Patents Assigned to SAFRAN AIRCRAFT ENGINES
  • Patent number: 10981247
    Abstract: A device for the additive manufacturing of a turbomachinery part by direct metal deposition onto a substrate comprising: a source of metallic material; a source of energy configured to produce molten metal from the metallic material produced from the source of metallic material; a substrate; a mold arranged on the substrate and equipped with at least one opening, in order to allow a localized deposition of molten metal onto the substrate, the mold comprising a magnetic material; and a substrate support arranged under the substrate, the support being configured to generate an electromagnetic force allowing the mold to be drawn towards the substrate.
    Type: Grant
    Filed: March 19, 2018
    Date of Patent: April 20, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Hervé Antoine Frédéric Seince, Sébastien Yohann Pouzet
  • Patent number: 10982560
    Abstract: The invention relates to a blade (16), in particular a fan blade, for resurfacing an abradable coating (26) on an internal surface of a turbine engine case (18) intended to surround the blade. The comprises a root (20) and an airfoil (24) having a tip opposite the root, said root comprising a housing (32) for the storage or passage of a polymerisable refill resin. The airfoil comprises longitudinal channels (34), the first ends of said channels being connected to the housing and the opposite ends opening at the aforementioned tip.
    Type: Grant
    Filed: April 10, 2017
    Date of Patent: April 20, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Michael Isemene, Alexandre Branco
  • Patent number: 10984153
    Abstract: A method of determining a maximum acceptable alternating stress at a point of a part subjected to cyclic loading: simulating that the part is subjected to constant loading equal to a threshold value during a level period, and assuming that the part has elasto-viscoplastic behavior; from the results of the simulation, determining a final static stress at the point at the end or after the end of the level period; and for the point under consideration, using a Goodman diagram to determine the maximum acceptable alternating stress, which is determined for a static stress equal to the final static stress; the duration of the level period being equal to the duration of the loading of the testpieces that were used to draw up the Goodman diagram.
    Type: Grant
    Filed: July 19, 2016
    Date of Patent: April 20, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Geoffrey Juan Desmeure, Francois Pierre Michel Comte, Anais Suzanne Amelie Gaubert, Arnaud Cyril Longuet, Marine Laetitia Camille Chevalier, Michael Piers Hansom, Lucie Marie Ida Lanciaux
  • Patent number: 10975716
    Abstract: Assembly forming a labyrinth seal for a turbomachine, comprising: at least one abradable material of which the inner surface defines a stair shape with a sequence of treads and risers; a plurality of fins extending radially toward said inner surface, the fins each comprising, at least in part, an upstream side wall forming a riser facing the corresponding fin such that, when seen in axial cross-section, the tangent at the top of the upstream side wall of at least one fin and the straight line passing through the downstream side wall of said at least one abradable material intersect, the angle between said tangent and said straight line being strictly between 5 and 15°.
    Type: Grant
    Filed: August 23, 2017
    Date of Patent: April 13, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Christophe Scholtes, Antoine Robert Alain Brunet, Wilfried Lionel Schweblen
  • Patent number: 10975725
    Abstract: A turbofan including a low-pressure shaft; a high-pressure shaft; a fan shaft; a reducing mechanism that couples the low-pressure shaft to the fan shaft; and a maximum of six chambers that accommodate the bearings of the low-pressure shaft, the bearings of the high-pressure shaft and the bearings of the fan as well as the reducing mechanism.
    Type: Grant
    Filed: March 15, 2017
    Date of Patent: April 13, 2021
    Assignee: Safran Aircraft Engines
    Inventors: Romain Guillaume Cuvillier, Nils Edouard Romain Bordoni, Michel Gilbert Roland Brault, Jeremy Dievart, Guillaume Patrice Kubiak, Arnaud Nicolas Negri, Nathalie Nowakowski
  • Patent number: 10974837
    Abstract: The invention concerns a propulsion device (1) comprising a torque generator (2) driving an output shaft (3) via a power gearbox (4), the output shaft (3) being rotatably coupled to a thruster (5), said power gearbox (4) being fixed on a frame (7) by means of suspension means (8, 14, 15), said suspension means including hydraulic torque recovery means comprising at least a first hydraulic system (15) and a second hydraulic system (15) spaced from each other, each hydraulic system (15) having a pressure chamber whose volume varies according to the position of the housing (9) of the power gearbox (4) relative to the frame (7), the pressure chambers of the hydraulic systems (15) being connected by a capillary so that a hydraulic fluid is able to flow from one pressure chamber to another via the capillary.
    Type: Grant
    Filed: July 11, 2017
    Date of Patent: April 13, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Geoffroy Marie Gérard Nicq, Nora El Ghannam, Mathieu Jean Jacques Santin
  • Patent number: 10975741
    Abstract: An aircraft twin-spool turbomachine comprises an inter flow compartment (50) housing a fuel tank (54), the exterior of the inter flow compartment being delimited by a cover (52) delimiting the interior of a bypass flow (14b) of the turbomachine, the cover comprising a closable access (64) to a remote lubricant tank filling orifice (74). The turbomachine also comprises: an overflow evacuation orifice (82) located on the tank lower than the lubricant inlet orifice (68); a lubricant overflow evacuation conduit (84) routed downwards from the overflow evacuation orifice (82); a controlled evacuation valve (88), associated with the overflow evacuation orifice (82); and a control device (90, 94) for the evacuation valve (88), the control device being accessible through the access (64).
    Type: Grant
    Filed: June 14, 2019
    Date of Patent: April 13, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventor: Pierrot Guillou
  • Patent number: 10975803
    Abstract: An aircraft comprising a fuselage and a propulsion assembly, the propulsion assembly comprising at least one fan rotor located at the rear of the fuselage in the extension thereof along a longitudinal axis, and a nacelle forming a fairing of the at least one fan rotor into which a flow of air passes. The aircraft also comprises a plurality of radial stator arms mounted upstream of the at least one fan rotor and extending between the fuselage and the nacelle, the radial arms comprising blowing means configured for blowing, into the environment of a trailing edge of the radial arms, an additional air flow adding to the airflow in the extension of the trailing edge.
    Type: Grant
    Filed: July 21, 2016
    Date of Patent: April 13, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Pascal Romano, Mathieu Simon Paul Gruber
  • Patent number: 10975801
    Abstract: An integrated test method for testing the operation of an electrical power converter powered by an on-board power supply network and using field-oriented control to control a three-phase electric motor for a thrust reverser of a turbojet of an aircraft is provided. The method includes: receiving an order to initiate the integrated test; controlling the converter from a current setpoint defined from a non-zero in-phase component and a zero quadratic component; measuring the currents delivered on each of the three outlet phases of said converter; determining in-phase and quadratic components of the three phase currents previously measured; comparing these components with the in-phase and quadratic components of the current setpoint; and sending a notification concerning the malfunctioning or the functioning of the thrust reverser as a function of the result of the comparison.
    Type: Grant
    Filed: August 10, 2017
    Date of Patent: April 13, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventor: Florian Boni Seka
  • Patent number: 10975722
    Abstract: The invention relates to a guide vane intended to be arranged in all or part of an air flow of an aircraft bypass turbomachine fan, the vane comprising an aerodynamic part equipped with at least one interior lubricant cooling passage delimited in part by an intrados wall and an extrados wall of the vane, there being flow-disturbing lugs, made as one piece with one of the intrados and extrados walls, passing across the passage. According to the invention, in any plane of section passing orthogonally through the lugs, the space defined between these lugs has a geometry defined exclusively by a set of annulus shapes of the same dimensions, partially overlapping one another and each in part delimiting at least two of these lugs.
    Type: Grant
    Filed: May 17, 2018
    Date of Patent: April 13, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Dimitri Daniel Gabriel Marquie, Geoffray Henri Robert Leguery, Pierre François Senejoux
  • Patent number: 10975881
    Abstract: A centrifugal impeller having an axis of rotation extending from front to rear, and including a body extending around the axis of rotation, the body having a front portion and a rear portion of larger section than the front portion, the impeller also have blades projecting from a front face of the body, the body presenting a setback in its front face between two consecutive blades, which setback is situated at a circumferential distance from the two blades.
    Type: Grant
    Filed: April 25, 2018
    Date of Patent: April 13, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Sylvain Frederic Avakian, Arnaud Jacques Jean Gascq, Felipe Winston Gomez Moyano, Damien Bernard Emeric Guegan
  • Patent number: 10975720
    Abstract: The invention relates to a balancing system of an aircraft turbomachine comprising a first annular row of first mounting ports for mounting balancing members, and a second annular row of second mounting ports for mounting balancing members which is axially offset from the first annular row, the number and angular positions of the first mounting ports being identical to the number and angular positions of the second mounting ports.
    Type: Grant
    Filed: July 31, 2019
    Date of Patent: April 13, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Nadège Pauline Audrey Hugon, Thomas Giraudeau, Jean-Marc Claude Perrollaz, Baptiste René Roger Batonnet, Romain Nicolas Lagarde
  • Patent number: 10967430
    Abstract: A method for heat treating a powder part preform including a titanium alloy, includes heat treating the preform in a furnace at a predefined temperature, wherein the preform is on a holder during the heat treatment. The holder includes a titanium alloy having a mass titanium content no lower than 45%, or a zirconium alloy having a mass zirconium content no lower than 95%, wherein the material making up the holder has a melting temperature higher than the predefined heat treatment temperature, and an antidiffusion barrier is arranged between the preform and the holder to prevent the preform from becoming welded to the holder.
    Type: Grant
    Filed: July 6, 2016
    Date of Patent: April 6, 2021
    Assignees: SAFRAN AIRCRAFT ENGINES, ALLIANCE
    Inventors: Guillaume Fribourg, Jean-Claude Bihr, Clément Gillot
  • Patent number: 10968779
    Abstract: A method for unscrewing a link nut of an HP rotor of a twin-spool turbine, including a front fan, an intermediate casing, a HP module with a HP rotor, and a LP turbine module, the intermediate casing including a support bearing for the HP rotor, the rotor being retained in the bearing by the link nut, the method including: placing an unscrewing tool in front of the link nut after having removed the fan and released access to the nut from the front; with rotation of the HP rotor locked and the frontal unscrewing tool including a socket spanner including teeth having a shape that complements that of teeth of the link nut, attaching a mounting for the socket spanner to the intermediate casing, the socket spanner being rotatably mounted on the mounting, and applying an unscrewing torque to the socket spanner. An unscrewing tool implements the method.
    Type: Grant
    Filed: April 12, 2018
    Date of Patent: April 6, 2021
    Assignee: Safran Aircraft Engines
    Inventors: Fabrice Tailpied, Michel Bertin, Jean-Michel Couture, Herve Dagron, Roland Manchon, Cedric Mustiere
  • Patent number: 10967980
    Abstract: An airplane propelled by a turbine engine having at least one fan, the turbine engine being integrated in the rear of a fuselage of the airplane, extending it rearwards, the airplane further including at least one acoustic baffle forming panel connected to the fuselage of the airplane and arranged below the turbine engine.
    Type: Grant
    Filed: November 21, 2016
    Date of Patent: April 6, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Norman Bruno Andre Jodet, Jeremy Paul Francisco Gonzalez, Herve Rolland
  • Patent number: 10968770
    Abstract: A gas turbine engine includes a fan driven by a fan shaft and retractable axial retainer of the shaft mounted on a stator element and movable between a first operational position and a second non-operational position. The retractable axial retainer may include a fluid supply configured for supplying at least one cavity with fluid. In some examples, the retractable axial retainer is mounted movably or slidingly so as to generate movement of the retractable axial retainer between the operation and non-operational positions.
    Type: Grant
    Filed: September 25, 2018
    Date of Patent: April 6, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Julien Fabien Patrick Becoulet, Michel Gilbert Roland Brault, Romain Guillaume Cuvillier, Arnaud Nicolas Negri
  • Patent number: 10967460
    Abstract: A method of fabricating a part includes: a) supplying powder particles; b) melting a first quantity of power with a beam and forming, on a support, a first pool including the melted powder and a portion of the support; c) forming a second pool by melting a second quantity of powder on the support; d) repeating c) to form a first layer; e) heating an [n]th quantity of the powder, and forming an [n]th pool above the first layer; f) heating an [n+1]th quantity of the powder, and forming an [n+1]th pool downstream from the [n]th pool above the first layer; g) repeating f) to form a second layer above the first layer; and h) repeating e) to g) until the part is constructed. The powder particles reaching each pool are at a temperature well below the pool temperature.
    Type: Grant
    Filed: November 29, 2013
    Date of Patent: April 6, 2021
    Assignees: SAFRAN AIRCRAFT ENGINES, MBDA FRANCE
    Inventors: Christophe Colin, Julie Maisonneuve, Gérard Saussereau
  • Publication number: 20210095618
    Abstract: An aircraft turbine engine having a primary air flow path with a low-pressure and a high-pressure compressors, a secondary air flow path with vanes and decks between vanes, each of the decks being located between the inner radial ends or between the outer radial ends of two adjacent vanes, each deck having a wall partially delimiting the secondary path. A pressurized air circuit draws air between the low-pressure compressor and the high-pressure compressor or in the high-pressure compressor and supplies at least one turbine engine component located near a main axis of the turbine engine. The pressurized air circuit includes a heat exchanger between the pressurized-air stream and the air stream flowing in the secondary path. The heat exchanger is formed by at least one deck through which the pressurized air flows, the wall of the deck performing the heat transfer between the pressurized air and the air stream flowing in the secondary path.
    Type: Application
    Filed: February 18, 2019
    Publication date: April 1, 2021
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Catherine PIKOVSKY, Christophe Marcel Lucien PERFRIGEON, Cedric ZACCARDI
  • Patent number: 10961856
    Abstract: A ceramic core used for fabricating a hollow turbine blade for a turbine engine by using the lost-wax casting technique and shaped to constitute the cavities of the blade as a single element, includes, in order to feed the insides of these cavities jointly with cooling air, core portions that are to form first and second lateral cavities and that are connected to a core portion that is to form at least one central cavity, firstly in the core root via at least two ceramic junctions, and secondly at various heights up the core via a plurality of other ceramic junctions of positioning that defines the thickness of the internal partitions of the blade, while also ensuring additional cooling air for predetermined critical zones of the first and second lateral cavities.
    Type: Grant
    Filed: March 22, 2016
    Date of Patent: March 30, 2021
    Assignees: SAFRAN AIRCRAFT ENGINES, SAFRAN
    Inventors: Sylvain Paquin, Charlotte Marie Dujol, Patrice Eneau, Hugues Denis Joubert, Adrien Bernard Vincent Rollinger
  • Patent number: 10960613
    Abstract: A fiber texture presents the shape of a strip extending in a longitudinal direction over a determined length between a proximal portion and a distal portion, and in a lateral direction over a determined width between first and second lateral edges. The fiber texture presents three-dimensional or multilayer weaving. The proximal portion of the fiber texture includes an end portion extending in the lateral direction so as to be set back from at least one of the first and second lateral edges and over a determined width that is less than the width of the fiber texture. The end portion projects in the longitudinal direction from at least one longitudinal edge of the fiber texture, the end portion extending in the longitudinal direction between a first end connected to the fiber texture and a free, second end opposite from the first end.
    Type: Grant
    Filed: May 24, 2018
    Date of Patent: March 30, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Jérémy Hellot, Sylvain Corradini, Hubert Jean Marie Fabre