Patents Assigned to SAFRAN HELICOPTER ENGINES
  • Patent number: 11401863
    Abstract: The invention relates to a centrifugal deaerator for an air/oil mixture of a turbomachine, comprising: an annular housing (10) for the centrifugal separation of said mixture, arranged around a hollow shaft (11); axial inlets (14) for the flow of said air/oil mixture into said housing (10); a pinion (20) for rotating said housing (10); and radial oil outlets (15) and oil-free air outlets (16), characterised in that it comprises a metal foam (50) housed in said housing (10) by partially extending along the axial direction (XX?) so as to define two successive spaces, a foam-free space (51) and a foam-lined space (52), said foam-free space opening up towards said axial inlets. A device can be advantageously added to the hollow shaft in order to reduce the free-vortex phenomenon and to thereby significantly reduce the load losses of the deaerator.
    Type: Grant
    Filed: March 7, 2018
    Date of Patent: August 2, 2022
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Jean-Pierre Pajard, Yannick Cazaux, Benjamin Fulleringer
  • Publication number: 20220235665
    Abstract: A turbine vane of a turbine engine is described. The turbine vane includes a blade and a root. The root includes a stilt having lateral flanks with a curvilinear profile. The stilt includes a frangible zone suitable for undergoing a breakage of the stilt if radial forces higher than a threshold are exerted on the vane, in particular centrifugal forces during an overspeed state of the turbine. The frangible zone includes at least one oblong frangibility recess formed on at least one of the lateral flanks of the stilt, the oblong recess extending in an axial direction of the stilt along a longitudinal axis parallel to or included in a minimum cross-sectional plane which contains a minimum cross-section of the stilt.
    Type: Application
    Filed: May 18, 2020
    Publication date: July 28, 2022
    Applicant: SAFRAN HELICOPTER ENGINES
    Inventor: Matthieu Claude Jean Denaux
  • Publication number: 20220235937
    Abstract: The invention relates to a pre-vaporizing pipe (5) for a combustion chamber of a turbomachine, comprising a generally elongate main body (50), comprising a first end portion (51) delimiting an inlet duct (52) in which a fuel injector is to be mounted, the body (50) having an external surface (500) having a first length (L1) that extends from the portion (51) to at least one first fuel outlet end piece (53), and a second length (L2) that extends the first length (L1) from the end piece (53) and that extends from the end piece (53) to a second fuel outlet end piece (54). According to the invention, inside the body (50) there is a first channel (55) connecting the duct (52) to the end piece (53) and a second channel (56) which is distinct from the first channel (55) and which connects the duct (52) to the end piece (54).
    Type: Application
    Filed: May 25, 2020
    Publication date: July 28, 2022
    Applicant: SAFRAN HELICOPTER ENGINES
    Inventors: Nicolas Roland Guy SAVARY, Claude Marie Michel BERAT, Olivier LAMAISON, Yvan Ludovic LAMEIGNERE, Hubert Pascal VERDIER, Chritophe Nicolas Henri VIGUIER
  • Patent number: 11391203
    Abstract: The invention relates to an aircraft propulsion system, comprising a main transmission unit (12) and at least two turbojet engines connected to the main transmission unit (12), respectively a first turbojet engine (14a) and a second turbojet engine (14b), each turbojet engine comprising a free turbine (24a, 24b), characterized in that the first turbojet engine (14a) comprises a heat exchanger (30) configured to recover some of the thermal energy from the exhaust gas at the outlet of the free turbine, and in that the propulsion system comprises at least one computer (28a, 28b) configured to control the two turbojet engines and to limit the acceleration and the deceleration of the first turbojet engine (14a) when neither of the turbojet engines is broken down, in order to limit the reactor power transients at the heat exchanger (30).
    Type: Grant
    Filed: June 7, 2019
    Date of Patent: July 19, 2022
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Olivier Audrey David Lafargue, Thomas Klonowski, Antoine Pascal Moutaux
  • Publication number: 20220213842
    Abstract: A propulsion assembly for aircraft includes a single-shaft engine turbomachine including a combustion chamber and a rotatably mounted shaft that turns at a turbomachine rating; an electrical generator coupled to the shaft; and a control system. The control system includes a fuel pump that brings fuel into the combustion chamber at a fuel flow rate which is a direct function of an ambient pressure and of the turbomachine rating, and power electronics that are coupled to the electrical generator and that control an electrical power drawn off the electrical generator so as to attain a target turbomachine rating.
    Type: Application
    Filed: July 3, 2020
    Publication date: July 7, 2022
    Applicants: SAFRAN HELICOPTER ENGINES, SAFRAN POWER UNITS
    Inventors: Fabien MERCIER-CALVAIRAC, Patrick MARCONI, Denis Antoine Julien REAL
  • Patent number: 11378006
    Abstract: A device for temporarily increasing power in order to increase the power from at least one first turbine engine and from at least one second turbine engine, the device including a tank of coolant liquid, a first injection circuit connected to the tank and leading to at least one injection nozzle configured to be installed upstream from the first turbine engine, a second injection circuit connected to the tank and leading to at least one injection nozzle configured to be installed upstream from the second turbine engine, each of the first and second injection circuits including at least one first valve and at least one second valve arranged upstream from said at least one first valve, and a bridge pipe connecting together the first injection circuit and the second injection circuit upstream from their respective first valves and downstream from their respective second valves.
    Type: Grant
    Filed: March 27, 2018
    Date of Patent: July 5, 2022
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Frédéric Pousse, Lionel Napias, Laurent Minel, Bertrand Moine
  • Publication number: 20220205523
    Abstract: The present invention relates to a pinion for a gear train of an aircraft turbine engine, the pinion comprising: —a cylindrical body (2) extending along an axis and configured to engage with a shaft received in the cylindrical body, —a rim (4) concentric with the cylindrical body, —a web (3) defined axially by a front wall (32) and a rear wall (33) and extending radially from the cylindrical body to the rim, each of the front and rear walls having a density, the pinion comprising a cross-linked structure (5) around the cylindrical body between the front wall and the rear wall, the cross-linked structure comprising a unit cell repeated along three axes of a three-dimensional coordinate system, a density of the unit cell being strictly less than each of the densities of the front and rear walls.
    Type: Application
    Filed: May 15, 2020
    Publication date: June 30, 2022
    Applicant: SAFRAN HELICOPTER ENGINES
    Inventors: Rémi Joseph LANQUETIN, Arnaud Georges NIFENECKER, Antoine LAHITTETE
  • Publication number: 20220204173
    Abstract: An electrical energy supply network of an aircraft equipped with a plurality of electrical loads to be supplied includes at least two generators of a turbogenerator of the aircraft, each suitable for providing an electrical energy source, and at least one stator associated with a rectifier. The stators of the generators are mounted in parallel on at least two distribution buses designed to supply the plurality of electrical loads. The supply network also includes contactors suitable for electrically connecting or disconnecting the distribution buses from each other.
    Type: Application
    Filed: April 23, 2020
    Publication date: June 30, 2022
    Applicant: SAFRAN HELICOPTER ENGINES
    Inventors: Thomas Barraco, Thomas Klonowski, Vincent Poumarede
  • Publication number: 20220190686
    Abstract: An assembly including a winding and a cooler in contact with conductors of the winding, the cooler including a container forming a heat dissipator and including a phase change material having the ability to absorb a surplus quantity of heat when the conductors of the winding are subject to an increase in their current density and the heat dissipator is composed of at least two hollow parts separate and nestable with one another and intended to house the phase change material.
    Type: Application
    Filed: February 19, 2020
    Publication date: June 16, 2022
    Applicants: SAFRAN, SAFRAN HELICOPTER ENGINES
    Inventors: Sabrina AYAT, Camel SERGHINE, Thomas KLONOWSKI
  • Publication number: 20220185497
    Abstract: Methods for controlling an electrical power supply network for an aircraft, include pre-charging at least one capacitor in a normal operating mode when a gas turbine is available, pre-charging the at least one capacitor in a backup operating mode when the gas turbine is not available, and discharging the at least one capacitor at the end of use of the electrical power supply network when the at least one capacitor is charged.
    Type: Application
    Filed: April 10, 2020
    Publication date: June 16, 2022
    Applicant: SAFRAN HELICOPTER ENGINES
    Inventors: Thomas Barraco, Thomas Klonowski, Vincent Poumarede
  • Publication number: 20220185489
    Abstract: A hybrid propulsion system for a vertical take-off and landing aircraft comprising at least one combustion engine driving an electricity generator, at least one electrical energy storage assembly associated with each electricity generator and defining, with each electricity generator, an energy branch, a plurality of electric motors actuating a same plurality of rotors providing together the propulsion and/or the lift of the aircraft, and an electrical power and distribution unit supplying power to the plurality of electric motors from the electricity generator and/or from the electrical energy storage assembly according to a pre-established flight phase, the system including at least two energy branches having an asymmetric configuration and each supplying power selectively, by means of the electrical power and distribution unit, all or part of the plurality of electric motors, and in that the electricity generators of the combustion engines have between them a power ratio comprised between
    Type: Application
    Filed: May 5, 2020
    Publication date: June 16, 2022
    Applicant: SAFRAN HELICOPTER ENGINES
    Inventors: Romain Jean Gilbert THIRIET, Stéphane Meyer BEDDOK
  • Patent number: 11359545
    Abstract: A pyrotechnic device comprising a main pyrotechnic charge, a firing device for firing the main pyrotechnic charge, a discharge passage for discharging the gas generated by firing the main pyrotechnic charge, and an injector device configured to inject a cooling fluid into said gas discharge passage, so as to deliver gas, specifically for driving turbines, at temperatures that are relatively low, and a method of cooling gas generated by firing the main pyrotechnic charge by injecting the cooling fluid.
    Type: Grant
    Filed: November 17, 2017
    Date of Patent: June 14, 2022
    Assignee: Safran Helicopter Engines
    Inventors: François Danguy, Laurent Paul Lattanzio Fabbri, Romain Maurice Henri Yannick Gauthier, Didier Paul Saucereau
  • Publication number: 20220178273
    Abstract: A toothed coupling mechanism for an assembly of rotating elements of an aircraft gas turbine engine includes a pair of coupling halves having an axial toothed coupling interface therebetween. Each coupling half has a plurality of splined teeth inter-engaged about an axis for transmitting torque therebetween. A protrusion is located on one of the splined teeth of one of the coupling halves. A splined tooth of the other coupling half comes into contact with the protrusion in a situation of uncoupling of said coupling halves.
    Type: Application
    Filed: March 11, 2020
    Publication date: June 9, 2022
    Applicant: SAFRAN HELICOPTER ENGINES
    Inventors: Olivier Pierre DESCUBES, Frédéric Ferdinand Jacques BATLLE
  • Publication number: 20220177144
    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: Application
    Filed: March 30, 2020
    Publication date: June 9, 2022
    Applicant: SAFRAN HELICOPTER ENGINES
    Inventors: Thomas Klonowski, Thomas Bruno Barraco
  • Publication number: 20220178311
    Abstract: A method for controlling a non-propulsive power generation turbine engine configured to supply power to a plurality of propulsion rotors of an aircraft, each propulsion rotor being connected to a power distribution module through at least one power supply bus, the turbine engine supplying each power supply bus via the power distribution module at a supply rate, the control method comprising a step of determining the power requirement of each power supply bus depending on the power requirement of each propulsion rotor, a step of determining the basic power requirement of each power supply bus, a step of determining the overall power requirement based on all the basic power requirements of the power supply buses and a step of determining an anticipation parameter based on the overall power requirement.
    Type: Application
    Filed: March 20, 2020
    Publication date: June 9, 2022
    Applicant: SAFRAN HELICOPTER ENGINES
    Inventors: Stéphane Meyer Beddok, Vincent Poumarede
  • Patent number: 11348378
    Abstract: A test specimen for validating operating parameters of a method for the additive manufacturing of a part by laser melting on powder beds includes at least one upper face, at least one lower face and side faces, including a front side face and a rear side face that are substantially on opposite sides from one another. The test specimen has at least one recess opening onto the front and rear side faces, the recess having a substantially triangular cross sectional shape being delimited by three internal faces, including a first lower internal face oriented upwards, a second upper internal face oriented downwards, and a third upper internal face which defines a narrow wall with one other of the side faces, which is inclined.
    Type: Grant
    Filed: March 27, 2018
    Date of Patent: May 31, 2022
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Yann Danis, Alexis Marchand, Aurèle Germain
  • Publication number: 20220166335
    Abstract: Method for monitoring the distribution of power in a hybrid propulsion system comprising one or more electrical sources delivering an AC voltage, each of which is associated with an AC-to-DC controlled rectifier and one or more batteries, wherein, the AC-to-DC controlled rectifier and the battery each being connected directly to an HVDC bus supplying one or more electrical loads with power, the monitoring of the distribution of power is performed through the individual AC-to-DC controlled rectifier by a feedback loop to a power setpoint (Pref) on the basis of a measured power of the battery (Pbat) and a feedback loop to a voltage setpoint (Vref) on the basis of a measured voltage of the HVDC bus (VHVDC), either one of these two feedback loops delivering an RMS current setpoint Idref and Iqref for a feedback loop on the basis of a current (Igen) of the electrical source delivering an AC voltage.
    Type: Application
    Filed: March 20, 2020
    Publication date: May 26, 2022
    Applicants: SAFRAN, SAFRAN ELECTRICAL & POWER, SAFRAN HELICOPTER ENGINES
    Inventors: Garance VINSON, Florent ROUGIER, Stéphane Meyer BEDDOK
  • Patent number: 11333025
    Abstract: A turbomachine blade formed of a hollow airfoil having a leading edge and a trailing edge opposed to each other and connected by an intrados wall and an extrados wall each extending along a radial axis of the blade, between a blade root and a blade tip, and including a cooling circuit supplied with air and delivering air jets ensuring through multiple perforations of the cooling circuit an impingement cooling of the inner surface of the airfoil, the cooling circuit includes superimposed cooling channels over the height of the blade, each integrated into the inner surface of the airfoil while matching its contour, the multiple perforations being drilled in the cooling channels terminating in a purge cavity of the airfoil are able to ensure a purge of the air having impinged the inner surface of the airfoil after its passage through the perforations.
    Type: Grant
    Filed: March 20, 2019
    Date of Patent: May 17, 2022
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Baptiste Hallouin, Jean-Maurice Casaux-Bic, Alexandre Montpellaz, Lionel Renault
  • Patent number: 11333027
    Abstract: A turbomachine rotor has a disk carrying vanes, each vane having a blade linked by a platform to a root. For at least one vane, a recess is defined between the platform and the disk, and a vibration damper is mounted in the recess. The vibration damper includes a first structural portion configured to contact the platform of which the vibrations are to be dampened, and a second mass portion configured to dampen these vibrations. The second mass portion is a powder and the first structural portion is a box containing the powder.
    Type: Grant
    Filed: December 12, 2017
    Date of Patent: May 17, 2022
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventor: Laetitia Pollet
  • Publication number: 20220134426
    Abstract: A method for manufacturing a compressor impeller or rotor including a hub that carries blades, involving a step of manufacturing a hub which includes all or some of the blades, and a step of additive manufacture by adding localised material using a method such as the LMD process to form or finish each blade.
    Type: Application
    Filed: February 18, 2020
    Publication date: May 5, 2022
    Applicant: SAFRAN HELICOPTER ENGINES
    Inventors: Rainer THOMAS, Laurent Pierre TARNOWSKI, Mathieu Laurent HERRAN, Ludovic André Joël NAUDOT