Patents Assigned to SAFRAN HELICOPTER ENGINES
  • PROPULSION SYSTEM FOR A SINGLE-ENGINE HELICOPTER
    Publication number: 20190352001
    Abstract: Propulsion system (8) for a single-engine helicopter (1), comprising: a main engine (9) connected to a front drive shaft (5) and a rear drive shaft (7), respectively, suitable for driving a main gearbox (4) referred to as MGB (4) and a tail gearbox (6) referred to as TGB (6); ? an assistance device (10) attached to the main engine (9); characterised in that said propulsion system (8) is designed in order that the assistance device (10) can mechanically drive the TGB and MGB (6, 4) by introducing power to the rear drive shaft (7).
    Type: Application
    Filed: February 5, 2018
    Publication date: November 21, 2019
    Applicants: SAFRAN HELICOPTER ENGINES, SAFRAN HELICOPTER ENGINES
    Inventors: Romain THIRIET, Camel SERGHINE, Alphonse PUERTO, Christian SARRAT
  • SUPERALLOY BASED ON NICKEL, MONOCRYSTALLINE BLADE AND TURBOMACHINE
    Publication number: 20190330714
    Abstract: A nickel-based superalloy comprises in mass percent: 4.0% to 6.0% chromium; 0.4% to 0.8% molybdenum; 2.5% to 3.5% rhenium; 6.2% to 6.6% tungsten; 5.2% to 5.7% aluminum; 0.0 to 1.6% titanium; 6.0% to 9.9% tantalum; 0.0 to 0.7% hafnium; and 0.0 to 0.3% silicon; the balance being constituted by nickel and any impurities. A monocrystalline blade comprises such an alloy and a turbomachine including such a blade.
    Type: Application
    Filed: October 24, 2017
    Publication date: October 31, 2019
    Applicants: Safran, Safran Aircraft Engines, Office National D'Etudes et de Recherches Aerospatiales, Safran Helicopter Engines
    Inventors: Jérémy RAME, Philippe BELAYGUE, Pierre CARON, Joël DELAUTRE, Virginie JAQUET, Odile LAVIGNE
  • Turboshaft engine for an aircraft equipped with an automatically-activated centraliser
    Patent number: 10458341
    Abstract: A turboshaft engine includes a casing in which is arranged a gas generator and a free turbine fitted to a power shaft. The power shaft is configured to be mechanically connected to/disconnected from a reduction gearbox. The turboshaft engine includes at least one centralizer movable between an active position, in which the centralizer forms a bearing for the power shaft and which corresponds to a mechanical disconnection between the power shaft and the reduction gearbox, and a passive position, in which the centralizer is distanced from the power shaft and which corresponds to a mechanical connection between the power shaft the reduction gearbox.
    Type: Grant
    Filed: April 26, 2016
    Date of Patent: October 29, 2019
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Olivier Lafargue, Sébastien Brotier
  • Method and a system for reliably starting a turbine engine
    Patent number: 10450962
    Abstract: There is provided a starting system for reliably starting a turbine engine, the system including first and second circuits connected in parallel and arranged between a battery of the engine and a DC starter of the engine, the first circuit including a DC-DC converter connected in series with a first switch and the second circuit including a second switch; a sensor configured to sense a speed of rotation of a compressor of the engine; a sensor configured to sense a temperature at an inlet to a free turbine of the engine; and a control circuit configured to control the first and second switches as a function of information supplied by the sensor configured to sense the speed of rotation of the compressor and by the sensor configured to sense the inlet temperature of the free turbine.
    Type: Grant
    Filed: December 15, 2014
    Date of Patent: October 22, 2019
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Vincent Poumarede, Pierre Harriet
  • INTEGRATION OF A PHASE-CHANGE MATERIAL FOR LIMITING THE TEMPERATURE OF FUEL FROM AN ELECTRONIC MODULE
    Publication number: 20190309687
    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: Application
    Filed: June 12, 2017
    Publication date: October 10, 2019
    Applicant: SAFRAN HELICOPTER ENGINES
    Inventors: Thomas KLONOWSKI, Camel SERGHINE
  • Method for automatically controlling the operating speed of a helicopter turboshaft engine, corresponding control device and helicopter provided with such a device
    Patent number: 10435167
    Abstract: The invention relates to a method for automatically controlling an operating mode of a turboshaft engine of a helicopter, comprising a step (10) of receiving data (27, 28, 29) that are representative of the flight of the helicopter; a step (11) of selecting the turboshaft engine for which a change of mode would be most relevant; a step (12) of determining an operating mode of said turboshaft engine, known as the selected mode, selected from a plurality of predetermined operating modes; and a step (14) of ordering the operating mode of said turboshaft engine into said selected mode. The invention also relates to a corresponding control device.
    Type: Grant
    Filed: December 15, 2014
    Date of Patent: October 8, 2019
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Romain Thiriet, Caroline Seve, Vincent Poumarede
  • Self-contained power unit for implementing a method for optimizing the operability of an aircraft propulsive unit
    Patent number: 10428739
    Abstract: A main power unit implements an optimization method in an aircraft including energy-consuming equipments, a cabin in which air is renewed and temperature and/or pressure of which are regulated by a regulation system, main power-generating engines, and a flight control unit. The main power unit is built into a compartment which is insulated from other zones of the aircraft with a fireproof bulkhead and fitted with an outside-air intake and an exhaust nozzle. The main power unit includes an engine-type power unit as a main power source, fitted with a gas generator and with a power turbine for driving equipments including a supercharger. The supercharger is coupled, via a regulation control which communicates with the control unit, with the regulation system in order to supply a necessary pneumatic energy to the cabin.
    Type: Grant
    Filed: June 10, 2016
    Date of Patent: October 1, 2019
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventor: Jean-Michel Haillot
  • Device for controlling a propeller, having variable-pitch blades, of a turboprop engine
    Patent number: 10421530
    Abstract: A device for controlling a propeller, having variable-pitch blades, of a turboprop engine, has a first hydromechanical device for controlling the pitch of the blades of the propeller and a second hydromechanical device for controlling the speed of rotation of the propeller. The device includes a single electromechanical actuator with a movable actuator member mechanically connected both to the first hydromechanical device for controlling the pitch, in order to manage the pitch setpoint, and to the second hydromechanical device for controlling the speed, in order to manage the speed setpoint.
    Type: Grant
    Filed: June 17, 2016
    Date of Patent: September 24, 2019
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Antoine Moutaux, Jean-Michel Presse
  • Hydraulic device for emergency starting a turbine engine, propulsion system of a multi-engine helicopter provided with one such device, and corresponding helicopter
    Patent number: 10422285
    Abstract: Emergency start-up device for a turboshaft engine of a helicopter, comprising: a hydraulic motor which is mechanically connected to said turboshaft engine; a hydropneumatic store which is connected to said hydraulic motor by a hydraulic circuit for supplying pressurized liquid to said hydraulic motor; and a hydraulic valve which has controlled quick opening, arranged on the hydraulic circuit between said store and said hydraulic motor, and is suitable for being placed on command at least in an open position in which the liquid can supply said hydraulic motor, or in a closed position in which said hydraulic motor is no longer supplied with pressurized liquid.
    Type: Grant
    Filed: March 20, 2015
    Date of Patent: September 24, 2019
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Romain Thiriet, Bertrand Moine, Camel Serghine, François Porel
  • PYROTECHNIC DEVICE
    Publication number: 20190285001
    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: Application
    Filed: November 17, 2017
    Publication date: September 19, 2019
    Applicant: Safran Helicopter Engines
    Inventors: François DANGUY, Laurent Paul Lattanzio FABBRI, Romain Maurice Henri Yannick GAUTHIER, Didier Paul SAUCEREAU
  • Turboshaft engine comprising a controlled mechanical coupling device, helicopter equipped with such a turboshaft engine, and method for optimising the zero-power super-idle speed of such a helicopter
    Patent number: 10415482
    Abstract: The invention relates to a turboshaft engine comprising a gas generator (5) that is capable of being rotated, and a free turbine (6) that is rotated by the gases of said gas generator, characterized in that it comprises a device (40) for controlled mechanical coupling of said gas generator (5) and said free turbine (6) that is capable of connecting said gas generator (5) and said free turbine (6) mechanically and on demand as soon as the rotational speed of said gas generator (5) reaches a predetermined threshold speed.
    Type: Grant
    Filed: March 20, 2015
    Date of Patent: September 17, 2019
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Patrick Marconi, Romain Thiriet, Camel Serghine
  • Twist-breakable mechanical fuse and cooling unit of a turbine engine fitted with such a fuse
    Patent number: 10408277
    Abstract: The invention relates to a mechanical fuse intended to be rigidly mounted between a drive unit (8, 9), and a receiver unit (10), each rotating about the same axis (7) of rotation, said fuse comprising a body (13) extending in a longitudinal direction parallel to said axis (7) of rotation, once the fuse is mounted between said drive unit (8, 9) and receiver unit (10). The invention is characterized in that said body (13) comprises a plurality of longitudinal bars (14), each bar (14) being deformable by bending, such as to form a twist-breakable mechanical fuse.
    Type: Grant
    Filed: December 7, 2015
    Date of Patent: September 10, 2019
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Mathieu Cladiere, Armand Bueno, Olivier Pierre Descubes, Stephane Vergez
  • DEVICE FOR LIMITING THE LOOSENING OF A NUT IN A TURBINE ENGINE
    Publication number: 20190271421
    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: Application
    Filed: December 1, 2016
    Publication date: September 5, 2019
    Applicant: Safran Helicopter Engines
    Inventors: Mathieu CLADIERE, Cedric Roger ZORDAN, Stephane VERGEZ
  • PROCESS FOR MANUFACTURING A TURBOMACHINE BLADE
    Publication number: 20190262945
    Abstract: A process for manufacturing a turbomachine blade of the type having at least one 3D cavity, wherein the blade is produced by a succession of depositions and selective consolidations of layers of a metal additive manufacturing powder based on an alloy of copper and nickel, the alloy including from 2% to 7% of nickel. It also relates to a turbomachine blade, wherein it is manufactured by metal additive manufacturing using the process.
    Type: Application
    Filed: November 10, 2017
    Publication date: August 29, 2019
    Applicant: SAFRAN HELICOPTER ENGINES
    Inventors: Yann DANIS, Denis Daniel Jean BOISSELEAU
  • Air supply plenum
    Patent number: 10392121
    Abstract: An air supply plenum for an engine, the plenum being disposed upstream of an air intake of the engine, the air intake being provided in a casing of the engine. The air supply plenum includes a first lateral wall and a second lateral wall which together form a conduit in which an air flow flows as the engine functions. Each lateral wall includes a step which forms a transverse recess relative to the direction of the air flow in the air supply plenum, such that an aerodynamic separation occurs in the step when the engine is operating.
    Type: Grant
    Filed: December 2, 2015
    Date of Patent: August 27, 2019
    Assignee: Safran Helicopter Engines
    Inventors: Nicolas Bulot, Fabrice Marchand
  • CLOGGING MONITORING IN A STARTER INJECTOR PURGE CIRCUIT FOR A TURBOMACHINE
    Publication number: 20190249604
    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: Application
    Filed: June 15, 2017
    Publication date: August 15, 2019
    Applicant: SAFRAN HELICOPTER ENGINES
    Inventors: Patrick DUCHAINE, Pascal Hubert VERDIER
  • Turboshaft engine, twin-engine helicopter equipped with such a turboshaft engine, and method for optimising the zero-power super-idle speed of such a twin-engine helicopter
    Patent number: 10371062
    Abstract: The invention relates to a turboshaft engine comprising a gas generator (5) that is capable of being rotated, and a free turbine (6) that is rotated by the gases of said gas generator (5), characterized in that it comprises a device (20) for spontaneously mechanically coupling said gas generator (5) and said free turbine (6) that is capable of mechanically and spontaneously connecting said gas generator (5) and said free turbine (6) as soon as the ratio of the rotational speed (NGG) of said gas generator to the rotational speed (NTL) of said free turbine reaches a predetermined threshold value.
    Type: Grant
    Filed: March 20, 2015
    Date of Patent: August 6, 2019
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Patrick Marconi, Romain Thiriet, Olivier Bedrine
  • AIRCRAFT TURBINE ENGINE WITH EPICYCLIC REDUCTION GEAR HAVING A VARIABLE REDUCTION RATIO
    Publication number: 20190218969
    Abstract: An aircraft turbine engine includes a rotating body comprising a compressor rotor and a turbine rotor interconnected by a rotor shaft, the turbine engine being configured to drive a member by said rotor shaft via an epicyclic reduction gear, said epicyclic reduction gear comprising a first element (50) configured to be rotationally secured to said shaft, a second element (56) rotationally secured to said member, and a third element configured to be selectively secured to a stator of the turbine engine and disengaged from the stator, wherein the turbine engine comprises driving means to rotationally drive said third element at a piloted speed when it is disengaged from said stator.
    Type: Application
    Filed: May 23, 2017
    Publication date: July 18, 2019
    Applicant: SAFRAN HELICOPTER ENGINES
    Inventors: Benjamin Fulleringer, Yannick Cazaux, Damien Lecouvreur
  • Compression assembly for a turbine engine
    Patent number: 10352179
    Abstract: Compression assembly for a turbine engine, in particular a turboshaft engine, said assembly comprising an air inlet duct capable of receiving an air flow, at least one air compression stage comprising at least one movable compressor wheel onto which the duct discharges, and a pre-rotation grille which is positioned in the air inlet duct upstream of the movable compressor wheel in order to adjust the speed of the air in said flow at the inlet of the movable wheel and comprises a plurality of variable-setting vanes, the assembly being characterized in that the pitch between two consecutive vanes of the grille is greater than the chord of one of the two vanes at a given height of the air duct, preferably in its upper part.
    Type: Grant
    Filed: November 7, 2013
    Date of Patent: July 16, 2019
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Jean-François Escuret, Pierre Biscay, Guillaume Sevestre
  • A DEVICE FOR CONTROLLING INLET GUIDE VANES BY MEANS OF A MULTILAYER PIEZOELECTRIC ACTUATOR
    Publication number: 20190211702
    Abstract: An electric actuator for inlet guide vanes of a gas turbine engine, the electric actuator including a fixed portion secured to a stationary portion of the engine and a movable portion that is mechanically connected to the inlet guide vanes, stationary electromagnets distributed at regular intervals around the periphery of the movable portion and fastened to the fixed portion, and movable electromagnets arranged between the stationary electromagnets, each movable electromagnet being secured on either side to first and second piezoelectric elements, the movable electromagnets and the first and second piezoelectric elements having a degree of freedom of movement relative to the movable portion and having inside faces forming a common line of contact that is tangential to the movable portion.
    Type: Application
    Filed: August 24, 2017
    Publication date: July 11, 2019
    Applicant: SAFRAN HELICOPTER ENGINES
    Inventors: Jean-Julien Camille VONFELT, Thomas KLONOWSKI, Antoine MOUTAUX