Patents Assigned to SAFRAN HELICOPTER ENGINES
  • Integration of a phase-change material for limiting the temperature of fuel from an electronic module
    Patent number: 11085376
    Abstract: The invention concerns an assembly comprising: a fuel supply circuit (15, 15a, 15b) configured to supply fuel to a turbine heat engine, an electronic module (14, 14a, 14b), a power source (13, 13a, 13b) for supplying power to the electronic module (14, 14a, 14b), and a heat exchanger (16, 16a, 16b) positioned to allow a flow of heat from the electronic module (14, 14a, 14b) to the fuel supply circuit (15, 15a, 15b), the assembly being characterised in that the electronic module (14, 14a, 14b) comprises a phase-change material (PCM), configured to change state when the temperature of same reaches a predetermined phase-change temperature (Tf).
    Type: Grant
    Filed: June 12, 2017
    Date of Patent: August 10, 2021
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Thomas Klonowski, Camel Serghine
  • PROPULSION SYSTEM FOR A HELICOPTER
    Publication number: 20210237887
    Abstract: A propulsion system for a helicopter includes a linked turbine engine that is configured to drive a main rotor configured to be coupled to a rotary wing. The propulsion system further includes an electric machine that is configured to form an electric motor. The electric machine is coupled directly or indirectly to the main rotor.
    Type: Application
    Filed: April 25, 2019
    Publication date: August 5, 2021
    Applicant: SAFRAN HELICOPTER ENGINES
    Inventors: Jean-Louis Robert Guy Besse, Benjamin Antoine Boussand
  • METHOD FOR LOW-PRESSURE CARBURIZING OF A WORKPIECE COMPRISING STEEL
    Publication number: 20210230732
    Abstract: A method for carburizing a steel workpiece includes implementing between 1 and 30 consecutive carburizing cycles, each carburizing cycle including injecting carburizing gas in such a way as to increase the surface carbon rate until a predetermined higher rate is reached, a step of injecting a neutral gas so as to decrease the surface carbon rate of the workpiece until it reaches a predetermined lower rate, followed by a second phase of injection of the neutral gas.
    Type: Application
    Filed: June 5, 2019
    Publication date: July 29, 2021
    Applicant: SAFRAN HELICOPTER ENGINES
    Inventors: Bruno Petroix, André Marcarie
  • Centrifugal deaerator for a turbomachine
    Patent number: 11060456
    Abstract: A centrifugal deaerator for an air/oil mixture of a turbine engine includes: an annular housing arranged around a hollow shaft and having an outer annular wall and an inner annular wall; axial mixture inlets for the inflow of the air/oil mixture into annular housing; a pinion for rotating the annular housing, the pinion including a web that is securely connected to the hollow shaft and to the inner and outer annular walls; radial oil outlets in the outer wall; and oil-free air outlets in the inner wall. The axial mixture inlets and the radial oil outlets are axially arranged on either said of the web to prevent the axial mixture inlets from reintroducing oil evacuated by radial oil outlets into the annular housing.
    Type: Grant
    Filed: March 7, 2018
    Date of Patent: July 13, 2021
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Benjamin Fulleringer, Jean-Pierre Pajard, Yannick Cazaux
  • TENSILE TESTING MACHINE
    Publication number: 20210199549
    Abstract: A tensile testing machine comprising a test specimen whose elongation is to be measured along a tensile axis, slide plates, an intermediate plate, and first and second parallel guide rods, which freely guide the slide plates axially past them.
    Type: Application
    Filed: May 29, 2019
    Publication date: July 1, 2021
    Applicant: Safran Helicopter Engines
    Inventors: Gilles Ader, Christophe Siret, Pierre Lamarque
  • Turboprop comprising an incorporated electricity generator
    Patent number: 11047312
    Abstract: An electrical generator is housed in an annular cavity between the casing and the propeller shaft of a turboprop, while imposing little or no additional space requirement and with lightweight ancillary equipment. The rotor of the generator is mounted on an autonomous shaft end. A flange of the outer casing is removable in order to access the generator and to enable its easy removal and remounting.
    Type: Grant
    Filed: February 28, 2018
    Date of Patent: June 29, 2021
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Thomas Klonowski, David Cazaux, Olivier Lafargue
  • CONNECTION BETWEEN A CERAMIC MATRIX COMPOSITE STATOR SECTOR AND A METALLIC SUPPORT OF A TURBOMACHINE TURBINE
    Publication number: 20210189895
    Abstract: A turbine of a turbomachine includes a ceramic matrix composite sector of a stator includes an outer platform and an inner platform connected via at least one vane, The outer platform has means for attaching to a sector of a metallic support, the attachment means having at least one central rim and two lateral rims. The central rim is radially offset with respect to said lateral rims along a directrix line such that the central rim is radially on one side of said directrix line and the lateral rims on the other. The central rim and said central hook bear radially against one another and are located radially on either side of said directrix line. The lateral rim and said corresponding lateral hook bear radially against one another and are located radially on either side of said directrix line.
    Type: Application
    Filed: December 3, 2018
    Publication date: June 24, 2021
    Applicants: SAFRAN AIRCRAFT ENGINES, SAFRAN HELICOPTER ENGINES
    Inventors: Nicolas Paul Tableau, Sébastien Serge Francis Congratel, Lucien Henri Jacques Quennehen, Gilles Gérard Claude Lepretre, Denis Daniel Jean Boisseleau
  • VIBRATION DAMPER FOR A TURBOMACHINE ROTOR VANE
    Publication number: 20210180460
    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: Application
    Filed: December 12, 2017
    Publication date: June 17, 2021
    Applicant: SAFRAN HELICOPTER ENGINES
    Inventor: Laetitia Pollet
  • Blade equipped with a cooling system, associated guide vanes assembly and associated turbomachine
    Patent number: 11035255
    Abstract: The present disclosure relates to a blade of a guide vane assembly of a turbomachine fitted with a cooling system, generally including an insert arranged inside an internal cavity of said blade, connected to a cooling air inlet of the blade and designed to cool the surface of the internal cavity of the blade, and a bleed device configured to bleed some of the cooling air inside the insert and designed to send this bled cooling air to a central hub of the turbomachine. The bleed device of the blade may further include a bleed head arranged in the internal cavity of the blade and passing through an opening of the insert, and configured to bleed some of the cooling air inside the insert.
    Type: Grant
    Filed: November 10, 2016
    Date of Patent: June 15, 2021
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Baptiste Hallouin, Jean-Luc Breining, Damien Laberny
  • Device for limiting the loosening of a nut in a turbine engine
    Patent number: 11022241
    Abstract: An assembly for a turbine engine. The assembly includes a mount, a nut clamping around the male portion of the mount, a member projecting from the mount and a device for limiting loosening of the nut. The loosening limitation device includes a member for locking the nut against rotation relative to the mount. The rotation locking member includes an inner surface designed to limit rotation of the nut with shape engagement with an outer surface of the nut. The rotation locking member includes a first anti-rotation abutment designed to rotatably abut against the projecting member. The loosening limitation device includes a translation locking member designed to limit translation of the rotation locking member relative to the nut.
    Type: Grant
    Filed: December 1, 2016
    Date of Patent: June 1, 2021
    Assignee: Safran Helicopter Engines
    Inventors: Mathieu Cladiere, Cedric Roger Zordan, Stephane Vergez
  • METHOD FOR PRODUCING PARTS HAVING A COMPLEX SHAPE BY METAL POWDER INJECTION MOULDING
    Publication number: 20210146437
    Abstract: A method for producing, by a metal powder injection moulding (MIM) technique, a part formed of at least one metal and/or at least one metal alloy including at least one internal cavity. A green core of a mixture of at least one powder of at least one ceramic and of a thermoplastic binder is used.
    Type: Application
    Filed: July 12, 2018
    Publication date: May 20, 2021
    Applicant: SAFRAN HELICOPTER ENGINES
    Inventors: Yann DANIS, Laurent CHARES
  • METHOD FOR CHECKING THE MAXIMUM AVAILABLE POWER OF A TURBINE ENGINE OF AN AIRCRAFT EQUIPPED WITH TWO TURBINE ENGINES
    Publication number: 20210108578
    Abstract: A method for checking the maximum available power of a turbine engine of an aircraft equipped with two turbine engines configured to operate in parallel and together to supply a necessary power to the aircraft during a flight phase includes: placing one of the turbine engines in a maximum take-off power regime, and adjusting a power supplied by the other turbine engine, such that the turbine engines continue to supply the necessary power to the aircraft during the flight phase; determining a power supplied by the turbine engine placed in the maximum take-off power regime, and processing the supplied power determined in this way, in order to deduce a piece of information relating to the maximum available power.
    Type: Application
    Filed: March 30, 2018
    Publication date: April 15, 2021
    Applicant: SAFRAN HELICOPTER ENGINES
    Inventors: Pierre DARFEUIL, Patrick MARCONI, Caroline SEVE
  • DEVICE FOR TEMPORARILY INCREASING TURBOMACHINE POWER
    Publication number: 20210102491
    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: Application
    Filed: March 27, 2018
    Publication date: April 8, 2021
    Applicant: SAFRAN HELICOPTER ENGINES
    Inventors: Frédéric POUSSE, Lionel NAPIAS, Laurent MINEL, Bertrand MOINE
  • Turboshaft engine embeddable in a reduction gearbox
    Patent number: 10961867
    Abstract: A turboshaft engine for a helicopter, comprising a case inside which a gas generator and a turbine are accommodated, the turbine being mounted on a power shaft that extends along a longitudinal direction. The turboshaft engine further comprises means for removably mounting the power shaft into a reduction gearbox inside which at least one gear of a first reduction stage is accommodated. The means for removably mounting the power shaft include a pinion having a central bore, the shape of which is adapted to that of the power shaft in such a way that the pinion can slide over the power shaft; furthermore, the contour of the pinion is adapted to the shape of the gear of the first stage in such a way that the pinion can form a leading input pinion of the gearbox in said gear once the power shaft has been mounted in the reduction gearbox.
    Type: Grant
    Filed: April 26, 2016
    Date of Patent: March 30, 2021
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Olivier Lafargue, Sébastien Brotier, Alphonse Puerto
  • TURBINE STATOR BLADE COOLED BY AIR-JET IMPACTS
    Publication number: 20210087938
    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: Application
    Filed: March 20, 2019
    Publication date: March 25, 2021
    Applicant: SAFRAN HELICOPTER ENGINES
    Inventors: Baptiste HALLOUIN, Jean-Maurice CASAUX-BIC, Alexandre MONTPELLAZ, Lionel RENAULT
  • Helicopter equipped with a device for emergency lift assistance
    Patent number: 10953981
    Abstract: The invention relates to a helicopter including a structural framework, at least one main rotor for lift and propulsion integral with said structural framework and a drive train for driving said main rotor including a power transmission gearbox and at least one main engine, wherein it further includes a plurality of extra booster power units fixed to said structural framework and configured so as to be able to supply extra lift of the helicopter in case of failure of the helicopter's drive train.
    Type: Grant
    Filed: September 2, 2016
    Date of Patent: March 23, 2021
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Eric Pierre Seinturier, Romain Thiriet, Fabien Mercier-Calvairac
  • Clogging monitoring in a starter injector purge circuit for a turbomachine
    Patent number: 10947903
    Abstract: A fuel supply system for a turbomachine. The supply system includes a starter circuit, at least one first hydraulic resistance and a purge circuit. The purge circuit includes a duct including an opening at the exterior of the supply system. The purge circuit is configured to make purge air flow between a starter injector and the opening through the first hydraulic resistance. The supply system includes a device for measuring a value representative of pressure, which devices are configured to measure a value representative of pressure between the starter injector and the first hydraulic resistance when purge air flows between the starter injector and the first hydraulic resistance.
    Type: Grant
    Filed: June 15, 2017
    Date of Patent: March 16, 2021
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Patrick Duchaine, Pascal Hubert Verdier
  • Assembly for turbomachine combustion chamber comprising a boss and an annular element
    Patent number: 10941943
    Abstract: An assembly for a turbomachine combustion chamber, including a boss for turbomachine combustion chamber, including a tubular body configured to be inserted in a receiving orifice formed in an annular wall of a flame tube and to accommodate a shank of a connecting pin for connecting the flame tube to an external casing, a first end of the boss including an annular flange configured to prevent radial translational movement of the boss in a first direction, and a second end of the boss being configured to be crimped to the wall of the flame tube so as to prevent radial translational movement of the boss in a second direction, and an annular element configured to fit coaxially with the receiving orifice and in radial contact with the annular wall of the flame tube on the one hand and with the annular flange of the boss on the other.
    Type: Grant
    Filed: June 19, 2015
    Date of Patent: March 9, 2021
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Ludovic Andre Joel Naudot, Philippe Olharan, Jean Menet-Haure
  • Assembly for turbine engine for measuring vibrations sustained by a rotating blade
    Patent number: 10921179
    Abstract: An assembly for a turbine engine, the assembly including a casing and an impeller rotatably movable inside the casing, the impeller including at least one blade having a tip edge opposite the casing, wherein the tip edge includes a magnet and wherein the casing includes an electrical conductor suitable for generating between the terminals thereof an electric voltage induced by the magnet of the tip edge opposite same and representing vibrations sustained by the tip edge of the blade when the impeller is rotated.
    Type: Grant
    Filed: December 22, 2014
    Date of Patent: February 16, 2021
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Arnaud Talon, Gilbert Arrouge, Jean-Yves Cazaux, Julien Garnier
  • High-pressure distributor blading having a variable-geometry insert
    Patent number: 10914179
    Abstract: The invention relates to distributor blading (10) having a blade (12), including a pressure-side wall (16) and a suction-side wall (14), and an insert (20) placed in the blade (12) and including: a closed wall (22) having an outer skin (24) extending opposite the pressure-side walls (16) and suction-side walls (14), the outer skin (24) and the wall of the facing blade (12) being separated by an air gap (30), a series of reinforcements (25) formed in the closed wall (22) and leading into the outer skin (24), and a series of through-openings formed in the reinforcements (25), the heights of impact (h) between said through-openings and the pressure-side wall (16) or the facing suction-side wall (14) being greater than the air gap (30).
    Type: Grant
    Filed: July 20, 2016
    Date of Patent: February 9, 2021
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Frederic Philippe Jean-Jacques Pardo, Guilhem Verron