Abstract: Rotor of a rotary electric machine, comprising a body having two opposite lateral surfaces and a surface of revolution, two short-circuiting rings disposed in contact with each lateral surface of the body, and conductors disposed in slots formed on the surface of revolution of the body and each connected to the short-circuiting rings, characterised in that each conductor comprises at least one shoulder aligned with a lateral surface of the body.
Type:
Application
Filed:
January 19, 2023
Publication date:
February 27, 2025
Applicant:
SAFRAN VENTILATION SYSTEMS
Inventors:
Claude Pendaries, Xavier Longere, Jacques Vincent, Samuel Bonnard
Abstract: A system for controlling the activation/deactivation of an electromagnetic shielding screen of a porthole or a protective window of an optoelectronic equipment, which includes, a radiofrequency electromagnetic sensor, with a bandwidth adapted to a cut-off band of said shielding screen corresponding to a range of electromagnetic fields to be blocked, connected to a detector-rectifier with a sensitivity higher than a minimum value of the power of an electromagnetic field to be blocked by means of said shielding screen and a device for activating/deactivating said electromagnetic shielding screen, said detector-rectifier being configured, in the presence of the electromagnetic field with a power exceeding said minimum value, to activate said device for activating/deactivating the electromagnetic shielding screen by capturing the electromagnetic energy supplied by said electromagnetic fields with a power exceeding said minimum value.
Type:
Grant
Filed:
February 16, 2022
Date of Patent:
February 25, 2025
Assignees:
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE, UNIVERSITE DE RENNES, SAFRAN ELECTRONICS & DEFENSE
Inventors:
Quentin Tricas, Patrice Foutrel, Philippe Besnier, Xavier Castel, Claire Le Paven
Abstract: The present disclosure relates to a system for supplying fuel to a turbomachine. In some embodiments, a fuel circuit includes a pressurisation valve at an outlet of the system and a pump. The circuit may include a flow rate sensor arranged between the outlet of the pump and the pressurisation valve. In some embodiments, the flow rate sensor may include a sliding drawer, a restoring spring, and a sensor for detecting the position of said drawer in order to indicate the flow passing through the flow rate sensor. The system may include a device arranged to drive the pump with a controllable rotational speed and a control configured to control the device on the basis of a measurement supplied by the flow rate sensor, in such a way as to adapt the rotational speed of the pump shaft.
Abstract: An air inlet of an aircraft propulsion unit comprising thrust reversal means configured to modify a bypass air flow circulating from upstream to downstream in a bypass duct into a reverse air flow circulating from downstream to upstream. The air inlet comprising an interior wall defining openings and, in each opening, a mobile member that comprises a covering wall and a deflecting wall and is mounted so as to pivot between a covering position, in which the covering wall obstructs the opening so as to guide the bypass air flow and promote a thrust phase, and a deflecting position, in which the deflecting wall obstructs the opening so as to separate the reverse air flow and promote a thrust reversal phase.
Abstract: A system for controlling discharge doors of a turbomachine includes: a ring and a device connecting the ring to each discharge door. The ring is made up of bars connected end-to-end by rotary links ensuring that a bar pivoting on itself causes the other bars to pivot on themselves, with each discharge door being connected to a corresponding bar in order to open or close when this bar pivots.
Type:
Grant
Filed:
January 26, 2022
Date of Patent:
February 25, 2025
Assignee:
SAFRAN
Inventors:
Nicolas Claude Parmentier, Gabriel Perez
Abstract: An electronic device for diagnosing the condition of a system of actuators of an aircraft turbine engine, the device being configured to be coupled to an electrical wiring harness of a turbine engine connecting a computer of a turbine engine to a system of actuators of the turbine engine, the device including a power supply block to power the device, a connection block configured to enable the connection of the device to the electrical wiring harness of the turbine engine to be diagnosed, a communication block configured to send information to a user and to receive instructions from the user, and a control block including a test signal transmission module and modules for measuring the signals received by the device in response to the test signals over a work cycle of the system of actuators of the turbine engine.
Type:
Application
Filed:
December 9, 2022
Publication date:
February 20, 2025
Applicant:
SAFRAN NACELLES
Inventors:
Patrick ARCOUËT, David PEREIRA, Hakim MAALIOUNE
Abstract: The invention relates to a method for estimating the direction of arrival of an electromagnetic wave at an antenna array (2), comprising the steps of: —estimating (202) a covariance matrix of signals acquired by the antenna array (2); —calculating (204) a normalised eigenvector of the covariance matrix; —correlating (205) the normalised eigenvector with a first reference table and a second reference table so as to produce a first correlation spectrum and a second correlation spectrum comprising correlation indices associated, respectively, with different directions of arrival; —constructing (312) a third reference table by linear combination of the first reference table and the second reference table with a polarisation component of the electromagnetic wave in the first direction and the second direction, respectively; —correlating (314) the normalised eigenvector with the third reference table so as to produce a third correlation spectrum comprising correlation indices associated with different directions of
Type:
Application
Filed:
December 13, 2022
Publication date:
February 20, 2025
Applicant:
SAFRAN ELECTRONICS & DEFENSE
Inventors:
Pierre-Antoine GARCIA, Arnaud LILBERT, Alain Michel CHIODINI
Abstract: An aircraft turbomachine has a gas generator that includes, along a longitudinal axis (X), at least one compressor, a combustion chamber, and at least one turbine. The turbomachine further includes at least one duct for supplying liquid to at least one member chosen from an oil jet and a fuel injector. The duct (20) has rectilinear portions and bent portions and includes at least one region in which the liquid is liable to coke. The turbomachine also includes at least one turbulence element in the at least one region in the duct.
Type:
Application
Filed:
December 21, 2022
Publication date:
February 20, 2025
Applicant:
SAFRAN HELICOPTER ENGINES
Inventors:
Benjamin Nicolas FULLERINGER, Alexandre DEBAT, Pierre-Marie FONTS, Olivier ROBERT
Abstract: A propulsion channel for aircraft at least one first dual-fed polyphase asynchronous rotating electric machine configured to be mechanically coupled to a turbine engine. The propulsion channel further includes at least one second polyphase rotating electric machine electrically coupled to the first asynchronous rotating electric machine, and a control and storage module configured to control the first polyphase asynchronous rotating electric machine. The module is connected to the first dual-feed polyphase asynchronous rotating electric machine as well as to the at least second polyphase rotating electric machine. The at least second polyphase rotating electric machine includes a polyphase synchronous rotating electric machine with permanent magnet.
Abstract: An autonomous impact detection device includes at least one impact detector; at least one wireless transmission device configured to transmit the information collected by the impact detector; at least one energy storage device configured to supply the impact detector and the wireless transmission device with energy; at least one Seebeck module configured to supply the storage device with energy when a temperature gradient is applied thereto; the wireless transmission device being configured to supply the storage device with energy when the temperature gradient to which the Seebeck module is exposed is not sufficient.
Abstract: The invention relates to a method for locating a transmitter, which is implemented in a processing unit of a processing station of a locating system.
Abstract: A system for conditioning fuel configured to supply a main turbomachine, based on fuel from a cryogenic tank, comprising a pump configured to operate at a predetermined constant speed, at least one heat exchanger, a supply member for supplying the main turbomachine with a fuel flow, the supply member being configured to deliver a nominal flow rate when the pump is operating at a predetermined constant speed, at least one buffer tank, a first valve for controlling the supply of fuel to the buffer tank, a second valve for controlling the distribution of the fuel flew flow and a regulating device that is configured to open the second valve when the setpoint flow rate is higher than the nominal flow rate.
Abstract: A method for repairing an end plate of a turbomachine rotor, the end plate including a crown having at least two collar fastening holes and at least one balancing-weight fastening hole located between the two collar fastening holes, each collar fastening hole being equipped with a crimped nut, the crown having a damaged portion between two collar fastening holes, the method including the steps of removing the two crimped nuts located on either side of the damage; removing the damaged crown portion, for example by machining; putting in place a strip in the form of a crown portion closing off the removed crown portion, the strip having at least one balancing-weight fastening hole and two mounting holes; fastening the strip to the crown with two crimped nuts, which penetrate the mounting holes, by crimping each nut in a collar fastening hole.
Type:
Grant
Filed:
February 9, 2022
Date of Patent:
February 18, 2025
Assignee:
SAFRAN AIRCRAFT ENGINES
Inventors:
Jean-Hilaire Lexilus, Cédric Nicolas Bot, Patrick Jean-Louis Reghezza
Abstract: Leaks in an oil lubrication circuit, in particular through a heat exchanger communicating with another circuit, are measured by the movements of a piston that is sensitive to variations in flow rates and pressure drops at two calibrated ports on either side of the predicted location of the leak. In one intended application, the second circuit contains overpressurised fuel which is used to constantly cool the oil.
Type:
Grant
Filed:
June 14, 2022
Date of Patent:
February 18, 2025
Assignee:
SAFRAN AIRCRAFT ENGINES
Inventors:
Thibault Maxime Adrien Mallet, Nicolas Andrea Fabbro
Abstract: A method of configuring an aircraft electrical system. The aircraft electrical system comprises a wiring harness and a plurality of electronic modules. The wiring harness comprises a plurality of connection points. The method comprises: connecting a first electronic module in the plurality to the wiring harness via a first connection point in the plurality; transmitting by the first electronic module, a connection point identification request; in response to the transmitting, receiving at the first electronic module from the wiring harness, an identifier of the first connection point; on the basis of the received identifier, determining configuration data for the first electronic module, the configuration data being associated with the first connection point; and configuring the first electronic module to operate in accordance with the determined configuration data.
Abstract: A seat leg assembly for a passenger seat, the seat leg assembly including: a seat leg member comprising a unitarily formed fitting member; and a plurality of stud members coupleable to the fitting member, wherein each of the plurality of stud members is formed of a material having an ultimate strength of at least 75 KSI.
Abstract: A hybrid turbofan engine for an aircraft, comprising a fan, an electric motor/generator and a gas generator, the engine comprising, between the fan and a splitter that separates the flows, an internal wall for delimiting an air duct, situated upstream of inlet guide vanes of a primary duct, and, upstream of outlet guide vanes, an internal upstream wall for delimiting a secondary duct, the motor/generator having a stator carried by a stator support fixed to a stator part of the engine. According to the invention, a plurality of heat pipe for cooling the motor/generator are provided, each heat pipe having an evaporation section fixed to the stator support, and a condensation section fixed to the internal wall or the internal upstream wall.
Type:
Grant
Filed:
January 7, 2022
Date of Patent:
February 18, 2025
Assignees:
SAFRAN, SAFRAN AIRCRAFT ENGINES
Inventors:
Thierry Sibilli, Vincent François Georges Millier, Loïc Paul Yves Guillotel
Abstract: Described is an adjustable friction slider assembly having a rail member and a carriage assembly moveably coupled to the rail member, the carriage assembly having a bracket member and a plurality of roller elements moveably coupled to the rail member and coupled to the bracket member using a plurality of attachment members, the plurality of roller elements comprising at least one adjustable roller element coupled to the bracket member using a moveable attachment member, wherein moving the moveable attachment member adjusts a friction between the plurality of roller elements and the rail member.
Abstract: A fibrous preform for forming the fibrous reinforcement of a composite material part, the fibrous preform being made as a single piece and obtained by three-dimensional weaving, the preform including first and second skins and a longitudinal stiffening portion connecting the first to the second skin, the longitudinal stiffening portion forming a stiffening element of the part in the longitudinal direction. The preform has an intermediate portion extending in the longitudinal direction between two end portions. The longitudinal stiffening portion includes, in the intermediate portion, longitudinal non-woven threads or strands held together by first transverse threads or strands coming from the first skin and second transverse threads or strands coming from the second skin. In the end portions, the longitudinal threads or strands of the longitudinal stiffening portion are woven with the transverse threads or strands.
Type:
Grant
Filed:
January 19, 2021
Date of Patent:
February 18, 2025
Assignee:
SAFRAN
Inventors:
Bruno Jacques Gérard Dambrine, Yann Didier Simon Marchal, Dominique Marie Christian Coupe, Marc-Antoine Colot
Abstract: A fan module for an aircraft turbine engine includes a fan having variable pitch blades and an oil transfer device configured to provide a transfer of oil between a stator and a rotor. The oil transfer device includes a stator ring having internal oil ducts, a shaft inserted into the ring and having internal oil ducts, and an annular support of the ring configured to deform elastically to allow movements of the ring in the radial direction. A plain bearing is located between the ring and the shaft, and roller bearings are mounted between the ring and the shaft on either side of the plain bearing.
Type:
Grant
Filed:
March 3, 2022
Date of Patent:
February 18, 2025
Assignee:
SAFRAN AIRCRAFT ENGINES
Inventors:
Julien Fabien Patrick Becoulet, Olivier Belmonte, Vincent François Georges Millier, Jean Charles Olivier Roda