Patents Assigned to SAFRAN HELICOPTER ENGINES
  • Patent number: 12291976
    Abstract: A rotor wheel for an aircraft turbine engine has a disc with a main axis and cells at its outer periphery. The cells extend along the axis, and each has a bottom and two side flanks. Vanes are mounted in the cells of the disc, each vane including a blade connected by a platform to a root mounted in one of the cells. Each root includes, at its radially inner end, a lobe with a first axial end having a circumferential notch and a second axial end having a radially inward facing stop configured to axially bear on a first face of the disc. An annular ring engages the notches of the vanes and is axially clamped against a second face of the disc. Each lobe has a radially inward facing projecting bulb configured to radially bear on the surface of the bottom of the corresponding cell.
    Type: Grant
    Filed: May 31, 2022
    Date of Patent: May 6, 2025
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Jean-Luc Breining, Denis Daniel Jean Boisseleau, Thomas Gabriel Elie Gatteau, Yvan Ludovic Lameignere
  • Patent number: 12286926
    Abstract: Aircraft turbomachine including a centrifugal compressor, a combustion chamber, the combustion chamber being supplied by the compressor via a diffuser and via a straightener, and a heat exchanger, the exchanger including a first circuit, supplied with exhaust gas from the turbomachine, and a second circuit, which are connected by volutes on the one hand to an outlet of the diffuser and on the other hand to an inlet of the straightener, the volutes having reversed winding directions such that their connection ports to the exchanger are independent of one another and are substantially diametrically opposed, and such that the minimum cross section of each duct is situated at a larger cross section of the other duct.
    Type: Grant
    Filed: June 15, 2021
    Date of Patent: April 29, 2025
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Bernard Claude Pons, Alphonse Puerto, Laurent Pierre Tarnowski, Lois Pierre Denis Vive
  • Patent number: 12264637
    Abstract: The invention relates to a propulsion system (1, 1) for an aircraft, comprising a rotor (2) and a nacelle failing (3) that extends around said rotor in relation to an axis (X) and includes an upstream portion (10) forming an inlet section (BA) of the nacelle fairing (3) as well as a downstream portion (20), a downstream end (21) of which forms an outlet section (BF) of the nacelle fairing (3); and characterized in that the downstream portion (20) has a radially inner wall (20a) and a radially outer wall (20b), both of which are made of a deformable shape memory material, and in that the downstream end (21) includes pneumatic or hydraulic actuators (23, 23?) extending in different consecutive angular sectors about said axis (X), each actuator being independently actuatable and being configured to deform, in a direction that extends radially in relation to said axis (X) and is centered angularly in relation to its angular sector, under the effect of a predetermined control pressure.
    Type: Grant
    Filed: October 12, 2020
    Date of Patent: April 1, 2025
    Assignees: SAFRAN, SAFRAN HELICOPTER ENGINES
    Inventors: Jean-Louis Robert Guy Besse, Ye-Bonne Karina Maldonado
  • Patent number: 12264628
    Abstract: A liquid fuel supply system for an aircraft engine includes a fuel tank, a suction duct connected to the fuel tank and located higher than the fuel tank, an electric pump, a supply pump that is mechanically driven by an accessory gear box and an outlet of the supply pump being connected to a fuel supply circuit of the engine, and an air expulsion drain. The electric pump is in communication with the suction duct independently of the supply pump, the electric pump is in communication with the air expulsion drain, and the supply pump is in communication with the suction duct independently of the electric pump.
    Type: Grant
    Filed: April 13, 2022
    Date of Patent: April 1, 2025
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Philippe Jean René Marie Benezech, Alexis Thomas Valentin Longin, Pierre Anthony Sicaire, Gabriel Darrieumerlou
  • Patent number: 12252261
    Abstract: A hybrid propulsion unit for an aircraft with multi-rotor rotary wings includes an electrical generator driven by an internal combustion engine, a rectifier configured to convert an AC current sent by the electrical generator into DC current, a DC-AC converter, an electrical network connecting the rectifier to the converter and including a high-voltage DC current bus, electric motors powered by propeller converters coupled to the electric motors, electrical energy storage connected to the electrical network, the electrical storage including at least one primary storage element and at least one secondary storage element.
    Type: Grant
    Filed: March 30, 2020
    Date of Patent: March 18, 2025
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Thomas Klonowski, Thomas Bruno Barraco
  • Publication number: 20250059918
    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
  • Publication number: 20250034680
    Abstract: The present invention relates to a metal powder for a powder bed additive manufacturing process, the metal powder comprising a nickel-based alloy comprising at least 0.05% carbon, at least 14.25% cobalt, at least 14% chromium, at least 4% aluminium, at least 3.9% molybdenum, at least 3% titanium, at most 0.5% iron, at least 0.012% boron, at most 0.060% zirconium, at most 0.150% manganese, at most 0.2% silicon, at most 0.1% copper, at most 0.5 ppm bismuth, at most 5 ppm silver, at most 5 ppm lead, at most 25 ppm sulphur, at most 200 ppm oxygen, and at most 60 ppm nitrogen.
    Type: Application
    Filed: December 5, 2022
    Publication date: January 30, 2025
    Applicants: SAFRAN AIRCRAFT ENGINES, SAFRAN HELICOPTER ENGINES
    Inventors: Hugo Jean-Louis SISTACH, Stéphane LAVIGNOTTE, Cédric Pierre Jacques COLAS, Romaric Jean-Marie PIETTE
  • Patent number: 12208912
    Abstract: Propulsion system for a helicopter comprising a main engine, a main rotor, a main gearbox including an output mechanically connected to the main rotor, a reduction gearbox mechanically coupled between the main engine and a first input of the main gearbox, and an assistance device. The assistance device comprises a first electric machine mechanically coupled to the reduction gearbox and configured to operate as an electric generator to take off energy produced by the main engine, and a second electric machine mechanically coupled to a second input of the main gearbox, the second electric machine being supplied with electrical power by the first electric machine and configured to operate as an electric motor to deliver additional mechanical power to the main gearbox.
    Type: Grant
    Filed: December 3, 2021
    Date of Patent: January 28, 2025
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Romain Jean Gilbert Thiriet, Fabien Mercier-Calvairac, Stéphane Albert André Douillard
  • Patent number: 12208911
    Abstract: A propulsion unit having a propeller for an aircraft including a nacelle; a propeller mounted in the nacelle so as to be capable of rotating about a longitudinal axis of rotation, the propeller having blades mounted by a root so as to be capable of pivoting between a deployed position, in which they extend radially relative to the axis of rotation, and a folded position, in which they are longitudinally received against the nacelle; drive means that rotate the propeller; indexing means for stopping the propeller in at least one indexed angular position (? i) relative to the nacelle; the propulsion unit wherein the indexing means consist of a stepping electric motor including a rotor that is coupled to the propeller.
    Type: Grant
    Filed: June 10, 2021
    Date of Patent: January 28, 2025
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Jean-Louis Robert Guy Besse, Camel Serghine
  • Patent number: 12208576
    Abstract: A process for three-dimensional printing of a workpiece (10), comprising a succession of steps for producing a layer (18) of the workpiece (10) by means of a nozzle (28) which has an output cross-section along a path (32) of the nozzle (28), wherein, during at least one step for producing a layer (18), use is made of at least one nozzle (28), an output portion (42) of which has an output cross-section which is variable between a first maximum cross-section and a second minimum cross-section, and wherein the cross-section of at least one part of an output portion (42) of the nozzle is varied along at least one portion (32a, 32b) of the path (32).
    Type: Grant
    Filed: May 20, 2020
    Date of Patent: January 28, 2025
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventor: Laurent Chares
  • Publication number: 20250027426
    Abstract: A device for controlling an airflow guiding system comprising: at least one vane movable in rotation about an axis of rotation between a first angle and a second angle, an actuator comprising a body inside which a piston is mounted in translation secured to an actuation rod, and a control rod comprising a downstream end connected to the axis of the vane, the actuator being configured to drive the control rod in movement between a first end position and a second end position of a nominal operating range and, in the event of breakdown of said device, to perform an over-stroke of the actuation rod into a safety position. The device comprises a drive mechanism linking an upstream end of the actuation rod to an upstream end of the control rod, opposite to the downstream end.
    Type: Application
    Filed: December 2, 2022
    Publication date: January 23, 2025
    Applicant: SAFRAN HELICOPTER ENGINES
    Inventors: Thibaut Maxime Javoy, Christophe Boris Baucheff
  • Patent number: 12203417
    Abstract: Disclosed is a turbomachine, comprising a gas generator (13) equipped with a first shaft (18), at least one reversible electrical machine (11), a free turbine (12) provided with a second shaft (17) and caused to rotate by a gas flow generated by the gas generator (13), an accessory gear box (14) and at least one accessory (15, 16). Said at least one electrical machine (11) is mechanically coupled to said second mechanical shaft (17) via the accessory gear box (14) during all phases of operation of the turbomachine (10), the accessory gear box (14) is coupled to the at least one accessory (15, 16) and the turbomachine (10) further comprises a single mechanical coupling means (20) for mechanically coupling said first mechanical shaft (18) to the accessory gear box (14) in a first configuration and mechanically uncoupling said first mechanical shaft (18) from the accessory gear box (14) in a second configuration.
    Type: Grant
    Filed: October 21, 2021
    Date of Patent: January 21, 2025
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Loïs Pierre Denis Vive, Thomas Drouin, Olivier Bedrine
  • Patent number: 12168520
    Abstract: A system (11) for balancing at least one parameter to be balanced of an electric motor of a propulsion system (1), in particular of an aircraft, includes at least two electric motors (3, 4) and a propulsion member (2) driven in rotation by said electric motors. The balancing system is configured to calculate a correction of the speed setpoint (Corr_Cons_VI, Corr_Cons_V2) as a function of a correction factor (F1, F2) of the speed setpoint depending on a parameter (P1, P2) of the associated electric motor that is intended to be balanced and on a speed setpoint (Cons_VH) of the propulsion member (2).
    Type: Grant
    Filed: December 9, 2020
    Date of Patent: December 17, 2024
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: David Lemay, Jean-Philippe Jacques Marin
  • Publication number: 20240413722
    Abstract: A rotor of an aircraft electric motor includes a shaft made of a first material, and a conductive assembly made of a second material different from the first material. The shaft includes a shoulder portion, the shoulder portion includes longitudinal notches. The notches include two contiguous notches radially superimposed in the shoulder portion, a first opening on a radially outer face of the shoulder portion, and a second opening connecting the two contiguous notches. The conductive assembly is a one-piece structure including a conductive bar that is positioned in one notch of the notches, and a skin that is fixed on the shoulder portion.
    Type: Application
    Filed: September 14, 2022
    Publication date: December 12, 2024
    Applicant: SAFRAN HELICOPTER ENGINES
    Inventors: Camel SERGHINE, Thomas KLONOWSKI
  • Publication number: 20240372448
    Abstract: A rotor of an aircraft electric motor includes a shaft made of a first material, and a skin made of a second material different from the first material. The skin includes two half-shells welded together, each half-shell of the two half-shells including a chamfer, and the chamfers assembling the two half-shells together. The shaft includes a shoulder portion the skin being fixed on the shoulder portion. The rotor further includes an interpenetration layer of the first material and of the second material, the interpenetration layer including an alloy of the first material and an alloy of the second material, the interpenetration layer being between the shaft and the skin.
    Type: Application
    Filed: September 14, 2022
    Publication date: November 7, 2024
    Applicant: SAFRAN HELICOPTER ENGINES
    Inventors: Camel SERGHINE, Thomas KLONOWSKI
  • Publication number: 20240353250
    Abstract: The invention relates to a sensor (1) for determining a liquid level (NE) for an aircraft tank (100), the determining sensor (1) comprising a closure device (2) for closing a port (101) of the tank (100) and a measuring device (3), removably mounted on the closure device (2), comprising a liquid line (20) configured to convey liquid from the port (100) of the tank (100), and a member (21) for automatically sealing the liquid line (20) if the measuring device (3) is not mounted on the closure device (2), the measuring device (3) comprising at least one pressure measuring member (30) configured to measure a pressure difference between the liquid pressure (P1) in the liquid line (20) and a reference pressure (P2) in order to deduce the liquid level (NE) thereof.
    Type: Application
    Filed: July 27, 2022
    Publication date: October 24, 2024
    Applicant: SAFRAN HELICOPTER ENGINES
    Inventors: Antoine Pascal MOUTAUX, Olivier ROBERT
  • Patent number: 12116904
    Abstract: Disclosed is a movable vane (1) for a wheel (2) of an aircraft turbine engine, the vane (1) comprising a blade (4) delimited by an outer heel (8) comprising a first seal (14), the vane (1) comprising an internal circuit (16) suitable for receiving a first minor gas flow (f1), this circuit (16) comprising a supply cavity (17) opening at the root (9) via at least one inlet opening (18), characterised in that the circuit (16) comprises at least two channels (19) connected with the supply cavity (17) and each opening on an outer surface of the first seal (14) via a discharge opening such that a gas jet (J) of the first minor gas flow (f1) is capable of being discharged from each discharge opening, each channel (19) being oriented such that the corresponding gas jet (J) is capable of being projected towards a second minor gas flow (f2) escaping between the heel (8) and a directly adjacent member (22).
    Type: Grant
    Filed: July 29, 2020
    Date of Patent: October 15, 2024
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Bertrand Guillaume Robin Pellaton, Lucas Benassis
  • Publication number: 20240336367
    Abstract: A turboprop includes a propeller, a propeller shaft carrying the propeller, the propeller being a variable-pitch propeller having a propeller pitch, a rotating electric machine having at least a first configuration in which it is mechanically coupled to the propeller shaft and at least one oil pump configured to supply a hydraulic circuit for adjusting the pitch of the propeller. The oil pump is configured to be electrically operated. An aircraft can include such a turboprop and methods can control such a turboprop and such an aircraft.
    Type: Application
    Filed: August 2, 2022
    Publication date: October 10, 2024
    Applicant: SAFRAN HELICOPTER ENGINES
    Inventors: Lucie Stéphanie APOSTIN, Didier Claude CHARTRAIN, Jean-Michel PRESSE
  • Patent number: 12110128
    Abstract: A device for a hybrid aircraft including a turboshaft engine having a gas generator, a free turbine, and a main rotor. The device includes a first reversible electric machine coupled to a shaft of the free turbine by way of a first free wheel, and to the main rotor. The device further includes a second reversible electric machine coupled to a shaft of the gas generator by way of a second free wheel, and coupled to the main rotor by way of a third free wheel. The second free wheel activates when the second electric machine rotates in a first direction of rotation, and the third free wheel activates when the second electric machine rotates in a second direction of rotation opposite to the first direction of rotation.
    Type: Grant
    Filed: April 25, 2022
    Date of Patent: October 8, 2024
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Benjamin Nicolas Fulleringer, Antoine Pascal Moutaux, Romain Jean Gilbert Thiriet
  • Publication number: 20240328617
    Abstract: A longitudinal-axis (X) dihydrogen injection device is configured to be mounted on an annular bottom of an annular combustion chamber of a turbomachine. The injection device includes an inner channel for dihydrogen circulation and an outer annular channel for circulation of a mixture of at least air. The inner channel and the outer annular channel are coaxial. An inner swirler is housed in the inner channel and an outer swirler is housed in the outer annular channel. A downstream end of the inner channel is arranged upstream, at a distance r, from a downstream end of the outer annular channel. With this dihydrogen combustion, polluting carbon emissions such as carbon monoxide, unburned hydrocarbons or even fine and smoke particles can be eliminated.
    Type: Application
    Filed: October 5, 2022
    Publication date: October 3, 2024
    Applicants: CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE, SAFRAN HELICOPTER ENGINES, UNIVERSITE TOULOUSE III - PAUL SABATIER
    Inventors: Stéphane Raphaël Yves RICHARD, Christophe Nicolas Henri VIGUIER, Sylvain MARRAGOU, Thierry SCHULLER