Patents Assigned to SAFRAN AERO BOOSTERS
  • Measuring System for Turbine Engine
    Publication number: 20200088600
    Abstract: A measuring system for a turbine engine includes a piezoresistive sensor and an analysis module, the sensor and the module being such that the module can determine, from measuring two electrical voltages, a pressure value (p) and a temperature value (T) in the vicinity of the sensor. The sensor can include a Wheatstone bridge arranged on a flexible membrane.
    Type: Application
    Filed: September 17, 2019
    Publication date: March 19, 2020
    Applicant: SAFRAN AERO BOOSTERS SA
    Inventors: Nicolas Raimarckers, Frederic Vallino
  • Icephobic Vane for a Compressor of an Axial Turbine Engine
    Publication number: 20200080433
    Abstract: The invention relates to an anti-icing turbomachine blade (26), in particular for a low-pressure compressor or an intermediate-pressure compressor of a turbomachine. The blade (26) has a leading edge (28) formed by an ice-phobic surface (40) and two hydrophobic surfaces (42; 44) which extend the ice-phobic surface (40) on the pressure side (32) and the suction side (34) to allow water droplets escaping from the leading edge (28) to flow.
    Type: Application
    Filed: November 8, 2017
    Publication date: March 12, 2020
    Applicant: SAFRAN AERO BOOSTERS SA
    Inventors: Olivier De Vriendt, Nicolas Raimarckers
  • Blade with Protuberance for Turbomachine Compressor
    Publication number: 20200080423
    Abstract: A turbine engine compressor blade includes a leading edge, a trailing edge, a suction surface, and a pressure surface. In addition, the blade includes at least one irregularity in the form of a projecting protuberance of the suction surface or the pressure surface or in the form of a recess nested in the suction surface or the pressure surface. The irregularity may have a direction of longest dimension substantially parallel to the leading edge or substantially axial.
    Type: Application
    Filed: August 30, 2019
    Publication date: March 12, 2020
    Applicant: SAFRAN AERO BOOSTERS SA
    Inventor: Stéphane Hiernaux
  • System and method for contactless measurement of circular geometrical parameters of turbine engine components
    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
  • Cooling of turbine engine by evaporation
    Patent number: 10526963
    Abstract: An axial turbine engine for an aircraft, in particular a ducted fan turbine engine. The engine comprises an oil circuit with a cooler fitted with a first heat exchange surface in contact with oil of the oil circuit, and a second heat exchange surface in contact with a secondary air flow entering the turbine engine. The cooler is of the air/oil type (ACOC) and comprises fins. To increase the capacity of the cooler, the cooler is fitted with a device for injecting a cooling liquid, e.g., water with additives. The thermal capacity of the water amplifies the cooling. Evacuation of the water increases the thrust of the turbine engine. A method is also provided for cooling the turbine engine of an aircraft by injection of a cooling liquid at the time of take-off.
    Type: Grant
    Filed: March 7, 2016
    Date of Patent: January 7, 2020
    Assignee: Safran Aero Boosters SA
    Inventor: Vincent Duprez
  • Electrical connector for turbine engine casing
    Patent number: 10526920
    Abstract: A turbine engine casing, and in particular an axial turbine engine compressor casing, includes an annular wall and a fastening flange associated with the wall. The fastening flange includes a fastening surface applied against a corresponding mounting surface of the turbine engine, for example, a surface on an intermediate fan casing or a mounting surface of a flow separator. The fastening flange includes at least one electrical connector with one end lying flush with the fastening surface of said fastening flange.
    Type: Grant
    Filed: April 5, 2018
    Date of Patent: January 7, 2020
    Assignee: SAFRAN AERO BOOSTERS SA
    Inventor: Frédéric Vallino
  • Brush seal for a turbine engine rotor
    Patent number: 10519793
    Abstract: An aircraft turbojet low-pressure compressor includes a sealing device for a turbine engine. The device includes an internal stator shroud connected to an external casing via an annular row of stator vanes and a rotor with two brush seals arranged inside the shroud and respectively upstream and downstream. The internal shroud includes a frustoconial internal surface, which is associated with each brush seal. Each frustoconical surface lies flush with and is inclined with respect to the bristles of the brush seal, so as to seal with the said brush. A method for assembling a sealing device is also proposed.
    Type: Grant
    Filed: March 29, 2018
    Date of Patent: December 31, 2019
    Assignee: SAFRAN AERO BOOSTERS SA
    Inventors: Stéphane Hiernaux, Nicolas Habotte
  • Compressor of axial turbine engine with contra-rotating rotor
    Patent number: 10502143
    Abstract: The present application relates to an axial turbine engine with a turbine, a low-pressure compressor, and a fan. The turbine drives the compressor and the fan via a plurality of epicyclic reducing gears. The rotor of the compressor includes upstream a disc with a row of vanes and downstream a drum with a plurality of rows of vanes. The disc and the drum are connected to different parts of the epicyclic reducing gears, so as to be counter-rotating. The turbine engine includes a row of stator vanes arranged between two rows of rotor blades of the drum of the compressor, so as to straighten the flow and improve the efficiency. The turbine engine includes at least two epicyclic reducing gears, so that the vane rows of the drum turn faster than that downstream, which itself turns faster than the fan.
    Type: Grant
    Filed: September 25, 2015
    Date of Patent: December 10, 2019
    Assignee: SAFRAN AERO BOOSTERS SA
    Inventor: Stéphane Hiernaux
  • 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
  • Insulating test engine hood for a turbine engine on a test bench
    Patent number: 10458272
    Abstract: The present application concerns a test engine hood for a turbine engine, such as a double flow turbine. The test hood allows replacement of a flight engine hood during tests on a test bench on the ground where the temperature conditions could damage the flight hood. The test hood includes a tubular wall of carbon-fiber epoxy composite, and metal flanges upstream and downstream. To provide thermal protection, the test hood includes a layer of silicone with a majority of polysiloxane. The layer covers the entire inner surface of the wall to create a barrier. The present application also concerns a method for testing a turbine engine on a test bench, where the turbine engine is fitted with a test casing. The present application also concerns a use of silicone for thermal insulation of the inside of the test hood of the turbine engine on a test bench on the ground.
    Type: Grant
    Filed: September 28, 2015
    Date of Patent: October 29, 2019
    Assignee: SAFRAN AERO BOOSTERS SA
    Inventors: Quac Hung Tran, Pierre Croes, Aurore Noelmans
  • De-Icing Shroud for a Compressor of Turbomachine
    Publication number: 20190309653
    Abstract: Shroud assembly of an axial turbomachine (2) having a rotor (12), such as a turbomachine compressor air-intake shroud (28). The assembly comprises an annular layer (32) of abradable material that is able to cooperate by abrasion with lips (44) of the turbomachine in order to ensure tightness, and a heating module (38) for the abradable layer (32). The module (38) comprises electrical heating resistors (42) within the abradable material in order to prevent the presence of ice on the shroud (28). The abradable material is thus used as a heating body which receives, transports and distributes the heat used for de-icing.
    Type: Application
    Filed: November 3, 2017
    Publication date: October 10, 2019
    Applicant: SAFRAN AERO BOOSTERS SA
    Inventor: Rafael Perez
  • Assembly for Turbine Engine
    Publication number: 20190309650
    Abstract: An assembly for a turbine engine includes an upstream section and a downstream section, each having an annular row of semi-cylindrical radial recesses and a plurality of flanges positioned between two circumferentially adjacent recesses for holding the two sections together. The recesses form a cylindrical opening when the two sections are assembled. The openings receive pivot sections of variable stator vanes.
    Type: Application
    Filed: April 9, 2019
    Publication date: October 10, 2019
    Applicant: SAFRAN AERO BOOSTERS SA
    Inventor: Morgan Vyvey
  • Method for producing a compressor stator of an axial turbomachine
    Patent number: 10436220
    Abstract: The invention relates to a method of producing a low-pressure compressor stator for an axial turbine engine. The stator comprises an external shroud with stubs and an annular row of stator blades extending radially towards the inside from the stubs. The method comprises the following stages: supply or production of a starting bar; bending of the bar so that it makes a circle, in order to form an unwrought external shroud; turning to form an axial annular wall delimited by annular fixing flanges; orbital friction-welding of a row of blades onto the stubs of the external shroud. The stubs are realized during a milling stage of the bar or of the external shroud, the milling being carried out before or after the bending stage. The shroud and the blades can be produced in titanium or in a thermoplastic polymer.
    Type: Grant
    Filed: July 13, 2015
    Date of Patent: October 8, 2019
    Assignee: Safran Aero Boosters SA
    Inventor: Francois Hindryckx
  • Axial turbomachine compressor casing
    Patent number: 10428833
    Abstract: The present application relates to an axial turbomachine low-pressure compressor stator. The stator includes an outer annular casing made of organic matrix composite materials. The stator also has groups of vanes having an outer shroud, several rows of stator vanes spaced axially from one another, and segments of inner shrouds at the inner ends of the vanes. The rows of stator vanes are aligned along the circumference of the casing. Each outer shroud is pressed against the inside of the casing so it can be fastened by means of attachment pins. The outer shroud, and the rows of vanes of said group forming a one-piece assembly. The device of the present application reduces the number of vane attachment elements to a few attachment portions distributed on the shroud.
    Type: Grant
    Filed: June 23, 2016
    Date of Patent: October 1, 2019
    Assignee: SAFRAN AERO BOOSTERS SA
    Inventor: Jean-François Cortequisse
  • Fuelling connection module for space launch vehicle
    Patent number: 10414522
    Abstract: Connection module for fuelling a space launch vehicle with cryogenic propellant. The module has a ground part placed on the launch pad mast side of the launch vehicle; a flight part fixed to the launch vehicle; a link fixed to the parts to unite them. The module exhibits a passage crossing the ground part, the flight part and the link. The passage allows communication between a line of the launch pad, such as an umbilical structure of the launch vehicle, and a line supplying a tank or a pneumatic circuit of the launch vehicle. Twisting means, such as a lever or an arm, are linked to a disconnection cable. During lift-off, the twisting means apply a torque to the link which causes the breakage of a link groove, allowing the link to split into two axial portions.
    Type: Grant
    Filed: May 10, 2016
    Date of Patent: September 17, 2019
    Assignee: SAFRAN AERO BOOSTERS SA
    Inventor: Julien Delcommune
  • Stator with adjustable vanes for the compressor of an axial turbine engine
    Patent number: 10408059
    Abstract: The invention concerns an assembly for the stator of a compressor of an axial-flow turbine engine, such as a low-pressure compressor of the turbojet engine also known as a booster. The assembly comprises: a first annular array of first vanes of the stator extending radially in the axial flow; and a second annular row of second vanes of the stator, with controlled orientation, also known as variable-pitch vanes or VSV. In addition, the assembly comprises an external monobloc shroud on which the first vanes and the second vanes are mounted in a pivoting manner.
    Type: Grant
    Filed: August 21, 2017
    Date of Patent: September 10, 2019
    Assignee: Safran Aero Boosters SA
    Inventor: Morgan Vyvey
  • Lattice type blade of an axial turbine engine compressor
    Patent number: 10400625
    Abstract: The invention relates to a blade of a low-pressure compressor of an axial turbine engine. The blade comprises a vane in which a cavity is formed. The vane has a leading edge and a trailing edge, an intrados surface and an extrados surface which extend from the leading edge to the trailing edge, an outer casing which forms the intrados surface and the extrados surface and which delimits the cavity. The blade further comprises closed foam, such as a polymethacrylic foam, which blocks the cavity in order to isolate it from the environment of the blade. The blade further has a three-dimensional lattice which is formed in the cavity and which is integral with the vane of the blade. This barrier protects from chemical attacks and the introduction of impurities. The invention also relates to a production method for a hollow turbine engine blade which is filled with foam.
    Type: Grant
    Filed: October 21, 2015
    Date of Patent: September 3, 2019
    Assignee: Safran Aero Boosters SA
    Inventor: Jean-Francois Cortequisse
  • Oil tank for a turbomachine with level measurement
    Patent number: 10393314
    Abstract: An oil tank fitted to a turbomachine, for example an aeroplane turbo-jet engine. The tank includes an inner chamber containing the oil of the turbomachine, a wall with an inner surface surrounding the inner chamber, and a capacitive device for measuring the oil level. The device includes at least one electrode and potentially two parallel electrodes forming the inner surface. These electrodes are immersed in the oil to measure the oil level by measuring capacitance. A method for manufacturing a tank in which the electrodes are printed on the wall.
    Type: Grant
    Filed: July 7, 2017
    Date of Patent: August 27, 2019
    Assignee: Safran Aero Boosters SA
    Inventors: Nicolas Raimarckers, Frederic Vallino, Giuseppe Giordano
  • Splitter nose of a low-pressure compressor of an axial turbomachine with annular deicing conduit
    Patent number: 10392965
    Abstract: The invention comprises a splitter nose of an axial turbomachine, in particular a compressor, the splitter nose comprising: an annular casing an annular conduit for de-icing a separation edge of the splitter nose; the conduit is connected to the casing only in a first zone in the region of a hot air inlet and in a second zone located in a position diametrically opposite the inlet, or forming relative to the axis of the turbomachine an angle ? less than 30° with respect to the position so as to allow expansion deformations of the conduit. The invention also comprises a compressor and a turbomachine comprising such a splitter nose.
    Type: Grant
    Filed: July 5, 2016
    Date of Patent: August 27, 2019
    Assignee: Safran Aero Boosters SA
    Inventor: Jean-Francois Cortequisse
  • Structural Casing for an Axial Turbine Engine
    Publication number: 20190242271
    Abstract: A structural casing for an axial turbine engine includes an outer ring, an inner hub, and a plurality of struts extending radially from the hub to the ring, wherein the ring is made of a plurality of angular segments welded together. The segments extend circumferentially of different angles, some segments being larger angularly than others. The structural casing is adapted to be an intermediate casing between two compressors of a turbine engine.
    Type: Application
    Filed: January 31, 2019
    Publication date: August 8, 2019
    Applicant: SAFRAN AERO BOOSTERS SA
    Inventors: Ludovic Bovyn, Eric Englebert, Maxime Peeters