Patents Assigned to Safran Aero Boosters S.A.
  • Patent number: 10683863
    Abstract: An internal gear pump includes a pinion, a ring arranged around the pinion, and a cylindrical wall arranged around the ring. A support element, on which the pinion and the ring are supported, carries high-pressure liquid towards a recess located at the junction between the ring and the cylindrical wall, and also carries low-pressure liquid towards another recess located at another point of the junction between the ring and the cylindrical wall. The recess allows the load of the ring on the cylindrical wall to be reduced.
    Type: Grant
    Filed: June 27, 2017
    Date of Patent: June 16, 2020
    Assignee: Safran Aero Boosters S.A.
    Inventors: Albert Cornet, Mathieu Chenoux
  • Publication number: 20200109661
    Abstract: The disclosed technology concerns an aircraft turbomachine part comprising a part body drilled with at least one cavity open to the outside and at least one conduit joining the cavity on the one hand and leading to the outside on the other hand. Each cavity receives a pressure sensor, and the conduit corresponds to the cavity guides the cables connected to the sensor to the outside of the part body. The part is an aircraft turbomachine vane.
    Type: Application
    Filed: October 3, 2019
    Publication date: April 9, 2020
    Applicant: Safran Aero Boosters S.A.
    Inventors: Nicolas Raimarckers, Maxime Dumont, Rafael Perez, Frédéric Vallino
  • Patent number: 10533842
    Abstract: A system for contactless measurement of circular geometrical parameters of a turbine engine component, comprising a contactless measurement module comprising a support, having a fixed position, for supporting the turbine engine component; an optical measurement device for transmitting a plurality of light beams onto at least the internal surface of the internal side wall, and for acquiring a plurality of reflections coming from the plurality of light beams, mechanically coupled to the support and comprising: an electronic conversion unit for converting a plurality of signals of the first optical sensor into a plurality of values of the plurality of circular geometrical parameters.
    Type: Grant
    Filed: October 17, 2017
    Date of Patent: January 14, 2020
    Assignee: Safran Aero Boosters S.A.
    Inventors: Romain Assemat, Jean-Michel Lorange
  • 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
  • Patent number: 10190437
    Abstract: A test bench for an aircraft turbojet engine is provided. The test bench comprises a U-shaped configuration with a passage in the form of an elongated corridor, an inlet duct, and an outlet duct. The corridor comprises a fixing zone with a fixing arm for holding a turbojet engine during testing. The passage furthermore has an upstream shutter with vertical pivoting air guides and a downstream shutter with an inflatable balloon in a collector tube. In the event of fire, the shutters close to confine the turbojet engine in order to suffocate the fire rapidly. A method for managing a fire in a test bench with a passage is also provided. Shutters are placed in the passage, where they deploy.
    Type: Grant
    Filed: March 7, 2016
    Date of Patent: January 29, 2019
    Assignee: Safran Aero Boosters S.A.
    Inventor: Gaetano Taccogna
  • Patent number: 10105770
    Abstract: A method for selecting a milling cutter, which method makes it possible to select a milling cutter on the basis of a part to be machined such that the cutting force is constant while the part is being machined.
    Type: Grant
    Filed: January 20, 2017
    Date of Patent: October 23, 2018
    Assignee: SAFRAN AERO BOOSTERS S.A.
    Inventor: Eric Englebert
  • Publication number: 20180281066
    Abstract: The present invention relates to a three-dimensional printer in which a localized powder flow is deposited on a construction surface. The three-dimensional printer comprises an electrostatic charge detector for measuring a characteristic of an electrostatic charge of the powder flow, for example the electrostatic charge thereof or the electrostatic charge thereof per unit of time. Said detector makes it possible to prevent explosions caused by the accumulation of electrostatic charge.
    Type: Application
    Filed: March 28, 2018
    Publication date: October 4, 2018
    Applicant: Safran Aero Boosters S.A.
    Inventors: Laurent Schuster, Eric Englebert
  • Patent number: 10082038
    Abstract: The invention relates to an axial turbomachine compressor outer casing. The casing comprises a sealing device collaborating with a row of rotor blades. The casing comprises a wall with an annular groove in which the sealing device is housed. The sealing device comprises a segmented outer shroud and a plurality of piezoelectric actuators moving the shroud radially in the groove so as to open or close the functional clearance. The invention also proposes a method for controlling a sealing device for a turbojet engine, the method comprising a step of measuring the altitude and a step of adjusting a clearance according to the altitude.
    Type: Grant
    Filed: September 14, 2015
    Date of Patent: September 25, 2018
    Assignee: Safran Aero Boosters S.A.
    Inventors: Jean-Francois Cortequisse, Philippe Minot
  • Publication number: 20180106603
    Abstract: A system for contactless measurement of circular geometrical parameters of a turbine engine component, comprising a contactless measurement module comprising a support, having a fixed position, for supporting said turbine engine component; an optical measurement device for transmitting a plurality of light beams onto at least said internal surface of said internal side wall, and for acquiring a plurality of reflections coming from said plurality of light beams, mechanically coupled to said support and comprising: an electronic conversion unit for converting a plurality of signals of said first optical sensor into a plurality of values of said plurality of circular geometrical parameters.
    Type: Application
    Filed: October 17, 2017
    Publication date: April 19, 2018
    Applicant: Safran Aero Boosters S.A.
    Inventors: Romain Assemat, Jean-Michel Lorange
  • Publication number: 20180094745
    Abstract: A fluid valve includes a valve member located between a first cavity and a second cavity, and an actuator that includes a pilot. The valve member is moved by the balance between the pressure prevailing in the first cavity and the pressure prevailing in the second cavity. The valve member includes a longitudinal hole that can be blocked by the pilot so as to modify the pressure prevailing in the first cavity and the force acting on the valve member so as to vary a fluid flow rate between an inlet and two outlets. The valve member is attached to a piston, one end of which is located in a third cavity. The force acting on the valve member is determined by the pressures prevailing in the various cavities.
    Type: Application
    Filed: September 29, 2017
    Publication date: April 5, 2018
    Applicant: SAFRAN AERO BOOSTERS S.A.
    Inventors: Cédric Frippiat, Jean-Christian Bomal, Nicolas Paulus
  • Publication number: 20180003173
    Abstract: An internal gear pump includes a pinion, a ring arranged around the pinion, and a cylindrical wall arranged around the ring. A support element, on which the pinion and the ring are supported, carries high-pressure liquid towards a recess located at the junction between the ring and the cylindrical wall, and also carries low-pressure liquid towards another recess located at another point of the junction between the ring and the cylindrical wall. The recess allows the load of the ring on the cylindrical wall to be reduced.
    Type: Application
    Filed: June 27, 2017
    Publication date: January 4, 2018
    Applicant: Safran Aero Boosters S.A.
    Inventors: Albert Cornet, Mathieu Chenoux
  • Publication number: 20170369174
    Abstract: An aircraft comprising a turbine engine, an atomizer, a reservoir, a conduit connecting the reservoir to the atomizer, and a unit for controlling the flow of liquid in the atomizer. The turbine engine, the atomizer, the reservoir, the conduit and the control unit are fixed to the aircraft. This allows cleaning in flight of at least some parts of the turbine engine.
    Type: Application
    Filed: June 27, 2017
    Publication date: December 28, 2017
    Applicant: SAFRAN AERO BOOSTERS S.A.
    Inventor: Mathieu Deladriere
  • Publication number: 20170209945
    Abstract: A method for selecting a milling cutter, which method makes it possible to select a milling cutter on the basis of a part to be machined such that the cutting force is constant while the part is being machined.
    Type: Application
    Filed: January 20, 2017
    Publication date: July 27, 2017
    Applicant: SAFRAN AERO BOOSTERS S.A.
    Inventor: Eric Englebert
  • Publication number: 20170211400
    Abstract: Stator vane for a turbine engine and including at least one portion made from material suitable for superelasticity. The portion made from material suitable for superelasticity is arranged so as to start to resonate at a predetermined speed of the turbine engine, in particular during a speed of the turbine engine typical of the cruising phase of the aircraft.
    Type: Application
    Filed: January 19, 2017
    Publication date: July 27, 2017
    Applicant: SAFRAN AERO BOOSTERS S.A.
    Inventor: Frédéric Vallino
  • Publication number: 20170211412
    Abstract: System for maintaining a turbine engine comprising said turbine engine of an aircraft comprising: an oil reservoir, a sensor able to measure an oil level in the oil reservoir, a transmission device, such as electrical wires, wireless transmitter circuit, etc., for transmitting a signal coupled to said sensor in order to transmit information relating to an oil level measured by said sensor, communication means, such as a display or a near field communications circuit coupled to said transmission devices, for communicating to the outside of the aircraft information representing an oil level measured by said sensor. The maintenance system further comprises a mobile apparatus able to communicate with said communication means and comprising a display for displaying said information representing an oil level to an operator situated on the ground outside the aircraft.
    Type: Application
    Filed: January 19, 2017
    Publication date: July 27, 2017
    Applicant: SAFRAN AERO BOOSTERS S.A.
    Inventors: Nicolas Raimarckers, Vincent Thomas, Bruno Servais
  • Publication number: 20170037984
    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: Application
    Filed: August 2, 2016
    Publication date: February 9, 2017
    Applicant: Safran Aero Boosters S.A.
    Inventors: Cédric Frippiat, Jean-Christian Bomal, Nicolas Paulus