Patents Assigned to SAFRAN
  • Sealing device between an injection system and a fuel injection nozzle of an aircraft turbine engine
    Patent number: 10495312
    Abstract: An arrangement for an aircraft turbine engine combustion chamber including an injection system and a fuel injector is provided. The injection system includes an injector nozzle guide, the inner surface of which delimits an opening for centering the nozzle, which includes an outer casing. The arrangement further includes a sealing device between the inner surface of the guide and the outer casing. The sealing device includes a first part accommodated in a groove of the outer casing, the groove being delimited, in part, by a downstream delimiting surface, the first part having a first sealing surface and bearing axially against the downstream delimiting surface; and a second part having a second sealing surface bearing radially against the inner surface of the guide.
    Type: Grant
    Filed: January 18, 2016
    Date of Patent: December 3, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Jose Roland Rodrigues, Christophe Chabaille
  • Propeller pitch control system
    Patent number: 10494084
    Abstract: A control system for controlling the pitch of a propeller, the system including a propeller shaft, a blade swivel device having a rotary control element suitable for placing the blades in an angular position corresponding to a desired propeller pitch, and a transmission presenting an outlet member coupled in rotation with the rotary control element of the blade swivel device. The transmission includes a variable speed drive having drive, control, and outlet rotors that are coupled in rotation respectively with the propeller shaft, with a control member, and with the outlet member of the transmission. With the variable speed drive, the speed of rotation of the outlet member of the transmission is a predetermined function of the speeds of rotation not only of the propeller shaft, but also of the control member.
    Type: Grant
    Filed: March 28, 2017
    Date of Patent: December 3, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventor: Alain Pierre Garassino
  • Unit for moulding a turbomachine blade, comprising a raised portion with a large cross-section
    Patent number: 10493520
    Abstract: A moulding unit for producing a turbomachine blade blank. The moulding unit has an upstream portion and a downstream portion. According to the invention, the moulding unit comprises a raised portion designed to form a downstream opening which, at the level of the trailing edge, passes through at least one of the side edges of the basin-like portion at the blade tip. The raised portion rigidly secures the upstream portion to the downstream portion and comprises a strengthening protuberance extending in the transverse direction.
    Type: Grant
    Filed: June 27, 2016
    Date of Patent: December 3, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Matthieu Jean Luc Vollebregt, Charlotte Marie Dujol, Patrice Eneau, Coralie Geurard, Patrick Emilien Paul Emile Huchin
  • Switch with customized circuit board electrical contact pad placement using selectively mounted electrical contactors
    Patent number: 10497527
    Abstract: A modular auxiliary switch includes a housing including a first housing part and a separate second housing part secured to the first housing part. A printed circuit board is housed in one of the first and second housing parts, and has a first side facing the first housing part and a second opposite side facing the second housing part. An actuator mechanism is housed in the first housing part and is coupled to the printed circuit board. A separate first electrical contactor is selectively mounted to the printed circuit board so that a first electrical contact surface of the first electrical contactor overlaps and is in direct contact with one of the first side and the second side to define a first electrical contact pad on the printed circuit board.
    Type: Grant
    Filed: April 23, 2018
    Date of Patent: December 3, 2019
    Assignee: SAFRAN ELECTRICAL & POWER
    Inventors: Christopher Kenneth Wyatt, James Broadwell, Dean Morgan
  • Turbomachine with multi-diameter propeller
    Patent number: 10494086
    Abstract: A turbomachine including at least two unducted propellers, one of which is an upstream propeller and one a downstream propeller, the upstream propeller including a plurality of blades, at least one first blade of which has a different length from that of a second blade.
    Type: Grant
    Filed: December 17, 2015
    Date of Patent: December 3, 2019
    Assignee: Safran Aircraft Engines
    Inventors: Laurence Francine Vion, Mathieu Simon Paul Gruber
  • System for clamping a part and method for sealing the inner casing of a low pressure rectifier of a turbomachine
    Patent number: 10493600
    Abstract: The invention relates to a clamping system (1) comprising a clamping jaw (7) mounted on the shaft of a pneumatic or hydraulic cylinder (4), wherein said cylinder has a structure which drives the clamping jaw towards its clamping position when the pneumatic or hydraulic energy supply of the cylinder is interrupted, the pneumatic or hydraulic energy supply of the cylinder opposing the clamping, and where means (8) are provided for locking the cylinder when the clamping jaw is in a non-clamped position.
    Type: Grant
    Filed: February 12, 2015
    Date of Patent: December 3, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Romain Rene Marcel Chardonnet, Jean-Yves Francois Henri Maillet, Erwan Soubigou
  • AIRCRAFT TURBINE ENGINE WITH A PAIR OF ROTATING AND NON-DUCTED PROPELLERS
    Publication number: 20190359315
    Abstract: An aircraft turbine engine has a pair of rotating and non-ducted propellers. An upstream propeller has an outer diameter D1 and a downstream propeller has an outer diameter D2. The engine further includes a system for varying the diameter D2. The downstream propeller includes an annular row of blades, each of which is configured to be mounted telescopically in the radial direction (R) in an outer fan duct.
    Type: Application
    Filed: May 22, 2019
    Publication date: November 28, 2019
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventor: Anthony Binder
  • MULTIELEMENT METHOD AND DEVICE FOR TESTING PARTS WITH ULTRASOUND
    Publication number: 20190360969
    Abstract: A method for nondestructively testing a part comprising an elongate microstructure is disclosed.
    Type: Application
    Filed: January 23, 2018
    Publication date: November 28, 2019
    Applicants: SAFRAN, CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE, ECOLE SUPERIEURE DE PHYSIQUE ET DE CHIMIE INDUSTRIELLES DE LA VILLE DE PARIS
    Inventors: Aurélien Baelde, Frédéric Jenson, Mathias Fink, Jérôme Laurent, Claire Prada
  • PASSENGER SEAT ENTERTAINMENT SYSTEM
    Publication number: 20190359334
    Abstract: A passenger seat, such as an aircraft passenger seat, includes a seat base and an entertainment system. The seat base includes a cushioning member and a cover covering the cushioning member. The entertainment system is positioned between the cushioning member and the cover and is removably connected to the cushioning member. The entertainment system is configured to determine a force caused by a passenger's legs in at least two locations on an upper surface of the seat base when used.
    Type: Application
    Filed: August 11, 2017
    Publication date: November 28, 2019
    Applicant: Safran Seats USA LLC
    Inventors: Lukas Riedel, Domenico Iacoviello, Emma Erkelens, Emma Wisse, David Randles, Max Kersten
  • Self-contained device for storing and releasing energy in order to power a piece of electrical equipment
    Patent number: 10487809
    Abstract: The invention relates to an autonomous device (10) for storing and releasing energy in order to power a piece of electrical equipment (12), in particular a piece of electrical equipment (12) of an aircraft, characterised in that said device comprises: a first means (16), configured to transform a variation in the surrounding pressure (P) to which the device (10) is subject into mechanical energy, at least one second means (20, 22), configured to mechanically store said mechanical energy by transforming same into the form of mechanical potential energy, a third means (24), configured to control the release of the mechanical potential energy contained in said second means (20, 22) and transform same into restored mechanical energy, a fourth means (28), configured to transform the restored mechanical energy into electrical energy suitable for powering said piece of electrical equipment (12).
    Type: Grant
    Filed: July 15, 2016
    Date of Patent: November 26, 2019
    Assignee: SAFRAN AIRCRAFTS ENGINES
    Inventors: Francois Prost, William Bense
  • Modular assembly for a turbine engine
    Patent number: 10487747
    Abstract: A modular assembly for a turbine engine has an annular bearing support that is configured to be connected to a first anti-friction bearing, which is configured to be fitted around a first shaft of the turbine engine. The modular assembly further includes a second anti-friction bearing configured to be fitted around a second shaft of the turbine engine, wherein the second shaft is not parallel to said first shaft.
    Type: Grant
    Filed: April 28, 2015
    Date of Patent: November 26, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Augustin Curlier, Kevin Morgane Lemarchand, Nathalie Nowakowski, Thomas Alain Christian Vincent
  • Front lip of a turbofan engine nacelle comprising hot-air bores upstream from acoustic panels
    Patent number: 10487738
    Abstract: A front lip of a turbofan engine nacelle is provided, defined at the rear by a partition wall, the lip comprising an annular de-icing space including a tube for supplying hot air in order to de-ice the outer walls thereof, said lip also including acoustic panels arranged on the wall thereof substantially radially facing the axis of the nacelle. The front lip includes hot-air outlet bores/piercings which are arranged between the front end of the lip and said acoustic panels, which allow a flow of hot air, from said annular space, forming a substantially regular film which covers said acoustic panels with a boundary layer in order to heat said acoustic panels.
    Type: Grant
    Filed: January 11, 2017
    Date of Patent: November 26, 2019
    Assignee: SAFRAN NACELLES
    Inventors: Marc Versaevel, Arnaud Delehouze, Laurence Lemains, Pierre-François Behaghel
  • Method and device for mounting an engine on an aircraft pylon
    Patent number: 10486819
    Abstract: The invention relates to a method for mounting an engine (1) on an aircraft strut (3) comprising engine suspension members (31) integral with the strut, the engine being integral with a suspension cradle (6) whereby it is suspended from the strut, the method comprising a step of hoisting the engine in a vertical direction as far as the strut then a step of approaching the strut by a movement of the engine in another direction, characterised in that an intermediate part (7) is fixed to the strut beforehand, by attaching it to said suspension members (31), said intermediate part (7) having an interface intended to cooperate with a complementary interface provided on the cradle (6), in such a way as to position the cradle relative to the intermediate part at the end of the approach movement to the strut. The invention also relates to the system for implementing the method.
    Type: Grant
    Filed: September 16, 2015
    Date of Patent: November 26, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Mario Lambey, Bruno Albert Beutin, Marc Patrick Tesniere
  • Turbine casing comprising ring sector attachment means
    Patent number: 10487689
    Abstract: An aircraft turbine casing configured to carry a set of ring sectors that partly delimits a conduit inside which a gas flow passes through the turbine, including a dynamic mechanism adjusting radial position of ring sectors, an upstream radial lug that connects an upstream end of each ring sector to the casing, and a downstream radial lug that connects a downstream end of each ring sector to the casing. The upstream lug is made as a single piece with the casing and is directly connected to the upstream end of each ring sector.
    Type: Grant
    Filed: March 6, 2012
    Date of Patent: November 26, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Damien Bonneau, Jean-Christophe Marc Cordier, Fabrice Marcel Noel Garin
  • Method for monitoring an aircraft engine operating in a given environment
    Patent number: 10486833
    Abstract: The present invention relates to method for monitoring an engine (1) of an aircraft (2) operating in a given environment. The invention is characterized in that it comprises the implementation, via means for data processing (31), of the steps of: (a) receiving a sequence of n-tuples (x1-exec. . . xn-exec; yexec) of physical-parameter values relating to said aircraft (2) engine (1), including at least one endogenous parameter specific to the operation of the engine (1) and at least one exogenous parameter specific to said environment; (b) For each n-tuple (x1-exec. . . xn-exec, yexec) of the received sequence, calculating, according to a regression model, a standardized value (yexec-norm) of the endogenous parameter in relation to the exogenous parameters; (c) identifying at least one stabilized phase in said normalized sequence of n-tuples (x1-exec. . .
    Type: Grant
    Filed: November 10, 2015
    Date of Patent: November 26, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Aurelie Gouby, Guillaume Bothier
  • Plug for rotating inlet cowl of a turbo machine including an aerodynamic external wall and a cone attachment element
    Patent number: 10487736
    Abstract: A rotating inlet cowl for a turbomachine, comprises a cone, a shell and a plug. The plug comprises an external wall with an external surface that will form an aerodynamic profile in continuity with an external surface of an external wall of the cone, when the external wall closes off a cavity that is formed between the external wall of the cone and the shell. The plug comprises an internal wall of the support and an attachment device. The attachment device is configured to pass through the support and to rigidly fix the support wall to an internal wall of the cone and the internal wall of the cone to the shell simultaneously, through an orifice in the external wall.
    Type: Grant
    Filed: February 23, 2018
    Date of Patent: November 26, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventor: Régis Eugène Henri Servant
  • Turbomachine combustion chamber
    Patent number: 10488049
    Abstract: The invention relates to a combustion chamber for a turbomachine, such as an aircraft turbojet engine or turboprop engine, comprising an internal annular shroud and an external annular shroud which at their upstream ends are connected by an annular chamber end wall (48), said chamber comprising deflectors (50) mounted upstream of the annular chamber end wall (48). Injectors (19) are mounted in sleeves (44) at least one of which comprises a radially annular flange (66) which is designed to slide radially between the chamber end wall (48) and the deflector (50) and which is blocked axially between the chamber end wall (48) and the deflector (50).
    Type: Grant
    Filed: September 29, 2015
    Date of Patent: November 26, 2019
    Assignee: Safran Aircraft Engines
    Inventors: Romain Nicolas Lunel, Thomas Olivier Marie Noel, Matthieu François Rullaud
  • Core for manufacturing a turbomachine blade
    Patent number: 10486226
    Abstract: A core used in the manufacture, by lost-wax casting, of a turbomachine blade, includes a main element and at least one first secondary element, each including a functional part and a non-functional part. The non-functional part of the main element and the non-functional part of the at least one first secondary element are assembled and shaped so as to cooperate with each other by sliding in a longitudinal direction extending between the base and the top of a blade and by rotating around the longitudinal direction.
    Type: Grant
    Filed: April 26, 2018
    Date of Patent: November 26, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Daniel Quach, Pascal Francis Patrick Gomez, Coralie Cinthia Guerard, Jean-Claude Marcel Auguste Hanny, Patrick Emilien Paul Emile Huchin, Joseph Toussaint Tami Lizuzu, Matthieu Jean Luc Vollebregt, Vincent Marc Herb, Laetitia Person
  • De-icing splitter lip for axial turbomachine compressor
    Patent number: 10487737
    Abstract: The present application relates to a de-icing splitter lip for a low-pressure compressor of a turbofan aircraft engine. The splitter lip surrounds the primary flow and includes an annular splitter wall with a circular leading edge, an outer shroud connected to the splitter wall, and a heating device in an electric ribbon that de-ices the splitter lip. The splitter lip further includes an elastic element made of elastomer, holding the heating device on the inside of the splitter wall. The elastic element is compressed, pre-loaded, in the splitter lip. Thus, the elastic element exerts a force F clamping the heating device against the splitter wall and the outer shroud in order to improve thermal contact. The present application also provides a method for assembling a splitter lip.
    Type: Grant
    Filed: April 18, 2016
    Date of Patent: November 26, 2019
    Assignee: SAFRAN AERO BOOSTERS SA
    Inventors: David Bouillon, Ghislain Herbaut
  • System for detecting an ephemeral event on a vane impeller of an aircraft engine
    Patent number: 10487683
    Abstract: A method and a system for monitoring an ephemeral event on a vane impeller of an aircraft engine are provided. The method includes: acquiring a time signal relating to movable vanes of the vane impeller; and detecting a disturbance in the time signal with respect to a reference time signal corresponding to a same flight phase, the disturbed time signal being indicative of an ephemeral event on said vane impeller. A system is provided to carry out this method.
    Type: Grant
    Filed: November 22, 2011
    Date of Patent: November 26, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Valerio Gerez, Serge Blanchard