Patents Assigned to SAFRAN
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Patent number: 11440416Abstract: In some embodiments, a control unit for a vehicle is provided. The vehicle may be a maglev vehicle. The control unit is configured to autonomously control positions of landing gear on the vehicle that are extendible and retractable. In some embodiments, the control unit is configured to detect a change in a weight-on-wheels state of the vehicle, and to transition between passively controlling extension or retraction of the landing gear and actively controlling the extension distance of the landing gear in order to maintain a desired distance between the vehicle and a levitation mechanism.Type: GrantFiled: February 28, 2020Date of Patent: September 13, 2022Assignees: SAFRAN LANDING SYSTEMS, SAFRAN LANDING SYSTEMS CANADA INC.Inventors: Andrew Michael Ellis, Graeme Peter Arthur Klim, Thibaud Mazoue
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Patent number: 11440670Abstract: The invention concerns a suspension device (4) for a turbomachine comprising a body (15) intended to be fixed to a fixed part of an aircraft, extending along a longitudinal axis (A) intended to be parallel to a driving shaft axis of the turbomachine once the suspension device (4) is connected to the turbomachine, a first connecting rod (28) and a second connecting rod (29) located in the same transverse plane (P) perpendicular to the longitudinal axis (A) of the body, each comprising a first end articulated with respect to the body (15), and a second end intended to be articulated to a first part of the turbomachine, a third connecting rod (37) articulated on the body (15) between the first ends of the first and second connecting rods (28, 29) and intended to be articulated on a first part of the turbomachine between the second ends of the first and second connecting rods (28, 29), the suspension device (4) being characterised in that it further comprises a rudder (45) articulated on the body (15) and a fourtType: GrantFiled: December 14, 2018Date of Patent: September 13, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Antoine Elie Hellegouarch, Marc Patrick Tesniere
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Patent number: 11444522Abstract: The disclosure relates to a brushless and magnet-free synchronous electrical machine, wherein it comprises a stator (20) comprising a ring (22), a winding (28) and a tooth system (24) comprising teeth (26) extending parallel to the axis of rotation from the ring (22), said winding being wound around the tooth system (24), a rotor (10), comprising a first portion (12a) extending in p preferred directions (18a), a second portion (12b) extending in p preferred directions (18b) shifted by p with respect to the preferred directions of the first portion (18a), and an intermediate portion (14) linking the first portion (12a) to the second portion (12b), and a coil (40) for exciting the rotor, fixed with respect to the stator, supplied with a DC electric current, positioned around the intermediate portion (14) of the rotor and configured so as to generate an electric flux in the rotor (10) through magnetic induction.Type: GrantFiled: April 12, 2019Date of Patent: September 13, 2022Assignee: SAFRAN ELECTRICAL & POWERInventor: Lionel Bourgeois
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Patent number: 11441434Abstract: A turbine ring assembly including ring sectors forming a turbine ring and a ring support structure, each sector having, in a section plane defined by an axial direction and a radial direction of the ring, a first and a second attachment tabs extending in the radial direction, and the structure including a central shell ring from which extend as projections a first and a second radial flanges between which are retained the first and second attachment tabs of each sector. Each sector includes rectilinear seatings mounted on the faces of the first and second attachment tabs in contact, respectively, with the second annular flange and the annular ring-flange and including, along a tangent to the circumferential direction, a variable thickness in the axial direction with a minimum thickness at the first and second ends of the sector and a maximum thickness in a median portion of the rectilinear seating.Type: GrantFiled: December 10, 2019Date of Patent: September 13, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Antoine Claude Michel Etienne Danis, Sébastien Serge Francis Congratel, Clément Jean Pierre Duffau, Lucien Henri Jacques Quennehen, Nicolas Paul Tableau
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Patent number: 11444561Abstract: Described is a system that includes a polyphase generator and a polyphase bridge rectifier electrically coupled to an output of the polyphase generator. The polyphase bridge rectifier may output a positive rectified ripple signal and a negative rectified ripple signal, and the positive rectified ripple signal and the negative rectified ripple signal may be summed to produce a total ripple signal. Further, the system may include a generator regulation feedback control loop that regulates the output of the polyphase generator with a field control signal. In an embodiment, the field control signal is based on summing the total ripple signal and a reference voltage.Type: GrantFiled: September 20, 2018Date of Patent: September 13, 2022Assignee: Safran Power USA, LLCInventors: Lev Sorkin, Manali S. Patil
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Patent number: 11444660Abstract: An emitting device includes: an oscillator configured for generating at least one carrier wave; an emitter including: at least one input connected to the oscillator; an activation input configured for receiving a signal representative of data to be transmitted; at least one output configured to generate a carrier wave modulated by the signal representative of the data to be transmitted; a communication link connected to the output of the emitter; a power line connected to the communication link at a connection point; a capacitive coupling component connected between the output of the emitter and the connection point. A receiving device and a system for transmission are also described.Type: GrantFiled: April 4, 2019Date of Patent: September 13, 2022Assignee: SAFRAN AEROTECHNICSInventor: Zoran Racic
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Patent number: 11441439Abstract: A lubricated enclosure for an aircraft turbine engine, including a drained roller bearing provided with drainage orifices, as well as a lubricant ejector intended to limit the retention of lubricant in a critical zone of the enclosure, the ejector being intended to be passed through by a primary lubricant flow in order to drive a secondary lubricant flow located around a nozzle of the ejector housed in the critical zone of the enclosure. The enclosure includes a device for establishing communication between the drainage orifices and the ejector, such that the lubricant that escapes from the drainage orifices supplies the ejector in order to form the primary flow.Type: GrantFiled: September 27, 2017Date of Patent: September 13, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventor: Serge Rene Morreale
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Patent number: 11441431Abstract: The present disclosure relates to a holding system for the dismantling of a blade wheel, the blade wheel comprising: a disc, a plurality of blades configured to be mounted circumferentially around the disc, the plurality of blades defining a plurality of inter-blade spaces, each of the inter-blade spaces being defined circumferentially between two adjacent blades of the plurality of blades, the holding system comprising a plurality of inserts, each of the inserts being configured to be inserted into each of the inter-blade spaces in a holding position so as to hold the relative position of the blades when the plurality of blades is dismantled from the disc.Type: GrantFiled: June 6, 2019Date of Patent: September 13, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Nicolas Daniel Delaporte, Alain Dominique Gendraud, Emmanuel Bernard Marie Charrier
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Patent number: 11440144Abstract: The invention relates to a retaining device for disassembling a bladed wheel of a turbine engine. The invention is characterized in that the retaining device (100) includes: an inter-blade ring sector (101), a plurality of retaining clips (105), each retaining clip (105) cooperating with one of the damping elements (40), the retaining clips (105) extending radially while being attached circumferentially to the ring sector (101).Type: GrantFiled: December 12, 2019Date of Patent: September 13, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Yannick Durand, Nicolas Daniel Delaporte
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Patent number: 11441442Abstract: A sealing device between a rotor part and a stator part, including at least one abradable coating cooperating with at least two upstream and downstream labyrinth seal lips. Axially upstream of the labyrinth seal lips, the sealing device includes a circumferential wall that radially extends beyond the upstream free axial sealing surface of the coating to create, at the free end of the upstream labyrinth seal lip, a separation of the circulating gas.Type: GrantFiled: April 24, 2018Date of Patent: September 13, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Baptiste Marie Aubin Pierre Jouy, Josselin Luc Florent Sicard, Mathieu Charles Jean Verdiere, Loïc Fabien François Villard
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Patent number: 11440095Abstract: A method for heat treating a powder part preform including a titanium-based alloy, wherein the method includes the heat treatment of the preform in a furnace at a predetermined temperature, wherein the preform is on a holder during the heat treatment, wherein the holder includes a zirconium-based alloy having a zirconium content greater than or equal to 95% by weight, wherein the holder material has a melting temperature higher than the predefined temperature of the heat treatment, and wherein an anti-diffusion barrier is arranged between the preform and the holder in order to prevent welding of the preform to the holder.Type: GrantFiled: March 5, 2021Date of Patent: September 13, 2022Assignees: SAFRAN AIRCRAFT ENGINES, ALLIANCEInventors: Guillaume Fribourg, Jean-Claude Bihr, Clément Gillot
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Patent number: 11441486Abstract: The invention relates to a semiconductor body revolving around a main axis (A) for a spark plug of a turbine engine, the semiconductor body comprising a baseplate and an upper portion extending from the baseplate along the main axis, the baseplate comprising a bottom surface substantially defined in a plane perpendicular to the main axis and a first conical surface intended to cooperate by form-fitting at least partially with a contact surface of an outer electrode of the spark plug. According to the invention, the upper portion comprises an interface located opposite the bottom surface along the main axis (A) and featuring a profile that is at least partially corrugated.Type: GrantFiled: February 21, 2020Date of Patent: September 13, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Thomas Gérard Daniel Riviere, Guillaume Thierry Richen, David Gino Stifanic
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Patent number: 11441646Abstract: A mechanism for driving a first member for adjusting the orientation of the blades of a first stage of a turbine engine diffuser and a second member for adjusting the orientation of the blades of a second stage of the turbine engine diffuser, including a single drive wheel which simultaneously drives the first adjustment member and the second adjustment member and a set of gears which is arranged between the drive wheel and the two adjustment members, wherein the set of gears includes a first gearwheel which is directly coupled with the drive wheel and with the first adjustment member and which is coupled with the second adjustment member with a secondary gearwheel which is directly coupled with the second adjustment member.Type: GrantFiled: October 6, 2017Date of Patent: September 13, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventor: Pierre-Alain Francis Claude Sebrecht
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Patent number: 11444543Abstract: An electrical power module comprising power components and supports, each including at least one metal portion, the metal portions of the supports forming a substrate of the electrical power module, at least one support comprising two angled metal portions that are angled relative to each other at an angle that is greater than 0°, each power component being fastened to two metal portions of two distinct supports by being positioned between said two metal portions, the electrical power module being arranged in such a manner that electrical power currents going to or coming from the power components flow in the metal portions of the supports.Type: GrantFiled: November 16, 2018Date of Patent: September 13, 2022Assignee: SAFRAN ELECTRONICS & DEFENSEInventors: Jean-Christophe Riou, Eric Bailly, Nawres Sridi-Convers
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Patent number: 11441779Abstract: The provision of air passage holes through a wall of a gas turbomachine combustion chamber. Multi-perforations are virtually positioned and distributed, even in a first safety zone without air passage openings. Multi-perforations with a virtual inlet or outlet in this first security zone are virtually removed. According to certain criteria, at least some of said removed multi-perforations are then virtually reintegrated, and, from then on a perimeter passing through the virtual inlets and outlets of all the multi-perforations present is defined, in the direction of a primary or dilution hole to be installed, a modified safety zone is defined, then, respecting around said hole and with the freedom to reposition it within this limit, the shape of this hole is redefined.Type: GrantFiled: April 16, 2020Date of Patent: September 13, 2022Assignee: Safran Aircraft EnginesInventors: François Pierre Ribassin, Patrice André Commaret, Romain Nicolas Lunel, Christophe Pieussergues
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Publication number: 20220282869Abstract: A fuel injector for an aircraft turbine engine includes a tubular body having an axis of elongation. A first longitudinal end configured to be supplied with fuel and a second longitudinal end configured to eject a jet of fuel. The body further includes an integrated purge-air circuit that has an internal cavity which is connected to air inlet orifices situated on the body and to at least one air outlet situated at said second end. Air-flow disruptors are provided, projecting into said cavity.Type: ApplicationFiled: July 16, 2020Publication date: September 8, 2022Applicant: SAFRAN HELICOPTER ENGINESInventors: Thomas Jean Olivier LEDERLIN, Denis Luc Alain CHANTELOUP, Simon Arthur MEILLEURAT
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Publication number: 20220282625Abstract: 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: ApplicationFiled: June 25, 2020Publication date: September 8, 2022Applicant: SAFRAN AIRCRAFT ENGINESInventors: Tony Alain Roger Joël Lhommeau, Dimitri Germinal Soteras, Clément René Roger Sirot, Alain Laurent Christian Vitalis
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Publication number: 20220282633Abstract: An abradable coating for a turbomachine, as well as a turbomachine module and a turbomachine including such an abradable coating, the abradable coating including, with a content of greater than 50% by volume, an inorganic compound whose Mohs hardness is less than 6 and whose melting temperature is greater than 900° C.Type: ApplicationFiled: July 22, 2020Publication date: September 8, 2022Applicant: SAFRAN AIRCRAFT ENGINESInventors: Guillaume FRADET, Laurent Paul DUDON, Serge Georges Vladimir SELEZNEFF
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Publication number: 20220281589Abstract: An aircraft landing gear assembly having a reinstating geometry in which a lock link can be moved to assume a first locking condition to inhibit movement of a stay when a main strut is in a deployed condition and a second locking condition to inhibit movement of the main strut when in a stowed condition. An unlock actuator is coupled between a first element of the stay and the lock link such that the actuator can break the lock link from the first locking condition and force it to assume the second locking condition by operational force in a single direction.Type: ApplicationFiled: May 23, 2022Publication date: September 8, 2022Applicant: Safran Landing Systems UK LTDInventor: Ian Robert Bennett
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Publication number: 20220282408Abstract: A weaving installation includes a loom that receives a series of strands, and at least one device for measuring the diameter of a strand having a defined number of filaments. The device includes a diaphragm having an external ring forming a support on which a series of strips forming an iris are fixed. The strips are movable and allow a substantially circular space with variable dimensions to be defined at the center of the iris. The diaphragm is configured to adjust the dimensions of the space so as to allow a strand of the loom to pass through it, and to encircle the profile of the strand so as to allow the number of filaments in the strand to be determined.Type: ApplicationFiled: August 20, 2020Publication date: September 8, 2022Applicant: SAFRAN AIRCRAFT ENGINESInventors: François CHARLEUX, Steven Gérard Joseph BIENVENU