least one support structure. The external envelope includes fan cowls. The fan casing cooperates with the fan cowls to define an interior space configured to house a thrust reverser configured to be displaced between a first position and a second position. The actuator configured to move the thrust reverser between the first position and the second position The support structure connects the fan cowls and the fan. The support structure includes at least one aperture configured to allow passage of part of the actuator.
    Type: Application
    Filed: November 29, 2021
    Publication date: March 17, 2022
    Applicants: Safran Nacelles, SAFRAN AIRCRAFT ENGINES
    Inventors: Patrick BOILEAU, Pierre CARUEL, Gina FERRIER, Quentin GARNAUD, Guillaume GLEMAREC
  • DEVICE FOR ATTACHING A LIFTING TOOL TO AN AIRCRAFT NACELLE THRUST REVERSER DOOR
    Publication number: 20220081128
    Abstract: A device for fixing a lifting tooling on an aircraft component includes a threaded screw, a hollow body, an orientation and positioning system, and a retraction system. The threaded screw has a longitudinal axis and includes a distal end having a screw head. The threaded screw further includes a threaded proximal end and an intermediate part. The hollow body houses the threaded screw while allowing the rotation of the threaded screw along its longitudinal axis. The orientation and positioning system is configured to allow rotation of the threaded screw about axes transverse to the longitudinal axis of the threaded screw, and translation of the threaded screw parallel to its longitudinal axis. The retraction system is configured to retract the threaded proximal end of the threaded screw in the hollow body.
    Type: Application
    Filed: November 29, 2021
    Publication date: March 17, 2022
    Applicant: Safran Nacelles
    Inventors: Tony DEHAIS, Vivien LUCIENNE
  • Turbine engine nacelle comprising a cooling device
    Patent number: 11268443
    Abstract: A nacelle of a turbine engine has a substantially tubular structure and defines a secondary channel. The nacelle includes a shroud forming a trailing edge on a downstream end of the nacelle, the shroud being defined by at least one outer face subjected to an outside air flow and an inner face subjected to an inside air flow circulating in the secondary channel of the nacelle. The nacelle further includes a cooling device having at least one heat-exchange channel that extends into the shroud.
    Type: Grant
    Filed: January 22, 2019
    Date of Patent: March 8, 2022
    Assignee: Safran Nacelles
    Inventors: Vincent Peyron, Patrick Gonidec, Jean-Nicolas Bouchout
  • NACELLE AIR INTAKE AND NACELLE COMPRISING SUCH AN AIR INTAKE
    Publication number: 20220041295
    Abstract: An air intake for a nacelle of an aircraft engine includes a substantially cylindrical outer wall, a substantially cylindrical inner wall, a front lip, a front mounting flange, and a support structure. The front lip connects the substantially cylindrical inner wall and the substantially cylindrical outer wall. The front mounting flange is configured to cooperate with a rear flange of a wall of the aircraft engine forming a fan casing. The support structure comprises a lower end configured to be secured to the fan casing, by the rear flange, and an upper end in contact at least with a downstream portion of the outer wall. The support structure includes access apertures configured to be crossed by maintenance tools during operations of maintenance of the air intake.
    Type: Application
    Filed: October 26, 2021
    Publication date: February 10, 2022
    Applicant: Safran Nacelles
    Inventors: Gina FERRIER, Patrick BOILEAU
  • NACELLE AIR INTAKE WITH AN ACOUSTIC PANEL
    Publication number: 20220042454
    Abstract: An air intake of a turbojet engine nacelle includes an annular structure including an outer fairing defining an aerodynamic outer surface and an inner fairing defining an aerodynamic inner surface. The outer and inner fairings are connected upstream by an air intake lip forming a leading edge. The inner fairing includes an outer skin fixed to the air intake lip by an upstream fixation flange, and the outer skin is configured to be fixed to an outer fan casing by a downstream fixation flange. The air intake includes at least one independent acoustic panel attached to the outer skin and which includes a perforated acoustic skin and a cellular core.
    Type: Application
    Filed: October 26, 2021
    Publication date: February 10, 2022
    Applicant: Safran Nacelles
    Inventors: Pierre CARUEL, Bertrand DESJOYEAUX, Bertrand LEROYER, Marc VERSAEVEL, Laurent Georges VALLEROY
  • AIR INTAKE FOR A TURBOJET ENGINE NACELLE
    Publication number: 20220042455
    Abstract: An air intake of a turbojet engine nacelle includes an air intake lip, an annular structure, a rear partition, and at least one acoustic attenuation structure. The annular structure includes at least a part of an outer fairing and an inner fairing joined to each other by the air intake lip. The rear partition is connected to the inner fairing. The acoustic attenuation structure is attached to the inner fairing of the annular structure. At least part of the outer fairing, the air intake lip and the inner fairing are integral with each other.
    Type: Application
    Filed: October 26, 2021
    Publication date: February 10, 2022
    Applicant: Safran Nacelles
    Inventors: Denis GUILLOIS, Fabienne QUENU, Anne MOUNIER, Franck Philippe Gérald ZAGANELLI
  • NACELLE AIR INTAKE AND NACELLE COMPRISING SUCH AN AIR INTAKE
    Publication number: 20220042456
    Abstract: An air intake for a nacelle for an aircraft engine includes a front lip connecting a substantially cylindrical internal wall and a substantially cylindrical external wall, and at least one acoustic structure including acoustic cells. The acoustic structure is situated in the space delimited by the internal wall, the external wall and the front lip. The acoustic structure is an added part secured to the air intake. The acoustic cells of the acoustic structure are arranged facing a region of the internal wall or of the lip at a predetermined distance so that the acoustic cells of the acoustic structure are not in contact with the internal wall or the lip while providing an acoustic attenuation function.
    Type: Application
    Filed: October 26, 2021
    Publication date: February 10, 2022
    Applicant: Safran Nacelles
    Inventors: Virginie Emmanuelle Anne Marie DIGEOS, Marc VERSAEVEL, Paul OLDHAM, Patrick BOILEAU
  • NACELLE AIR INTAKE AND NACELLE COMPRISING SUCH AN AIR INTAKE
    Publication number: 20220041296
    Abstract: An air intake includes a substantially cylindrical inner wall, a substantially cylindrical outer wall, a front lip connecting the inner wall and the outer wall, a front mounting flange, and a support structure. The front mounting flange is configured to cooperate with a rear flange of a wall of an aircraft engine. The support structure is configured to be secured to the wall of the aircraft engine at a location longitudinally downstream of the mounting flange. The outer wall includes a downstream end configured to be positioned in a junction area flush with a front end of a fan external cowl. A portion of the outer wall being configured to bear at least against the support structure. The support structure is configured to be secured to the wall of the aircraft engine so that a load path passes directly from the outer wall towards the fan casing.
    Type: Application
    Filed: October 26, 2021
    Publication date: February 10, 2022
    Applicant: Safran Nacelles
    Inventors: Gina FERRIER, Patrick BOILEAU, Pierre CARUEL
  • Tubular fibrous structure with lobes
    Patent number: 11235492
    Abstract: A tubular structure having lobes is produced as a single piece over at least two lobes. Circumferential fibres of the structure have a constant orientation with respect to the longitudinal axis (A) of the structure in any plane (P) transverse to the longitudinal axis. The structure is obtained by weaving or by filament winding.
    Type: Grant
    Filed: November 25, 2019
    Date of Patent: February 1, 2022
    Assignee: Safran Nacelles
    Inventors: Bertrand Desjoyeaux, Benjamin Provost, Fabien Depeux, Davi Silva De Vasconcellos
  • METHOD FOR MANUFACTURING A STRUCTURAL SURFACE HEAT EXCHANGER FOR A NACELLE
    Publication number: 20220023931
    Abstract: A method for manufacturing a structural surface heat exchanger of preset or left-hand final shape for an aircraft includes the steps of forming, shaping and assembling, by welding or brazing, a first corrugated skin and a second smooth skin in order to obtain channels. Each channel is delimited by a corrugation of the first skin and the second smooth skin so as to form a structural surface heat exchanger of preset or left-hand final shape, wherein a fluid is configured to circulate in the channels and air is configured to circulate in contact with the second smooth skin.
    Type: Application
    Filed: October 4, 2021
    Publication date: January 27, 2022
    Applicant: Safran Nacelles
    Inventors: Vincent PEYRON, Jean-Nicolas BOUCHOUT, Flavie HUBERT-CHOINARD, Alexandra DUGARDIN
  • SYSTEM FOR COOLING AN AIRCRAFT TURBOJET ENGINE
    Publication number: 20220025816
    Abstract: A cooling system for cooling an aircraft turbojet engine includes a first heat-exchanger for exchanging heat between a heat-transfer fluid and a lubricant of the turbojet engine, a second heat-exchanger for exchanging heat between the heat-transfer fluid and air, and a circulation duct for circulating heat-transfer fluid in a closed circuit. The cooling system further includes at least one regulating device for regulating the heat drawn from the lubricant, controlled by a control module of the regulating device that is configured to receive information according to the various flight phases.
    Type: Application
    Filed: October 4, 2021
    Publication date: January 27, 2022
    Applicant: Safran Nacelles
    Inventors: Julien CORBIN, David PEREIRA, Vincent PEYRON, Jean-Nicolas BOUCHOUT, Caroline DANG, Nicolas CHOUQUET
  • Heat-transfer fluid for a cooling system of an aircraft turbojet engine
    Patent number: 11230973
    Abstract: In a cooling system of an aircraft turbojet engine surrounded by a nacelle, a heat-transfer fluid is circulated that is less flammable than a lubricant (H) for the turbojet engine and liquid at temperatures between ?70° C. and +175° C., the heat-transfer fluid (C) being intended to circulate in a closed-circuit circulation duct including a first surface heat-exchanger between the heat-transfer fluid (C) and air (F), at the level of at least one of the outer fairing and the inner fairing of the nacelle, and a second surface heat-exchanger between the heat-transfer fluid (C) and the lubricant (H).
    Type: Grant
    Filed: April 3, 2020
    Date of Patent: January 25, 2022
    Assignee: Safran Nacelles
    Inventors: Vincent Peyron, Jean-Nicolas Bouchout
  • SYSTEM FOR CONTROLLING A THRUST REVERSER FOR A NACELLE
    Publication number: 20220010752
    Abstract: A control system includes an actuator, a locking/unlock device, a central control valve, first and second control valves, and a spool control valve. The actuator is arranged so as to move a door of a thrust reverser between direct jet and reverse jet positions. The locking/unlocking device unlockable under load allowing locking and/or unlocking of the door. The locking/unlocking device is movable between a closure position in which it holds the door in the direct jet position and an opening position in which the door is released. The first and second control valves each fed by the central control valve. The spool control valve fed at least by the first and second control valves. The spool control valve is configured so that a pressure difference between two inlets of the first and second control valves provides a displacement of the spool control valve between first and second stable positions.
    Type: Application
    Filed: August 16, 2021
    Publication date: January 13, 2022
    Applicant: Safran Nacelles
    Inventors: Pierre Caruel, Régis Giard, Alexandre Descamps, Philippe Vancon
  • Acoustic attenuation panel for an aircraft propulsion unit and propulsion unit including such a panel
    Patent number: 11220346
    Abstract: An acoustic attenuation panel for a propulsion unit including a nacelle and a turbojet engine includes a cellular core disposed between an inner skin and an outer skin, called acoustic skin, the acoustic skin including a plurality of acoustic apertures, the acoustic apertures being inclined, at a non-zero inclination angle (?) relative to the direction normal to the acoustic skin, upstream with respect to the flow direction of the air or gas flow to which the panel is intended to be subjected under normal operating conditions, that is to say upstream of the propulsion unit when the panel is mounted in such a unit.
    Type: Grant
    Filed: January 29, 2019
    Date of Patent: January 11, 2022
    Assignees: Safran Nacelles, Safran Aircraft Engines
    Inventors: Marc Versaevel, Denis Ramage, Baptiste Cordier, Georges Riou, Jacky Mardjono
  • SEALING JOINT FOR AIRCRAFT TURBOJET ENGINE NACELLE
    Publication number: 20210404417
    Abstract: A sealing joint for an aircraft turbojet engine nacelle includes a bead designed to be mounted in a joint support. The sealing joint is characterized in that the bead includes a retaining projection which extends in a direction substantially transverse to a longitudinal axis of the sealing joint, the retaining projection being designed to extend through the joint support when the sealing joint is mounted in the support thereof and/or a sealing lip which extends under the bead in a direction substantially parallel to the longitudinal axis of the sealing joint and which is designed to be compressed on the joint support when the sealing joint is mounted in the support thereof.
    Type: Application
    Filed: May 10, 2021
    Publication date: December 30, 2021
    Applicant: Safran Nacelles
    Inventors: Cédric RENAULT, Arnaud BONNY
  • Hydraulic control system for a thrust reverser comprising a data concentrator module
    Patent number: 11203999
    Abstract: The present disclosure relates to a hydraulic control system for a thrust reverser of an aircraft turbofan nacelle. The hydraulic control system includes devices for actuating and controlling the reverser having hydraulic locks and cylinders, the corresponding hydraulic solenoid valves, and sensors. The turbofan includes a full-authority electronic computer or aircraft having an avionics computer that gives reverse thrust commands. The system further includes an electronic concentration module, different from the computer, which concentrates the data relating to the operation of the reverser actuation and control devices. The module includes internal contact switches for controlling the solenoid valves, a device for monitoring the sensors, a device for analog or digital processing of the data, and a bus for communication with the computer.
    Type: Grant
    Filed: June 14, 2018
    Date of Patent: December 21, 2021
    Assignee: Safran Nacelles
    Inventor: Vincent Pierre Germain Le Coq
  • METHOD FOR CREATING ALVEOLAR CORES HAVING OPEN INNER CONICAL SHAPES
    Publication number: 20210390940
    Abstract: A method for manufacturing a sound attenuating panel uses an alveolar-core structure including a first edge and a second edge separated by alveolar cells, the alveolar cells including walls extending from the first and second edges and defining a primary conduit for the circulation of a sound wave that is to be attenuated. The method includes covering the first edge or the second edge of the alveolar-core structure with a compartmentation wall; deforming the compartmentation wall to define at least one secondary conduit for the circulation of a sound wave that is to be attenuated, the secondary conduit extending at least partially within said primary conduit; and creating an opening in the compartmentation wall to permit communication between the primary and secondary conduits.
    Type: Application
    Filed: August 30, 2021
    Publication date: December 16, 2021
    Applicant: Safran Nacelles
    Inventors: Bertrand DESJOYEAUX, Marc VERSAEVEL, Mathieu PREAU, Laurent MOREAU
  • Thrust reverser with movable cascades for an aircraft propulsion unit and related mounting and dismounting methods
    Patent number: 11199158
    Abstract: An aircraft propulsion assembly with an engine provided with a cascade-type thrust reverser includes cascades of mobile deflection vanes connected to cascade rails with a slideway connection that allows the cascades of vanes a translational movement between a cruising-flight position and a reverse-thrust position. The thrust reverser allows the cascade rails to be positioned in a forward position, in which the engine, the cascade rails and the deflection vanes can be removed from the propulsion assembly without the cascade rails colliding with the mobile cowl of the reverser. Dismantling and assembly or reassembly methods allow maintenance operations to be carried out on the engine thus dismantled.
    Type: Grant
    Filed: May 18, 2020
    Date of Patent: December 14, 2021
    Assignee: Safran Nacelles
    Inventors: Pierre Caruel, Vincent Peyron
  • EXPANDABLE CELLULAR SYSTEM FOR A SANDWICH PANEL
    Publication number: 20210380220
    Abstract: A sandwich panel for an aircraft turbojet nacelle includes an outer skin in contact with an air flow, an inner skin opposed to the outer skin, and an intermediate system comprising partitions connecting the inner and outer skins so as to form cells, the inner skin of at least one cell having at least one corrugation configured to allow the materials making up the sandwich panel to deform in the event of thermal variation.
    Type: Application
    Filed: August 26, 2021
    Publication date: December 9, 2021
    Applicants: Safran Nacelles, SAFRAN CERAMICS
    Inventors: Bertrand DESJOYEAUX, Davi SILVA DE VASCONCELLOS, François TAILLARD, Florent BOUILLON