Abstract: An emergency braking method for aircraft, comprising using a progressing parking brake controlled by a lever (10) that can be actuated by the pilot between a “0%” position in which the brakes are connected to the return pressure of the aircraft, and a “100%” position in which the brakes are connected to the feed pressure of the aircraft, the lever being blockable in the 100% position in order to provide parking braking when the aircraft is stationary.
Type:
Grant
Filed:
June 12, 2019
Date of Patent:
December 27, 2022
Assignee:
SAFRAN LANDING SYSTEMS
Inventors:
David Frank, Jérôme Fraval, Donny Warint
Abstract: The invention relates to an assembly (1) for a turbomachine comprising: a first rotor module (2) comprising a first blade (20), a second rotor module (3), connected to the first rotor module (2), and comprising a second blade with a length less than the first blade (20), and a damping device (4) extending with at least one component along a turbomachine longitudinal axis (X-X), characterized in that the damping device (4) is annular while extending circumferentially around the turbomachine longitudinal axis (X-X) and in that the damping device (4) comprises a first radial external surface (40) supported with friction against the first module (2) as well as a second radial external surface (42) supported with friction against the second module (3), so as to couple the modules (2, 3) in order to damp their respective vibrational movements during operation.
Type:
Grant
Filed:
December 18, 2018
Date of Patent:
December 27, 2022
Assignee:
SAFRAN AIRCRAFT ENGINES
Inventors:
Philippe Gérard Edmond Joly, François Jean Comin, Charles Jean-Pierre Douguet, Laurent Jablonski, Romain Nicolas LaGarde, Jean-Marc Claude Perrollaz
Abstract: The invention relates to an assembly (10) for a turbomachine comprising a pipe (12) connected at one end (12a) to means (14) for supplying pressurized air and at one opposite end (12b) to an item of equipment (16) of the turbomachine, the pipe (12) having a bent portion (12c) intended for forming in use a low point of the pipe (12), said bent portion (12c) having a hole (18) for first draining water from the pipe (12), wherein it further comprises an orifice (20) arranged downstream of the drain hole (18).
Type:
Grant
Filed:
April 16, 2020
Date of Patent:
December 27, 2022
Assignee:
SAFRAN AIRCRAFT ENGINES
Inventors:
Brice Cyril Edwiges, Philippe Robert Jean Goffinon, Arnaud Baudran
Abstract: A method for obtaining, by additive manufacture, a component including at least one recess, this method including: a step of forming, by additive manufacture, a one-piece blank component, in which the at least one recess contains a support including a core in the form of a block of material and cellular elements that connect the core to the recess; and a step of detaching the support from the rest of the blank component in order to expose the recess.
Type:
Grant
Filed:
March 19, 2019
Date of Patent:
December 27, 2022
Assignee:
SAFRAN AIRCRAFT ENGINES
Inventors:
Nicolas Ovaere, Jacques Marcel Arthur Bunel, Thomas Gricourt, Paul André Somazzi, Sylvain Zambelli
Abstract: Process for producing semiconductor devices in a substrate, comprising: photolithography of a pattern of a reticle onto a portion of the substrate, defining first elements of the semiconductor devices, an exposure of the pattern being repeated a plurality of times in order to define all of the devices, photolithography of a pattern of an etch mask over all of the substrate, etching photolithography patterns into one portion of the thickness of the substrate, wherein first dicing lanes encircling the devices are included in the pattern of the etch mask and/or of the reticle, and the photolithography of the etch mask defines second dicing lanes defined by predetermined fracture lines of the edges of the substrate, and furthermore comprising the implementation of a step of irradiating the substrate with a laser beam through the first and second dicing lanes.
Type:
Grant
Filed:
December 17, 2018
Date of Patent:
December 27, 2022
Assignees:
COMMISSARIAT A L'ENERGIE ATOMIQUE ET AUX ENERGIES ALTERNATIVES, SAFRAN
Abstract: A method for producing a thin-walled metal part with complex geometry includes mixing a metal powder with a polymer binder in order to obtain a composite mixture, producing a flexible composite sheet from the composite mixture, cutting, in the flexible composite sheet, a preform based on a contour of the metal part, applying the preform in a mold having a surface configured with a relief of the metal part, and debinding and sintering the preform in order to obtain the metal part.
Abstract: An electrodynamic assembly for propelling a spacecraft in orbit around a celestial body having a magnetic field is disclosed. The assembly includes a plurality of coaxial cables for an electrodynamic assembly for propelling a spacecraft in orbit around a celestial body having a magnetic field. Each coaxial cable includes an electrically conductive core surrounded by a first electrically insulating sheath, and an electrically conductive current return circuit mounted outside the first electrically insulating sheath. The current return circuit includes a first end electrically connected to a first end of the core of the coaxial cable.
Type:
Grant
Filed:
March 6, 2018
Date of Patent:
December 27, 2022
Assignee:
SAFRAN AIRCRAFT ENGINES
Inventors:
Frederic Raphael Jean Marchandise, Laurent Godard, Benjamin Laurent, Michael Oberg
Abstract: A modular and autonomous assembly for detecting the angular position of the blades of an impeller intended to be mounted on a turbine engine, the assembly comprises at least one electrical power source allowing the operation of the elements of the detection assembly independently of the turbine engine on which it is intended to be carried, at least one first sensor intended to be associated with the first impeller, at least one second sensor intended to be associated with the second impeller, and a main housing including a processing unit and storage means.
Abstract: A conductive metal frame for a power electronics module comprising at least first and second power semiconductor components each having upper and lower faces, connectors for linking these power semiconductor components to external electrical circuits and at least one radiator for expelling via the conductive metal frame the heat flow generated by the power semiconductor components, the conductive metal frame being characterized in that the connectors, the at least one radiator and the conductive metal frame forming a single three-dimensional part made of a single material on an inner surface of which the first and second power semiconductor components are intended to be attached by their lower faces and provision is made for a central folding line so that, once the conductive metal frame is folded on itself, enclosing the first and second power semiconductor components, it provides a double-sided cooling assembly.
Type:
Application
Filed:
November 12, 2020
Publication date:
December 22, 2022
Applicants:
SAFRAN, SAFRAN ELECTRONICS & DEFENSE
Inventors:
Toni YOUSSEF, Stéphane Joseph AZZOPARDI, Thanh Long LE, Jean-Christophe RIOU, Nawres SRIDI-CONVERS
Abstract: An electric module for an aircraft turbomachine includes an electric machine stator having an annular shape around an axis (A) and being configured to surround a rotor of the electric machine, and an annular support element of the stator. The support element includes an outer annular surface configured to be swept over by a gas stream (F) from the turbomachine with a view to conductively cooling the stator.
Type:
Application
Filed:
November 24, 2020
Publication date:
December 22, 2022
Applicant:
SAFRAN AIRCRAFT ENGINES
Inventors:
Vincent François Georges MILLIER, Loïc Paul Yves GUILLOTEL
Abstract: A method for removing a component fixed to an aeronautical part, the aeronautical part comprising a first material, and the component comprising a second material different from the first material, the method comprising steps of determining the thicknesses of the component as a function of the position on the component, and of removing the component by means of a pressurized water jet moving over the component as a function of the thicknesses determined in the determination step.
Type:
Application
Filed:
November 16, 2020
Publication date:
December 22, 2022
Applicants:
SAFRAN AIRCRAFT ENGINES, CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE, UNIVERSITE PAUL SABATIER - TOULOUSE III
Inventors:
Mathieu Julien CHARLAS, Damien Bruno LAMOUCHE, Redouane ZITOUNE
Abstract: A diaphragm holder for an oleo-pneumatic-type shock absorber includes a tubular body made of thermoplastic material, having a first end arranged to hold a diaphragm provided with flow restricting orifices and an opposite second end defining an arched bottom for withstanding pressure forces. Each of the two ends is provided with a localised mechanical reinforcement element forming an axial stop arranged to allow tensile stressing of the tubular body.
Abstract: A process for manufacturing a blade made of composite material for a turbomachine is provided. The blade includes an airfoil having a pressure side and a suction side which extend from a leading edge to a trailing edge of the airfoil. The blade further includes a metal sheath that extends along the leading edge of the airfoil. The process includes the steps of: a) placing a preform, made by three-dimensionally weaving fibers, in a mold, a polymerizable adhesive being inserted between the sheath and the edge of the preform; and b) injecting polymerizable resin into the mold to impregnate the preform so as to form the airfoil after solidifying, wherein the resin is injected within a time interval during which the adhesive reaches a freezing point.
Type:
Application
Filed:
November 25, 2020
Publication date:
December 22, 2022
Applicant:
SAFRAN
Inventors:
Adrien Touze, Magali Mélanie Coulaud, Nicolas Pierre Lanfant, Matthieu Stackler
Abstract: An air inlet into a nacelle of an aircraft turbojet engine having a de-icing device and extends along an axis X, an air stream flowing in the air inlet from upstream to downstream, the inlet comprising an inner wall and an outer wall which are connected by a leading edge, the inner wall having a plurality of air delivery lines, each air delivery line having a plurality of through-holes designed to blow elementary streams from the hot air source in order to de-ice said inner wall, the air delivery lines being parallel to one another in a cylindrical projection plane, each air delivery line having a depth P3 defined along the axis X as well as a length L3 defined along the axis Y in the cylindrical projection plane, two adjacent air delivery lines being spaced apart by a distance D3, each position along the axis Y with no more than one through-hole, the ratio of the distances L3/D3 being between 0.8 and 1.
Abstract: The disclosed technology concerns an aircraft turbomachine part comprising a part body drilled with at least one cavity open to the outside and at least one conduit joining the cavity on the one hand and leading to the outside on the other hand. Each cavity receives a pressure sensor, and the conduit corresponds to the cavity guides the cables connected to the sensor to the outside of the part body. The part is an aircraft turbomachine vane.
Type:
Grant
Filed:
October 3, 2019
Date of Patent:
December 20, 2022
Assignee:
SAFRAN AERO BOOSTERS S.A.
Inventors:
Nicolas Raimarckers, Maxime Dumont, Rafael Perez, Frédéric Vallino
Abstract: A method of navigating a vehicle (A) by means of a navigation algorithm arranged to determine spatial information (p(xr, yr, zr), v, a(?xr, ?yr, ?zr), PL) on the basis firstly of inertial measurements (Mi) coming from a signal processor circuit (100) for processing the signals from an inertial measurement unit (I) and secondly of pseudo-distance measurements (Mpd) determined in response to receiving signals from positioning satellites, the measurement processor circuit (100) having a calibration input adjustable on a self-calibration value (VCal) in order to reduce the influence of an error of the inertial measurement unit (I) on the spatial information (p(xr, yr, zr), v, a(?xr, ?yr, ?zr), PL) supplied by the navigation algorithm.
Abstract: A process for manufacturing pyrocarbon, includes forming pyrocarbon by a calefaction process from at least one C2 to C6 alcohol or polyalcohol precursor, the precursor being ethanol, rough laminar pyrocarbon being obtained by imposing a temperature of between 1250° C. and 1325° C. during calefaction.
Type:
Grant
Filed:
October 18, 2018
Date of Patent:
December 20, 2022
Assignees:
SAFRAN CERAMICS, CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE, COMMISSARIAT A L'ENERGIE ATOMIQUE ET AUX ENERGIES ALTERNATIVES
Inventors:
Arnaud Delehouze, Amandine Lorriaux, Laurence Maille, Patrick David
Abstract: Seat assemblies (200) including structural components (212, 222, 232) made of foam are described. A seat sub-assembly (210, 220, 230) can include a frame (214, 224, 234) and a foam support (212, 222, 232). The foam support (212, 222, 232) can be coupled to the frame (214, 224, 234) for receiving a load on the seat sub-assembly (210, 220, 230), dissipating at least half of the load, and dispersing the load through the frame (214, 224, 234).
Type:
Grant
Filed:
September 20, 2016
Date of Patent:
December 20, 2022
Assignee:
Safran Seats USA LLC
Inventors:
Jason K. Smith, Raul G. Reyes, Andrew B. Severance
Abstract: A process for manufacturing a friction component made of composite material, includes the densification of a fibrous preform of carbon yarns by a matrix including at least pyrocarbon and at least one ZrOxCy phase, where 1?x?2 and 0?y?1, the matrix being formed by chemical vapor infiltration at least from a first gaseous precursor of pyrocarbon and a second gaseous precursor including zirconium, the second precursor being an alcohol or a C1 to C6 polyalcohol modified by linking the oxygen atom of at least one alcohol function to a group of formula —Zr—R3, the substituents R being identical or different, and R being selected from: —H, C1 to C5 carbon chains and halogen atoms.
Type:
Grant
Filed:
October 16, 2018
Date of Patent:
December 20, 2022
Assignees:
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE, SAFRAN CERAMICS
Inventors:
Eric Bouillon, Arnaud Delehouze, Amandine Lorriaux, Laurence Maille
Abstract: An aeronautical thrust reverser including a sliding cowl, shutter flaps and deflection cascades. The reverser includes, for each flap, a return member hinged to the sliding cowl, to a driving connecting rod itself hinged to a front frame of the reverser, and to a return connecting rod itself hinged to the flap, the latter being moreover hinged by its rear end to the sliding cowl. The return member, the driving connecting rod and the return connecting rod form an actuation system capable of opening the secondary flow duct in a direct thrust configuration.
Type:
Application
Filed:
October 20, 2020
Publication date:
December 15, 2022
Applicant:
SAFRAN NACELLES
Inventors:
Josse PLAQUIN, Cedric François Pierre RENAULT