Patents Assigned to SAFRAN HELICOPTER ENGINES
  • Method and system for controlling an emergency device
    Patent number: 11198505
    Abstract: The invention relates to a method for controlling an emergency device of a helicopter, said helicopter comprising a rotor suitable for being rotated, said emergency device being suitable for supplying additional emergency propulsion power to the helicopter, in said method comprising a step (10) of measuring the rotation speed of the helicopter rotor, a step (12) of calculating the drift of the measured rotation speed, a step (20) of continuously verifying conditions such that the speed of rotation of the rotor is higher than a predetermined value, referred to as arming speed, and the drift of the rotation speed is lower than a predetermined value, referred to as arming drift, and a step (22) of activating the emergency device if the verified conditions are validated.
    Type: Grant
    Filed: February 14, 2018
    Date of Patent: December 14, 2021
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Romain Thiriet, Jean Michel Bazet, Jean-Luc Charles Gilbert Frealle, Pierre Darfeuil
  • ELECTRICAL MACHINE OF A TURBOMACHINE COMPRISING A ROTOR COOLED BY A COOLING CHANNEL
    Publication number: 20210376677
    Abstract: The invention relates to an electrical machine comprising a stator (1) and a rotor (2) designed to be rotated in relation to each other, said rotor (2) or said stator comprising a plurality of permanent magnets (5), at least one permanent magnet comprising at least one fluid-propagation channel (10) extending longitudinally inside the permanent magnet, the propagation channel comprising a fluid inlet and a fluid outlet, the fluid inlet being bell-mouthed and oriented in a preferential direction of rotation of the permanent magnet.
    Type: Application
    Filed: November 14, 2018
    Publication date: December 2, 2021
    Applicant: SAFRAN HELICOPTER ENGINES
    Inventors: Thomas KLONOWSKI, Camel SERGHINE, Jean-Luc Charles Gilbert FREALLE, Sebastien COMBEBIAS, Jean-Julien Camille VONFELT
  • Wheel blade for turbomachine, comprising a winglet at its tip and at the leading edge
    Patent number: 11187234
    Abstract: A wheel blade for a turbomachine compressor. The blade comprises a body extending between the root of the blade in the direction of the height of the blade. The body extends from a leading-edge to a trailing edge in a direction of the camber line of the blade. The blade comprises a winglet located in the extension of the body in the direction of the height. The winglet is located at the tip of the blade and at the leading edge of the blade. The body has a curvature oriented in a first direction of rotation with respect to the direction of the camber line, the winglet having a curvature in a second direction of rotation counter to the first direction of rotation.
    Type: Grant
    Filed: January 25, 2018
    Date of Patent: November 30, 2021
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Fabien Artus, Youssef Bouchia, Laurent Pierre Tarnowski
  • Assembly for a turbomachine
    Patent number: 11181009
    Abstract: An assembly for a turbomachine including an annular channel designed to form a flow duct for a flow of gas between two turbine stages of the turbomachine. The channel is bounded by a radially inner annular wall and a radially outer annular wall. The walls are connected by hollow arms that extend radially, a support having a radially outer annular part that is located radially outside the outer annular wall of the annular channel, and a radially inner annular part that is located radially inside the inner annular wall of the annular channel. The outer and inner parts of the support are connected by connecting parts that extend radially and pass through one of the hollow arms of the annular channel. The connecting parts may be connected by a connecting partition having a frangible part that ruptures when the mechanical stresses in the connecting partition are above a threshold.
    Type: Grant
    Filed: February 28, 2019
    Date of Patent: November 23, 2021
    Assignee: Safran Helicopter Engines
    Inventors: Baptiste Hallouin, Alexandre Montpellaz, Sylvain Pierre Votie, Fabrice Iparaguirre, Yann Danis
  • TURBINE SEAL
    Publication number: 20210348518
    Abstract: An assembly for a multistage turbine of a turbomachine has a static sealing device and a nozzle with a radially outer end and an outer casing surrounding the nozzle. The static sealing device is arranged radially between a radially outer end of the nozzle and the outer casing. The static sealing device includes an annular seal borne by the nozzle and an annular structure that defines a plurality of radial annular walls. The walls are axially spaced apart from one another, and at least one first wall is in annular contact radially inwardly with the annular seal. A longitudinal dimension of the annular contact is less than a longitudinal dimension of the seal.
    Type: Application
    Filed: September 20, 2019
    Publication date: November 11, 2021
    Applicant: SAFRAN HELICOPTER ENGINES
    Inventor: Frédéric Philippe Jean-Jacques Pardo
  • Architecture for a propulsion system of a helicopter including a hybrid turboshaft engine and a system for reactivating said hybrid turboshaft engine
    Patent number: 11161603
    Abstract: The invention relates to an architecture of a propulsion system of a multi-engine helicopter comprising turboshaft engines connected to a power transmission gearbox, characterised in that it comprises: at least one hybrid turboshaft engine (20) capable of operating in at least one standby mode during a stable cruise flight of the helicopter; at least two systems (30; 40) for controlling each hybrid turboshaft engine (20), each system (30; 40) comprising an electric machine (31; 41) connected to the hybrid turboshaft engine (20) and suitable for rotating the gas generator thereof, and at least one source (33; 43) of electrical power for said electric machine (31; 41), each reactivation system (30; 40) being configured such that it can drive said turboshaft engine (20) in at least one operating mode among a plurality of predetermined modes.
    Type: Grant
    Filed: October 6, 2015
    Date of Patent: November 2, 2021
    Assignees: SAFRAN HELICOPTER ENGINES, SAFRAN ELECTRICAL & POWER
    Inventors: Philippe Vallart, Jean-Michel Bazet, Loïc Le Duigou
  • Labyrinth seal comprising a lip provided with a deflector
    Patent number: 11143049
    Abstract: A labyrinth seal lip (5) comprises, standing on one of its lateral faces (7), a deflector (13) which channels the flow of gas tangent to the lip (5) towards the facing seal (4) so as to disturb the leakage flow (22) through the gap and decrease the flow rate.
    Type: Grant
    Filed: November 16, 2018
    Date of Patent: October 12, 2021
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Bertrand Guillaume Robin Pellaton, Lucas Benassis
  • Thermometric measurement by meshing of probes, particularly in turbine engines
    Patent number: 11125630
    Abstract: The invention relates to a temperature measurement device comprising at least three probes, a computer, the computer being configured to estimate a temperature on the basis of voltage measurements at the output of the probes, characterised in that the probes are connected together in a plurality of meshes mounted in series, with at least one mesh comprising at least two probes mounted in parallel and at least one other mesh comprising a probe or a plurality of probes mounted in parallel.
    Type: Grant
    Filed: February 28, 2018
    Date of Patent: September 21, 2021
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Rafaël Samson, Antoine Pascal Moutaux
  • 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