Patents Assigned to SAFRAN
  • Transmission assembly comprising a transmission member and an oil distribution system
    Patent number: 10215055
    Abstract: A transmission assembly including a transmission member and an oil distribution system. The transmission member includes a rotary pivot, and a pivot portion for pivoting about the rotary pivot; the oil distribution system is to receive oil feed and to transfer it to an oil reception chamber of the rotary pivot; the rotary pivot includes injection orifices putting the oil reception chamber into fluid flow communication with the gap between the rotary pivot and the pivot portion to form a fluid bearing; and the transmission assembly is for injecting oil into the gap at a first pressure into an outer portion of the gap, and at a second pressure into an inner portion of the gap, the second injection pressure being different from the first injection pressure.
    Type: Grant
    Filed: March 19, 2015
    Date of Patent: February 26, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Augustin Curlier, Yassine Krid
  • Method for repairing a fan casing
    Patent number: 10213882
    Abstract: A method for repairing a fan casing in which the inner surface is damaged, includes attaching a reinforcement element to the fan casing, the reinforcement element being attached to the outer surface of the fan casing opposite the damage.
    Type: Grant
    Filed: December 16, 2015
    Date of Patent: February 26, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Antoine Patrice Marie Desreumaux, Patrick Jean-Louis Reghezza, Sébastien Marc Jean-Michel Perez
  • Architecture of a multi-engine helicopter propulsion system and corresponding helicopter
    Patent number: 10214296
    Abstract: The invention relates to an architecture of a propulsion system of a multi-engine helicopter, comprising turboshaft engines (1, 2) that are connected to a power transmission gearbox (3), and comprising a low DC voltage onboard network (7) for supplying helicopter equipment during flight, characterized in that it comprises: a hybrid turboshaft engine (1) that is capable of operating in at least one standby mode during a stable flight of the helicopter; an electrotechnical pack (20) for quickly restarting said hybrid turboshaft engine in order to bring said engine out of said standby mode and to reach a mode in which it provides mechanical power, said restart pack (20) being connected to said onboard network (7); and at least two sources (4, 16, 18) of electrical power for said onboard network (7).
    Type: Grant
    Filed: March 20, 2015
    Date of Patent: February 26, 2019
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Fabien Mercier-Calvairac, Sophie Humbert, Stephane Beddok
  • Method for marking the surface of a mechanical part with a predefined graphical representation having a holographic effect
    Patent number: 10214040
    Abstract: A method of marking the surface of a mechanical part with a predefined graphic having a holographic type effect, the method including using a laser source to apply a succession of laser pulses to the outside surface of a part for marking, with different masks being interposed between the laser source and the outside surface of the part, each mask having a particular pattern, each laser pulse having a power density of at least 20 MW/cm2 and a duration that is less than or equal to 100 ns.
    Type: Grant
    Filed: March 26, 2015
    Date of Patent: February 26, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Pascal Fabrice Bilhe, Geoffrey Begue-Duthu
  • Method for modeling a non-axisymmetric surface
    Patent number: 10216867
    Abstract: A method for modeling at least part of a non-axisymmetric surface (5) of one portion (2) of a part (1). The portion (2) is bounded by first and second extremal planes (PS, PR). The method includes processing data from a device (10), by: (a) modeling at least two basic non-axisymmetric surfaces (Sk, SI, SE) making up the surface, each of the basic surfaces (Sk, SI, SE) extending between both extremal planes (PS, PR) of the portion (S); (b) constructing at least one connection curve (CR) tangential to the first and second surfaces; (c) locally modifying the first and second basic surfaces (Sk, SI, SE) to keep to the connection curve (CR) near a discontinuity; and (d) restoring, at least part of the obtained surface (5).
    Type: Grant
    Filed: July 7, 2014
    Date of Patent: February 26, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Damien Joseph Cellier, Vincent Perrot, Matthieu Jean Luc Vollebregt, Nicolas Jean Fernand Pignier
  • Constant-volume combustion (CVC) chamber for an aircraft turbine engine including an intake/exhaust valve having a spherical plug
    Patent number: 10215092
    Abstract: A constant-volume combustion chamber for an aircraft turbine engine, including a compressed gas intake valve configured to adopt an open position and a closed position, and in the closed position blocking intake of compressed gas into the chamber, and a combusted gas exhaust valve configured to adopt a closed position, in the closed position blocking exhaust of combusted gas outside the chamber. At least one of the intake and exhaust valves includes at least one spherical plug.
    Type: Grant
    Filed: July 30, 2013
    Date of Patent: February 26, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventor: Bernard Robic
  • Passenger seat
    Patent number: 10214127
    Abstract: Described are passenger seat assemblies including spreaders with a transitional region having a forward surface with a radius of curvature of about 3.5 to 3.7 inches and an aft surface with an angular profile configured so that the aft surface is located forward of a plane formed by a surface of the at least one seat back in a fully upright position. The passenger seat assemblies also include leg assemblies with a forward leg portion having a forward surface that is substantially aligned with a forward base frame tube, and an aft surface with an angular profile having a shape of an “r.
    Type: Grant
    Filed: May 17, 2017
    Date of Patent: February 26, 2019
    Assignee: Safran Seats USA LLC
    Inventors: Jeffrey P. Wegenka, Allen Shirey, Aram Krikorian
  • A BLADE PLATFORM AND A FAN DISK FOR AN AVIATION TURBINE ENGINE
    Publication number: 20190055847
    Abstract: A platform suitable for being interposed between two adjacent blades of a fan, and including a passage wall, a bottom wall, and axial and radial retention surfaces. The passage wall defines a fan air flow passage, the bottom wall presents a main surface for bearing against a fan disk, and the axial and radial retention surfaces are arranged at the two axial ends of the platform. The radial retention surface arranged at the upstream axial end of the platform is radially offset from the main surface of the bottom wall in the direction in which the bottom wall bears against the disk.
    Type: Application
    Filed: March 20, 2017
    Publication date: February 21, 2019
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Thomas Alain DE GAILLARD, ALEXANDRE Bernard Marie BOISSON
  • TOOL FOR MACHINING WELLS IN MULTl-STAGE DISCS BY PECM, ELECTROCHEMICAL MACHINING ASSEMBLY AND MACHINE INCLUDING SAID TOOL, AND METHOD USING SAID TOOL
    Publication number: 20190054555
    Abstract: Tooling (10) for making slots in a multistage disk (1) by electrochemical machining. The tooling comprises first and second rings (20) arranged coaxially about a disk axis and configured to act as cathodes, each ring having an inside periphery with a plurality of radial machining projections. The first and second rings (20) are rigidly secured relative to each other. A method of making slots in a multistage disk by electrochemical machining using such a tool.
    Type: Application
    Filed: October 7, 2016
    Publication date: February 21, 2019
    Applicants: SAFRAN AIRCRAFT ENGINES, PEMTEC
    Inventors: Janvier LECOMTE, Mickael RANCIC, Sophie TALLON, Juri KRAFT, Andreas GRUTZMACHER
  • Turbomachine Lubrication Unit and Method of Manufacture
    Publication number: 20190055854
    Abstract: An aircraft bypass turbojet engine lubrication unit includes from three to five superposed pumps, a body housing the pumps and an internal passage in the body for communicating with each of the pumps. The material of the body exhibits a stack of layers in a direction of stacking, the pumps being housed in the said stack of layers. The passage exhibits an end in the direction of stacking of the layers and an internal profile, for example triangular, with two straight lines which form the said end and which are inclined with respect to the stacked layers. The lubrication unit may be manufactured by additive manufacturing in layers.
    Type: Application
    Filed: July 30, 2018
    Publication date: February 21, 2019
    Applicant: SAFRAN AERO BOOSTERS SA
    Inventors: Mathieu Chenoux, Nicolas Fellin
  • METHOD FOR MANUFACTURING A TURBINE SHROUD FOR A TURBOMACHINE
    Publication number: 20190054537
    Abstract: The invention relates to a method for manufacturing a turbine shroud (24) for a turbomachine, the method comprising manufacturing at least one turbine shroud sector (28), positioning the turbine shroud sector (26) in a bottom mold so that an outer surface of the turbine shroud sector is in contact at least in part with the bottom mold, and depositing a powder layer on an inner surface (28) of the turbine shroud sector (26). Thereafter, a top mold is positioned on the powder layer and an abradable layer (32) is made by subjecting the powder layer to a method of SPS sintering, the abradable layer (32) being for being disposed facing a turbine wheel.
    Type: Application
    Filed: March 10, 2017
    Publication date: February 21, 2019
    Applicants: SAFRAN AIRCRAFT ENGINES, CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE, UNIVERSITE PAUL SABATIER - TOULOUSE III
    Inventors: Jean-Baptiste MOTTIN, Yannick Marcel BEYNET, Geoffroy CHEVALLIER, Romain EPHERRE, Claude ESTOURNES
  • DRIVE TRAIN
    Publication number: 20190055011
    Abstract: A drive train for a helicopter, which includes an engine, a reduction gear and a main gearbox, the reduction gear including an output shaft, which are received in assembled front and rear housings, the output shaft being supported and guided rotatably by a plurality of rolling bearings, mounted in the housings. The drive train includes a redundant mount arranged around the output shaft and between a wall of the main gearbox and the front end of the front housing, and the redundant mount is configured, sized and attached to the wall of the main gearbox and to the front end of the front housing so as to create, if the front housing breaks, a secondary path for absorbing loads passing via the redundant mount, via the output shaft of the reduction gear and via the bearings.
    Type: Application
    Filed: February 7, 2017
    Publication date: February 21, 2019
    Applicant: SAFRAN TRANSMISSION SYSTEMS
    Inventors: Thomas Marie Joseph DE DREUILLE DE LONGEVILLE, Frederic Nicolas Francois LAISNEZ
  • Method and device for regulating the cooling of oil in a turbomachine
    Patent number: 10208669
    Abstract: A method for regulating oil cooling within an oil cooling device of a turbomachine including a first heat exchanger mounted in series with a second heat exchanger, the first heat exchanger being an oil/air exchanger while the second heat exchanger is an oil/fuel exchanger, each heat exchanger having an oil inlet and an oil outlet, a bypass directly connecting the oil inlet of the first heat exchanger to the oil outlet of the first heat exchanger, and a flow regulator to regulate the flow rate of oil flowing through the bypass. Circulation of oil though the bypass is allowed by means of the flow regulator when the oil temperature is less than or equal to a predetermined temperature comprised between 70° C. and 90° C., preferably equal to about 80° C.
    Type: Grant
    Filed: February 24, 2014
    Date of Patent: February 19, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Sebastien Gameiro, Brice Andre, Guillaume Mathon Margueritte, Nicolas Potel
  • Landing gear comprising a zinc-nickel deposit resistant to fretting
    Patent number: 10207796
    Abstract: A landing gear (1) for aircraft comprising a first pair of first and second parts (7, 8, 7?, 8?), said first part (7, 7?) having a steel substrate and a sliding layer (C, C?) formed on this substrate, the second part (8, 8?) being in sliding contact against said sliding layer (C, C?) with a maximum rectilinear sliding amplitude (G, G?) of less than 0.5 mm, the sliding layer (C, C?) being adapted to support a surface pressure in excess of 50 MPa. The sliding layer (C, C?) is a zinc and nickel alloy comprising, in terms of percentage by weight of the alloy, between 12% and 18% nickel and the first part has a protective layer (P, P?) against corrosion extending from the sliding layer (C, C?), this protective layer (P, P?) being formed of said zinc and nickel alloy.
    Type: Grant
    Filed: June 30, 2016
    Date of Patent: February 19, 2019
    Assignee: SAFRAN LANDING SYSTEMS
    Inventors: Sacha Mierzejewski, Romain Ottenio
  • Fluidic valve
    Patent number: 10208873
    Abstract: A fluid valve is suitable for use with a hydraulic circuit of an item of aircraft equipment. The fluid valve includes a valve body having one inlet, two outlets and a communication channel with an external pressure source. The fluid valve further includes an electric solenoid actuator located in the valve body and having a movable ferromagnetic pilot. A valve member is movable inside valve body to at least partially block a passage between said inlet and one of the two outlets. The valve member at least partially defines first and second cavities. A fixed limiter is disposed within the communication channel such that a displacement of the movable pilot causes a variation in pressure in one of the first and second cavities to produce a force for moving the valve member.
    Type: Grant
    Filed: August 2, 2016
    Date of Patent: February 19, 2019
    Assignee: Safran Aero Boosters S.A.
    Inventors: Cédric Frippiat, Jean-Christian Bomal, Nicolas Paulus
  • Starter-generator brush
    Patent number: 10211585
    Abstract: A brush for a starter-generator includes a first carbon block, a second carbon block, a terminal lug, and a plurality of brush leads. Each carbon block has an outboard edge and an inboard edge. Each carbon block includes a front carbon wafer and a rear carbon wafer. Front brush leads connect the terminal lug with the front carbon wafers of the respective carbon blocks adjacent the inboard edges of the respective carbon blocks. Rear brush leads connect the terminal lug with the rear carbon wafers of the respective carbon blocks adjacent the outboard edge of the respective carbon blocks.
    Type: Grant
    Filed: March 2, 2016
    Date of Patent: February 19, 2019
    Assignee: SAFRAN ELECTRICAL & POWER
    Inventors: Regan Scott Robinault, Donald Orville Kodger
  • Overspeed protection device of an aircraft engine
    Patent number: 10208620
    Abstract: The invention relates to an overspeed protection device of an aircraft engine.
    Type: Grant
    Filed: July 21, 2015
    Date of Patent: February 19, 2019
    Assignees: SAFRAN ELECTRONICS & DEFENSE, SAFRAN HELICOPTER ENGINES
    Inventors: Michael Montoya, Nicolas Marti, Stephen Langford, Rafael Samson
  • Abradable Seal Composition for Turbomachine Compressor
    Publication number: 20190048454
    Abstract: A composition for an abradable seal for a turbomachine, in particular in powder form, is able to crumble in the event of contact with a rotor of said turbomachine. The seal is formed on the arcuate wall of a substrate casing. The composition includes a majority metallic phase with a majority by mass of aluminium with some chromium, a minority second phase including a mineral material and/or an organic material.
    Type: Application
    Filed: August 13, 2018
    Publication date: February 14, 2019
    Applicant: SAFRAN AERO BOOSTERS SA
    Inventor: Laurent Schuster
  • EQUIPMENT DRIVE GEARBOX IN A TURBOMACHINE
    Publication number: 20190048801
    Abstract: A drive gearbox for turbomachine equipment, the drive gearbox having a main shaft intended to be rotationally connected to a power transmission shaft of a turbomachine. The main shaft has at least one bevel gear rotationally driving at least one piece of equipment. The gearbox has gear set with cylindrical gearwheels that have an input connected to the rotational drive to the main shaft and a plurality of outputs each intended to drive a piece of equipment. The gear set extends over an angular sector and the outputs are angularly spaced apart along the angular sector.
    Type: Application
    Filed: September 13, 2016
    Publication date: February 14, 2019
    Applicant: Safran Transmission Systems
    Inventors: Maxence Guillemont, Fanelle Drevon, Julien Viel
  • HUB FOR PROPELLER HAVING VARIABLE-PITCH BLADES, WITH RADIAL AND AXIAL DIMENSIONING VARIATION
    Publication number: 20190048888
    Abstract: A hub for a propeller having variable-pitch blades for a turbomachine with longitudinal rotation axis, including a plurality of blade platforms, each one being designed to receive a blade root, the platforms being distributed around the annular outer periphery of the hub concentrically with the longitudinal rotation axis, wherein each blade platform has the general geometric shape of a spherical cap, and wherein, between two adjacent blade platforms around the longitudinal rotation axis, the transverse dimension, in particular the diameter, of the hub can vary axially and radially.
    Type: Application
    Filed: February 20, 2017
    Publication date: February 14, 2019
    Applicant: Safran Aircraft Engines
    Inventors: Paul Antoine FORESTO, Vivien Mickaël COURTIER, Christophe Paul JACQUEMARD