Patents Assigned to SAFRAN HELICOPTER ENGINES
  • 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
  • Ring-shaped combustion chamber for a turbine engine
    Patent number: 10895383
    Abstract: An annular combustion chamber (10) having a first annular wall (12) and a second annular wall (13) that are coaxial about an axis (X), a chamber end wall (14) connecting together the first and second walls (12, 13), and a plurality of injectors (16), the first wall (12) including first air feed holes (18) downstream from the injectors (16), the combustion chamber (10) being characterized in that for at least a first one of said injectors (16), at least three of the first holes (18) sharing the first injector as their closest injector are situated at equal distances (D) from the first injector (16).
    Type: Grant
    Filed: October 4, 2016
    Date of Patent: January 19, 2021
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Stéphane Pascaud, Guillaume Taliercio
  • TURBINE STATOR VANE COMPRISING AN INNER COOLING WALL PRODUCED BY ADDITIVE MANUFACTURING
    Publication number: 20210003015
    Abstract: A stator vane of a turbine of a gas turbine engine, including an outer platform and an inner platform between which there extends an outer wall forming an outer skin, wherein it includes an inner wall, forming an inner skin, facing the outer wall so as to define an inter-skin cavity between the outer wall and the inner wall, the inner wall including a plurality of cooling orifices for impingement cooling of the outer wall, the outer wall and inner wall being produced by additive manufacturing.
    Type: Application
    Filed: March 26, 2019
    Publication date: January 7, 2021
    Applicant: SAFRAN HELICOPTER ENGINES
    Inventors: Baptiste HALLOUIN, Jean-Luc BREINING, Damien LABERNY
  • ASSEMBLY FOR A TURBOMACHINE
    Publication number: 20200408109
    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: Application
    Filed: February 28, 2019
    Publication date: December 31, 2020
    Applicant: Safran Helicopter Engines
    Inventors: Baptiste Hallouin, Alexandre Montpellaz, Sylvain Pierre Votie, Fabrice Iparaguirre, Yann Danis
  • Removable pack for reactivating a turboshaft engine, architecture for a multi-engine system for propelling a helicopter, provided with such a pack, and corresponding helicopter
    Patent number: 10858999
    Abstract: The invention relates to a removable reactivation pack for a turboshaft engine of a helicopter, comprising a gas generator equipped with a drive shaft, said turboshaft engine (6) being capable of operating in at least one standby mode during a stable flight of the helicopter, said removable pack comprising: a removable gearbox comprising a gearbox output shaft; controlled means for rotating said gearbox output shaft, referred to as reactivation means of said turboshaft engine; mechanical means for reversibly coupling said gearbox output shaft to said drive shaft of said gas generator.
    Type: Grant
    Filed: October 14, 2015
    Date of Patent: December 8, 2020
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Patrick Marconi, Romain Thiriet, Camel Serghine, Caroline Seve, Pierre Darfeuil
  • Bladed rotor
    Patent number: 10858946
    Abstract: A bladed rotor comprising a rotor disk (12) presenting two front faces (14, 15) and an outer peripheral face (16), sockets (18) being provided in the outer peripheral face (16) and opening out into at least one of the front faces (14, 15). The rotor (10) comprising blades (30), each having a root (32) whereby the blade is fastened in a socket (18), an end face (31) of the root being substantially level with the front face (14) of the disk when the blade is fastened in the socket. A coating layer (40) is deposited on the disk (12) so as to cover both at least a portion of the front face (14) of the disk and at least a portion of the end face (31) of the root (32).
    Type: Grant
    Filed: November 28, 2014
    Date of Patent: December 8, 2020
    Assignee: Safran Helicopter Engines
    Inventor: Ludovic Meziere
  • PROPULSION SYSTEM FOR AN AIRCRAFT
    Publication number: 20200354051
    Abstract: A propulsion system for an aircraft, comprising at least one rotor and a nacelle fairing extending around the at least one rotor with respect to an axis of rotation of the rotor, the nacelle fairing comprising: an upstream section forming an inlet section of the nacelle fairing; a downstream section, a downstream end of which forms an outlet section of the nacelle fairing; and an intermediate section connecting the upstream and downstream sections, wherein the downstream section comprises a radially inner wall and a radially outer wall made of a deformable shape memory material, and wherein the downstream end forming the outlet section has a pneumatic or hydraulic annular actuator extending around the axis of rotation and configured to deform radially under a predetermined control pressure so as to vary an outer diameter of the outlet section between a minimum diameter and a maximum diameter.
    Type: Application
    Filed: April 10, 2020
    Publication date: November 12, 2020
    Applicants: SAFRAN, SAFRAN HELICOPTER ENGINES
    Inventors: Jean-Louis Robert Guy Besse, Ye-Bonne Karina Maldonado
  • Aircraft turboprop engine provided with an electric machine
    Patent number: 10807724
    Abstract: The electrical machine according to the invention is a dual machine, and comprises a first machine which can be reversed and a second machine functioning through induction between two windings. The second machine can be used for de-icing a propeller, the induction-receiving winding being mounted on the propeller shaft. The first electrical machine can function as an electrical engine to ‘taxi’ the aircraft. In certain embodiments, the winding mounted on the stator is common to the two machines and different magnetic flows are utilised to control them. A separate functioning of the two machines and a very good integration into the aircraft engine, with space-saving and low mass, are possible.
    Type: Grant
    Filed: October 2, 2017
    Date of Patent: October 20, 2020
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Thomas Klonowski, Olivier Lafargue, Antoine Moutaux, Jean-Julien Camille Vonfelt, Bertrand Nogarede
  • PROPULSION SYSTEM FOR AN AIRCRAFT
    Publication number: 20200324875
    Abstract: A propulsion system for an aircraft, comprising at least one rotor and a nacelle fairing extending around the at least one rotor with respect to an axis of rotation of the rotor, the nacelle fairing comprising: an upstream section forming an inlet section of the nacelle fairing; a downstream section wherein a downstream end forms an outlet section of the nacelle fairing; and an intermediate section connecting the upstream and downstream sections, wherein the downstream section comprises a radially inner wall and a radially outer wall made of a deformable shape memory material, and further comprising at least one actuator mechanism with at least one cylinder configured to cooperate with one or more components, projections, etc., embedded in an inner surface of the radially outer wall so as to vary an outer diameter of the outlet section between a minimum diameter and a maximum diameter.
    Type: Application
    Filed: April 10, 2020
    Publication date: October 15, 2020
    Applicants: SAFRAN, SAFRAN HELICOPTER ENGINES
    Inventors: Jean-Louis Robert Guy Besse, Ye-Bonne Karina Maldonado
  • Particle-trapping device for a turbomachine and turbomachine with such a device
    Patent number: 10767512
    Abstract: The invention relates to a particle-trapping device (2) for a turbomachine, said particles being contained in an air stream flowing inside a turbomachine, in particular the air stream flowing in the bypass region (17) of the combustion chamber (13) of said turbomachine. The device is characterized in that it comprises: —at least two particle deflectors (3, 3a, 3b, 3c), —a member (5) for collecting and storing the particles deflected by said deflector, —and means (6) for attaching said trapping device (2) to a part of the turbomachine.
    Type: Grant
    Filed: September 8, 2016
    Date of Patent: September 8, 2020
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Amaury Paillard, Stephane Pascaud
  • Architecture of a multiple-engine helicopter propulsion system, and corresponding helicopter
    Patent number: 10766629
    Abstract: An architecture of a propulsion system of a multi-engine helicopter is disclosed, comprising turboshaft engines that are connected to a power transmission gearbox. It comprises: a hybrid turboshaft engine that is capable of operating in at least one standby mode during a stable flight of the helicopter; a pack for quickly restarting said hybrid turboshaft engine in order to bring said engine out of said standby mode and to reach a nominal operating mode; an auxiliary power unit that is connected to said electrotechnical restart pack by means of a first AC/DC converter and is capable of providing said restart pack, on demand, with power required for bringing said hybrid turboshaft engine out of said standby mode.
    Type: Grant
    Filed: March 20, 2015
    Date of Patent: September 8, 2020
    Assignees: SAFRAN HELICOPTER ENGINES, SAFRAN POWER UNITS
    Inventors: Fabien Mercier-Calvairac, Stéphane Beddok, Stéphane Chevalier, Sophie Humbert
  • Method of evaluating the corrosion resistance of a coated metal substrate
    Patent number: 10753853
    Abstract: A method of evaluating the corrosion resistance of a coated metal substrate, the method including putting a liquid composition into contact with a corrosion protection coating present on the surface of a metal substrate, the liquid composition including water, a gelling agent, corrosion-catalyst ions, and a color pH indicator; gelling the liquid composition in order to form a corrosion-accelerator gel in contact with the coating; performing a corrosion test during which the gel that has formed is left in contact with the corrosion protection coating; and evaluating the corrosion resistance of the substrate coated by the corrosion protection coating by observing the color of the color pH indicator present in the gel after performing the corrosion test.
    Type: Grant
    Filed: September 9, 2016
    Date of Patent: August 25, 2020
    Assignees: ARIANEGROUP SAS, SAFRAN HELICOPTER ENGINES
    Inventors: Marie Betaille-Francoual, Loïc Oger, Anaïs Lecaplain
  • Turbomachine designed to operate in turning gear mode
    Patent number: 10753280
    Abstract: A field of turbine engines, and more particularly to an engine including a compressor; a combustion chamber; a first turbine connected to the compressor by a first rotary shaft; an actuator device for actuating the first rotary shaft in order to keep the first turbine and the compressor in rotation while the combustion chamber is extinguished; and a lubrication circuit for lubricating the engine. The circuit passes through at least one heat source suitable for heating the lubricant in the lubrication circuit while the first turbine and the compressor are rotating with the combustion chamber extinguished.
    Type: Grant
    Filed: September 29, 2014
    Date of Patent: August 25, 2020
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Romain Thiriet, Vincent Poumarede, Camel Serghine