Patents Assigned to SAFRAN AIRCRAFT ENGINES
  • Publication number: 20240189908
    Abstract: A method for manufacturing a metal alloy part for an aircraft turbine engine, the method including the steps of: (a) producing a blank of the part by additive manufacturing by laser fusion on a powder bed, and (b) abrasively machining the blank to obtain the part, the machining being carried out by vibratory finishing by immersing the blank in an abrasive composition contained in a tank subjected to a vibratory movement, the abrasive composition having an abrasive element formed by alumina particles, a carrying element formed by copper particles, and a liquid.
    Type: Application
    Filed: March 21, 2022
    Publication date: June 13, 2024
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Arnaud TUREL, Mickaël VOIRON
  • Patent number: 12005666
    Abstract: A verification method for verifying whether the aerodynamic profile of a real blade for an aircraft turbine engine complies with a theoretical blade, the method including constructing a camber line of the theoretical blade and constructing a camber line of the real blade; constructing a relationship for the thickness of the theoretical blade and constructing a relationship for the thickness of the real blade, the thickness relationship of a blade corresponding to the curve plotting the thickness of the blade as a function of curvilinear length along the camber line from a leading edge of the blade to a trailing edge of the blade, where thickness is the dimension of the blade extending perpendicularly to the camber line at each point of the camber line; superposing the thickness relationship of the real blade on the thickness relationship of the theoretical blade; and extracting the leading-edge and trailing edge thicknesses.
    Type: Grant
    Filed: August 7, 2020
    Date of Patent: June 11, 2024
    Assignees: SAFRAN AERO COMPOSITE, SAFRAN AIRCRAFT ENGINES, SAFRAN AEROSPACE COMPOSITES
    Inventors: Damien Vincent Le Cloarec, Clement Giacovelli, Jeffrey Steven Sherman, Mickaelle Lucie Alicia Thomas
  • Patent number: 12006877
    Abstract: Method for controlling a first, a second and a third variable of a turbomachine as a function of a first, a second and a third control quantity of a turbomachine which can each be saturated as a function of the operating parameters of the turbomachine. The method comprises a first multivariable correction (120) delivering a first value for the three control quantities, a selection (130) of the first control quantity to be delivered as a function of a minimum value, of a maximum value and of the value determined by the first correction, a second multivariable correction (140) delivering a second value for the second and third control quantities, and a selection (150) of the values of the second and third control quantities to be delivered in the values determined during the first correction and those determined during the second correction.
    Type: Grant
    Filed: March 18, 2020
    Date of Patent: June 11, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Typhaine Raslain, Christophe Marc Alexandre Le Brun, Sylvain Clermonte
  • Patent number: 12006841
    Abstract: The present invention relates to a fan blade of a turbomachine comprising a structure made of composite material comprising a fibrous reinforcement obtained by three-dimensional weaving of strands and a matrix in which the fibrous reinforcement is embedded, which comprises a first portion forming the suction-side wall and a second portion forming the pressure-side wall, the strands of the fibrous reinforcement comprising first strands comprising carbon or aramid fibres, the Young's modulus of which is greater than 250 GPa, and second strands produced from a viscoelastic material and having a Young's modulus less than 10 GPa, the first portion comprises uniquely first strands whereas the second portion comprises second strands.
    Type: Grant
    Filed: August 31, 2021
    Date of Patent: June 11, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Clément Pierre Postec, Thomas Alain De Gaillard, Guillaume Pascal Jean-Charles Gondre, Pierre-Antoine Gérard Joseph Barbier
  • Patent number: 12006844
    Abstract: The invention relates to a blade pivot with adjustable orientation for a turbomachine fan hub, comprising a stud having means for retaining a fan blade root and coupling means for the transmission of a torsional torque, a rolling bearing for absorbing the centrifugal forces having an inner bushing mounted in transverse abutment against an external radial portion of the stud, a ring for radially retaining the stud relative to the rolling bearing housed in an annular groove formed in the stud, a plurality of clamping parts each mounted in transverse abutment against the retaining ring and in radial abutment against the inner bushing of the rolling bearing, and a clamping nut screwed onto an outer thread of the stud to come into conical abutment against the clamping parts such that said clamping parts ensure a clamping of the inner bushing of the rolling bearing on the stud and a clamping.
    Type: Grant
    Filed: December 3, 2020
    Date of Patent: June 11, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Vincent François Georges Millier, Olivier Belmonte
  • Patent number: 12000298
    Abstract: A device for pressurizing a turbomachine downstream enclosure, the device being fed by means of a pressurizing air flow and including: a first shaft portion, a second shaft portion coupled to the first shaft portion via internal splines and external splines and extending, at a distance, inside the first shaft portion. The device includes at least a first passage made through the splines, and at least one orifice passing right through the second shaft portion, the orifice being arranged upstream of the first passage, in fluidic communication with the first passage, and opening out inside the second shaft portion so as to allow the pressurizing air flow to circulate from the first passage, between the first and second shaft portions, towards the downstream enclosure.
    Type: Grant
    Filed: October 22, 2021
    Date of Patent: June 4, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Maeva Daphne Gros-Borot, Clementine Charlotte Marie Mouton
  • Patent number: 12000344
    Abstract: An aircraft turbine engine includes a turbine shaft having a first axis of rotation, a propulsion propeller having a second axis of rotation parallel to and spaced from the first axis, and a mechanical reduction gear coupled to the turbine shaft and rotating the propeller. The reduction gear has a sun gear connected to the turbine shaft, a ring gear, and at least two planet gears, each including a first external toothing that is meshed with an external toothing of the sun gear. A second external toothing is located within the ring gear and is meshed with an internal toothing of the ring gear.
    Type: Grant
    Filed: September 16, 2022
    Date of Patent: June 4, 2024
    Assignees: SAFRAN AIRCRAFT ENGINES, SAFRAN TRANSMISSION SYSTEMS
    Inventors: Paul Ghislain Albert Levisse, Julien Fabien Patrick Becoulet, Guillaume Pierre Mouly, Patrice Jocelyn Francis Gedin, Olivier Belmonte
  • Patent number: 12000290
    Abstract: Method for controlling a clearance between the tips of the blades of a rotor of an aircraft engine turbine and a turbine ring, comprising the estimation of the clearance to be controlled and the control of a valve delivering an air stream directed towards the turbine ring based on the thus estimated clearance, this method comprising: the detection of a transient acceleration phase based on at least one parameter representative of the engine; the receipt of a data relating to the altitude of the aircraft; the determination of data representative of the temperature of the rotor during the transient acceleration phase and in steady speed and the calculation of a relative temperature deviation.
    Type: Grant
    Filed: January 4, 2021
    Date of Patent: June 4, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Jérôme Claude George Lemonnier, Damien Bonneau, Cécile Racinet, Antoine Bruno Van Noort
  • Patent number: 12000295
    Abstract: A turbomachine blade is made of composite material formed of woven fibers and embedded in a polymerised resin. The blade includes a root connected by a stilt to a vane which comprises a pressure side and a suction side. At least one anti-wear strip of fabric is located on a surface of the root and/or the stilt. At least one anti-wear strip is secured to the root surface in a unitary manner by the resin.
    Type: Grant
    Filed: April 1, 2021
    Date of Patent: June 4, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Matthieu Patrick Jean Roger Perlin, Nicolas François Paul Broussais-Colella, Damien Vincent Le Cloarec, Ambroise Nicolas Marie Malfroy
  • Patent number: 12000414
    Abstract: The invention concerns a method for controlling a mechanism (10) displaying asymmetrical behaviour, the mechanism (10) comprising a first operating direction (F+) and a second operating direction (F?), the control method making it possible to generate, using a control module (24) of a computer (20), a control signal (x_com) from a setpoint signal (x_cons), in which—when the setpoint signal (x_cons) indicates that the mechanism (10) should be operated in the first direction (F+), the control module (24) applies a first corrector (100) to the setpoint signal (x_cons) in order to generate a control signal (x_com),—when the setpoint signal (x_cons) indicates that the mechanism (10) should be operated in the second direction (F?), the control module (24) applies a second corrector (100) to the setpoint signal (x_cons) in order to generate a control signal (x_com), and in which the first and second correctors (100, 200) have different parameters (Kp1, Kp2, Ti1, Ti2), in order to compensate for the asymmetrical beha
    Type: Grant
    Filed: December 17, 2019
    Date of Patent: June 4, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Christophe Marc Alexandre Le Brun, Sébastien Jean Fernand Deneuve
  • Patent number: 12000303
    Abstract: The invention relates to a fan blade (3) made of composite material the fibrous reinforcement of which comprises first strands (12) having a first stiffness, second strands (13) having a second stiffness and third strands (14) having a third stiffness lower than the first stiffness and greater than the second stiffness, the blade comprising a first portion (15) comprising only first strands (12), a second portion (16) comprising only second strands (13) and a third portion (17) which is located between the first and second portions (15, 16) and which comprises both first, second and third strands (12, 13, 14); there is a gradual transition of properties at the interface between the different portions (15, 16, 17).
    Type: Grant
    Filed: November 29, 2021
    Date of Patent: June 4, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Carole Onja Rakotoarisoa, Teddy Fixy, Guillaume Pascal Jean-Charles Gondre, Julien Paul Schneider-Die-Gross
  • Patent number: 12002298
    Abstract: A system for aircraft maintenance is disclosed, such as for monitoring parts mounted in a turbojet engine, the turbojet engine being accommodated in a nacelle compartment delimited by a nacelle wall. The system can verify parts, each of the parts being equipped with an RFID tag. The verification system includes an inner antenna accommodated in the nacelle compartment, the inner antenna being arranged to allow the exchange of radio frequency signals with each RFID tag, an interface device including an access point located outside the nacelle compartment, the interface device being arranged to be able to be connected to an interrogator device arranged to communicate with the RFID tag, and a transmission line connecting the interface device to the inner antenna.
    Type: Grant
    Filed: July 24, 2019
    Date of Patent: June 4, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Tony Alain Roger Joel Lhommeau, Guillaume Philippe Camille Bastard, Hervé Jean Albert Mouton, Philippe Roger Jacques Canteau
  • Patent number: 12000294
    Abstract: The invention concerns a bypass turbomachine (1) with a primary flow path and a secondary flow path, comprising: —a low-pressure body comprising a low-pressure compressor (120) connected to a low-pressure turbine (122) via a low-pressure shaft (124), —a high-pressure body comprising a high-pressure compressor (130) connected to a high pressure turbine (132), via a high-pressure shaft (134), —a low-pressure power take-off system (220) comprising an electrical generator (226), configured to take power (W12) from the low-pressure body, wherein—the turbomachine comprises a debris removal system (500), located between the two compressors (226, 236), —the low-pressure power take-off system (220) is configured to take power (W12) from the low-pressure shaft (124) using the resistive torque of the electrical generator (226), in order to avoid a risk of surging.
    Type: Grant
    Filed: March 18, 2020
    Date of Patent: June 4, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Nicolas Bertrand Georges De Blois, Clément Dupays
  • Publication number: 20240175363
    Abstract: The present invention relates to a vane (7) of a turbine engine, comprising: —a structure which has an aerodynamic profile (20); —a spar (21) comprising a vane root portion (24), a blade portion (25) arranged inside the structure which has an aerodynamic profile (20), and a stilt portion (26), the blade portion (25) comprising a body (27) connected to the vane root portion (24) and two arms extending radially from the body (27); and —a structural reinforcement (31) extending from the vane root portion (24) to the body (27) of the blade portion (25), the structural reinforcement (31) being rigidly connected to the vane root portion (24) and configured to form a force path separate from the stilt portion (26) in the event of failure of the spar (21) within the stilt portion (26).
    Type: Application
    Filed: March 24, 2022
    Publication date: May 30, 2024
    Applicant: Safran Aircraft Engines
    Inventors: Vincent JOUDON, Clément COTTET, Vivien Mickaël COURTIER, Régis Eugène Henri SERVANT
  • Publication number: 20240175378
    Abstract: An upstream part of an air-discharge system for a turbomachine includes: a tube with an upstream end and a downstream end, and an internal tubular structure located inside the tube and configured to form therein a narrowing of its cross section. The internal tubular structure is made in one piece with the tube at the downstream end of the tube and is freely suspended at the upstream end of the tube. A turbomachine with a device for discharging air from the bearing chambers, in which the air is conducted towards the outside of the turbomachine by the air-discharge system is provided. A method for manufacturing the air-discharge system is provided.
    Type: Application
    Filed: March 22, 2022
    Publication date: May 30, 2024
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Patrick Edmond KAPALA, Olivier Pascal Paul CHANTOISEAU
  • Patent number: 11994033
    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.
    Type: Grant
    Filed: November 13, 2020
    Date of Patent: May 28, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventor: Alméric Pierre Louis Garnier
  • Patent number: 11993365
    Abstract: An assembly comprising a propeller blade and its system for angularly adjusting the pitch of the blade including a bowl which is radially delimited by an annular wall extending about an axis for adjusting the pitch of the blade, the bowl having a bottom wall, a free lower end of the root being fitted axially into a complementary housing of the bottom wall in order to rotatably connect the bowl and the blade about the pitch-adjustment axis. The root of the blade comprises a first limiting face that engages with a first abutment face of the bowl to limit the rotation of the blade in the event of breakage of the lower end of the root.
    Type: Grant
    Filed: July 15, 2021
    Date of Patent: May 28, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Clement Cottet, Vivien Mickael Courtier, Vincent Joudon, Regis Eugene Henri Servant, Laurent Jablonski
  • Patent number: 11993408
    Abstract: A bladed disc for masking a moving disc of a jet engine, including blades, each blade including a pressure-side wall and a suction-side wall that meet at a leading-edge and at a trailing edge, and wherein each blade has a pressure-side wall and a suction-side wall each including a concave zone and a convex zone that are at a distance from the leading-edge and from the trailing edge and are spaced apart from one another, these concave zones and these convex zones each extending over the majority of the height of the blade, the concave zone of the pressure-side wall is opposite the convex zone of the suction-side wall, the concave zone of the suction-side wall is opposite the convex zone of the pressure-side wall.
    Type: Grant
    Filed: December 4, 2019
    Date of Patent: May 28, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Michel Dumas, Laurent Christophe Francis Villaines
  • Patent number: 11993032
    Abstract: A mould for manufacturing a turbomachine fan casing made of a composite material with fibrous reinforcement that is densified by a matrix, includes an impregnation mandrel around which a fibrous preform is to be wound and angular counter-mould sectors assembled around the external contour of the impregnation mandrel, which are intended to close the mould. The impregnation mandrel includes a main body with an annular shape, and an annular barrel which is arranged around the main body and around which the fibrous preform is to be wound, the barrel and the angular sectors defining a moulding cavity intended to receive the fibrous preform. The main body and the angular sectors are made of a first material having a first thermal expansion coefficient, the barrel being made of a second material that has a second thermal expansion coefficient, the second thermal expansion coefficient being greater than the first thermal expansion coefficient.
    Type: Grant
    Filed: September 6, 2021
    Date of Patent: May 28, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Maxime Marie Désiré Blaise, Hubert Jean Marie Fabre
  • Patent number: 11994032
    Abstract: An abradable member for a turbomachine turbine, including a cellular structure including walls defining wells which open through a wear face. The cellular structure includes at least one flow straightener jutting from the wear face.
    Type: Grant
    Filed: July 31, 2020
    Date of Patent: May 28, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventor: Julian Nicolas Girardeau