Patents by Inventor Olivier Belmonte

Olivier Belmonte has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).

  • Publication number: 20200116081
    Abstract: Aircraft turbomachine with mechanical reducer and counter-rotating turbine are described. The turbomachine includes a fan driven in rotation by a fan shaft, a mechanical reducer with epicyclic gear train, a gas generator comprising a counter-rotating turbine, a first turbine shaft of which is coupled to an input shaft of the reducer and to a pin, and a second turbine shaft of which is coupled to the fan shaft. The guidance of the reducer input shaft is provided by a first ball bearing, the guidance of the pin is provided by a second roller bearing, and the guidance of the first shaft is provided by a third roller bearing axially interposed between the first and second bearings.
    Type: Application
    Filed: October 9, 2019
    Publication date: April 16, 2020
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Paul Ghislain Albert Levisse, Olivier Belmonte, Olivier Formica
  • Publication number: 20200116104
    Abstract: Turbine engine (10) with a contra-rotating turbine for an aircraft, the turbine engine comprising a contra-rotating turbine (22) whose first rotor (22a) is configured to rotate in a first direction of rotation and is connected to a first turbine shaft (36), and a second rotor (22b) is configured to rotate in an opposite direction of rotation and is connected to a second turbine shaft (38), the first rotor comprising turbine wheels (36a) inserted between turbine wheels (38a) of the second rotor, the turbine engine further comprising a mechanical reduction gear (42) with an epicyclic gear train which comprises a sun gear (44) driven in rotation by said second shaft, a ring gear (40) driven in rotation by said first shaft, and a planet carrier (46) fixed to a stator casing (28) of the turbine engine situated downstream from the contra-rotating turbine with respect to direction of flow of the gases in the turbine engine, the turbine engine further comprising a bearing (56) for guiding the second shaft with respec
    Type: Application
    Filed: October 8, 2019
    Publication date: April 16, 2020
    Inventors: Paul Ghislain Albert LEVISSE, Olivier BELMONTE, Yanis BENSLAMA
  • Patent number: 10479514
    Abstract: An assembly for an aircraft turbine machine including a receiver for a pair of open rotor contra-rotating propellers, the assembly including a duct, ancillaries routed inside the duct, an attachment case, attachment device of the duct on an annular installation portion of the case. The attachment device in an assembled configuration include a split ring fitted with internal projections housed inside orifices in the duct; a radial loading surface of the ring made on the portion the surface being tapered and narrowing along a first axial direction, and being in contact with a peripheral surface of the complementary shaped tapered split ring; device of axially loading the ring along the first direction, the device being blocked in the axial direction on the portion.
    Type: Grant
    Filed: January 4, 2017
    Date of Patent: November 19, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Clementine Charlotte Marie Mouton, Olivier Belmonte, Jeremy Phorla Lao, Didier Jean-Louis Yvon
  • Patent number: 10443609
    Abstract: A device for controlling the pitch of fan blades in a turbine engine having an unducted fan including at least one set of adjustable pitch fan blades, each fan blade being coupled, for pitch adjustment purposes, to a radial control shaft constrained to rotate with the set of fan blades and suitable for pivoting about a radial pitch axis of the fan blade, the device including a stationary actuator centered on a longitudinal axis of the turbine engine and driving an outer ring of a load transfer bearing in translation, the outer ring of the load transfer bearing being coupled directly to a lever arm of each control shaft via a respective ball joint connection in order to adjust its pivoting.
    Type: Grant
    Filed: April 25, 2016
    Date of Patent: October 15, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Emmanuel Pierre Dimitri Patsouris, Olivier Belmonte, Clementine Charlotte Marie Mouton, Thomas Julien Nguyen Van
  • Patent number: 10408069
    Abstract: A radial control shaft for a device for controlling the pitch of fan blades of a turbine engine having an unducted fan, is disclosed. The shaft includes an external portion that is designed to be mounted in the control device from its outside and to be coupled to at least one fan blade in order to adjust its pitch, and an internal portion, independent of the external portion, that is designed to be mounted from the inside of the control device, to be connected to a load transfer bearing in order to pivot the shaft about a radial axis, and to close an oil enclosure in which the bearing is housed, the external and internal portions of the shaft being coupled to each other. A method of mounting such a shaft and a control device including such a shaft are also disclosed.
    Type: Grant
    Filed: May 10, 2016
    Date of Patent: September 10, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Olivier Belmonte, Emmanuel Pierre Dimitri Patsouris, Thomas Julien Nguyen Van
  • Patent number: 10302187
    Abstract: A reduction gear having an epicyclic gear train for a turbine engine, in particular of an aircraft, comprising: a planetary shaft having an axis of rotation A; a ring gear having an axis A extending around said planetary shaft; planet gears distributed around said axis A, which mesh with said ring gear and the planetary shaft; and a planet carrier including members for supporting bearings of the planet gears, having axes of rotation B, which are evenly distributed around the axis A, as well as a part holding each supporting member substantially by the middle thereof along the axis B thereof, wherein said supporting members are made as a single part having means for supplying lubricating oil to said bearings. A method for assembling said reduction gear is also provided.
    Type: Grant
    Filed: April 21, 2016
    Date of Patent: May 28, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Jérémy Phorla Lao, Olivier Belmonte, Clémentine Charlotte Marie Mouton, Thomas Julien Nguyen Van, Emmanuel Pierre Dimitri Patsouris
  • Patent number: 10279889
    Abstract: A hydraulic ram comprising a fixed support, a cylinder that is movable in translation relative to the support, a piston secured inside the cylinder delimiting two chambers with the cylinder and a device for supplying the chambers with hydraulic fluid upstream from the fixed support. The ram is characterized by the fact that the supply device comprises telescopic channels, each telescopic channel comprising two tubular elements sliding one into the other, a first tubular element being rigidly connected to the fixed support at one end and the second tubular element being rigidly connected to the cylinder at at least two points separated from each other along a generatrix of the cylinder. The invention is applicable to controlling the pitch of the blades of a turbine engine propeller.
    Type: Grant
    Filed: September 22, 2014
    Date of Patent: May 7, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Olivier Belmonte, Augustin Curlier
  • Patent number: 10280795
    Abstract: A device for recovering oil injected by centrifugal effect in a turbine engine, comprising a substantially circular ring around an axis, the ring comprising a first part forming a basin surrounding the axis and having an opening turned radially inward, so as to recover the oil injected radially across from the opening, and a second part forming a substantially toroidal chamber, radially open outward at a low point, so as to allow oil to escape, a passage being arranged between the basin and the chamber substantially over the entire circumference around the axis so as to cause the oil recovered by the basin to enter the chamber, wherein a rim is arranged between a radially inner bottom of the chamber and the passage, so as to contain the oil accumulating in this radially inner bottom of the chamber, and in some embodiments, at a high point.
    Type: Grant
    Filed: June 9, 2017
    Date of Patent: May 7, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Jérémy Phorla Lao, Olivier Belmonte, Clémentine Charlotte Marie Mouton
  • Patent number: 10280941
    Abstract: A device for guiding variable pitch stator vanes of a turbine engine is provided. The device includes a plurality of inner ring angular sectors arranged end-to-end in order to form an inner ring, each inner ring sector having chimneys passing radially through the inner ring sector, a plurality of cylindrical bushings, each being put into place in a chimney of the inner ring from the inside and each serving to receive a guide pivot of a stator vane, a plurality of reconstitution ring angular sectors arranged end-to-end in order to form a reconstitution ring and put into place radially from the inside against the inner ring, and a plurality of blocking elements passing axially through the inner and reconstitution rings in order to assemble the rings together.
    Type: Grant
    Filed: November 19, 2014
    Date of Patent: May 7, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Clementine Charlotte Marie Mouton, Olivier Belmonte
  • Publication number: 20190010957
    Abstract: A pivot for an adjustable-pitch blade for a turbine engine fan hub, the pivot including a stud having coupling device for transmitting a twisting torque and an outside thread, a force-decoupling part positioned around the stud, provided with an outside thread, pressing transversely against the stud at its radially outer end, an outer rolling bearing having an inside ring mounted to press transversely against the force-decoupling part, an inner rolling bearing assembled around the force-decoupling part and held thereby, a pitch transmission ring provided with a coupling device co-operating, with the coupling device of the stud, a first clamping nut screwed onto the outside thread of the force-decoupling part in order to clamp the outer and inner rolling bearings around the fan hub, and a second clamping nut screwed onto the outside thread of the stud in order to provide clamping between the stud, the force-decoupling part, and the pitch transmission ring.
    Type: Application
    Filed: January 4, 2017
    Publication date: January 10, 2019
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Olivier BELMONTE, Christophe Paul JACQUEMARD, Clementine Charlotte Marie MOUTON, Emmanuel Pierre Dimitri PATSOURIS
  • Publication number: 20180347460
    Abstract: A turbojet of the unducted rotor type and an aircraft including such a turbojet, the turbojet comprising a gas generator (3-8), a first unducted propeller (21) connected to a shaft (81) of the gas generator (3-8) via first reduction gearing (23), and a second unducted propeller (91) connected to a shaft (81) of the gas generator (3-8) via second reduction gearing (93), wherein the first propeller (21) and the first reduction gearing (23) are mounted at the front of the gas generator (3-8), and wherein the second propeller (91) and the second reduction gearing (93) are mounted at the rear of the gas generator (3-8).
    Type: Application
    Filed: May 31, 2018
    Publication date: December 6, 2018
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Thomas Julien NGUYEN VAN, Olivier BELMONTE, Jeremy Phorla LAO, Clementine Charlotte Marie MOUTON, Emmanuel Pierre Dimitri PATSOURIS, Didier Jean-Louis YVON
  • Patent number: 10072729
    Abstract: A balancing method for a rotating part device including a nut having an internal thread, and a countersunk collar is disclosed. The countersunk collar has a through-hole with a diameter greater than the diameter of the internal thread of the nut. The countersunk collar includes a balancing weight.
    Type: Grant
    Filed: March 26, 2015
    Date of Patent: September 11, 2018
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Olivier Belmonte, Lucie Galons
  • Publication number: 20180163850
    Abstract: A reduction gear having an epicyclic gear train for a turbine engine, in particular of an aircraft, comprising: a planetary shaft having an axis of rotation A; a ring gear having an axis A extending around said planetary shaft; planet gears distributed around said axis A, which mesh with said ring gear and the planetary shaft; and a planet carrier including members for supporting bearings of the planet gears, having axes of rotation B, which are evenly distributed around the axis A, as well as a part holding each supporting member substantially by the middle thereof along the axis B thereof, wherein said supporting members are made as a single part having means for supplying lubricating oil to said bearings. A method for assembling said reduction gear is also provided.
    Type: Application
    Filed: April 21, 2016
    Publication date: June 14, 2018
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Jérémy Phorla Lao, Olivier Belmonte, Clémentine Charlotte Marie Mouton, Thomas Julien Nguyen Van, Emmanuel Pierre Dimitri Patsouris
  • Patent number: 9995176
    Abstract: The device (20) comprises two outer and inner concentric rings (22, 23), one of which is connected to an oil supply from one of the repositories, the other ring being connected to the other repository, the oil flowing between said rings, and bearings between the rings in order to change repositories between the two rings. According to the invention, the device (20) further comprises a flexible means (31) forming a shock absorber, provided between a first of said rings and an intermediate ring (41) that is separated from a second of said rings by said bearings (25), said flexible means (31) defining a deformable sealed chamber (32) in which oil travels between the two repositories.
    Type: Grant
    Filed: October 1, 2014
    Date of Patent: June 12, 2018
    Assignee: SNECMA
    Inventors: Olivier Belmonte, Jérémy Phorla Lao
  • Patent number: 9988937
    Abstract: The disclosed subject matter relates to a hydraulic and electrical interface ring for a turbine engine, characterized in that said ring comprises fluid transfer pipes which axially pass therethrough and having axial ends that form axial interlocking means, the supporting means of at least one electrical device, and at least one electrical linking connector of the device, said connector being configured to engage by axial interlocking with a complementary electrical connector of another part.
    Type: Grant
    Filed: September 24, 2013
    Date of Patent: June 5, 2018
    Assignee: SNECMA
    Inventors: Augustin Curlier, Olivier Belmonte
  • Patent number: 9957896
    Abstract: A device for axially arresting a sealing ring made of an abradable material in contact with a periphery of an aircraft turbomachine module rotor, the device having a first reference central axis, and including: a support including a support opening defining a circular track centered on a second axis at a distance from the axis; and an axial stop part including an extraction passage centered on a third axis at a distance from the axis, and defining a complementary circular track around its periphery, cooperating with the track to allow the part to rotate about the axis, between an axial stop position for the sealing ring, and a position to extract the ring through the extraction passage.
    Type: Grant
    Filed: December 4, 2012
    Date of Patent: May 1, 2018
    Assignee: SNECMA
    Inventors: Olivier Belmonte, Sebastien Jean Laurent Prestel
  • Patent number: 9944382
    Abstract: A device for controlling the pitch of the blades of a rotor is provided. The device includes a radial shaft, the rotation of which controls the pitch of the blades; a guiding bearing for guiding the radial shaft; a nut which tightens the guiding bearing along the radial axis; and a circumferential rib extending as a protrusion towards the outside of the nut, for guiding a lubrication oil towards the outside of the nut.
    Type: Grant
    Filed: September 18, 2014
    Date of Patent: April 17, 2018
    Assignee: SNECMA
    Inventors: Olivier Belmonte, Emmanuel Pierre Dimitri Patsouris
  • Patent number: 9926944
    Abstract: A device for guiding variable pitch diffuser vanes of a turbine engine is provided. The device includes a first ring having an axial portion at its periphery that is extended by a collar extending radially outwards; a second ring mounted around the axial portion of the first ring so as to cooperate therewith to define a plurality of outwardly open sockets; a plurality of cylindrical bushings, each mounted in a respective socket for the purpose of receiving a guide pivot of a diffuser vane; and a resilient clamping ring for cooperating with one of the rings in order to clamp the two rings axially one against the other.
    Type: Grant
    Filed: July 28, 2014
    Date of Patent: March 27, 2018
    Assignee: SNECMA
    Inventors: Clementine Charlotte Marie Mouton, Olivier Belmonte, Alain Marc Lucien Bromann, Jeremy Phorla Lao
  • Publication number: 20180065730
    Abstract: A device for controlling pitch of fan blades of a turbine engine including an un-ducted fan, the device including: at least one set of fan blades of adjustable pitch, the set being constrained to rotate with a rotary ring centered on a longitudinal axis and mechanically connected to a turbine rotor, each blade of the set being mounted on a blade root support that is pivotally mounted on the rotary ring; and at least one radial control shaft adjusting pitch of at least two adjacent blades of the set, the control shaft being constrained to rotate with the rotary ring and being configured to pivot about an axis of the shaft, being coupled to the blade root supports of the at least two blades of the set to adjust their pitch via a transmission system including eccentrics connected together by at least one connecting rod.
    Type: Application
    Filed: April 29, 2016
    Publication date: March 8, 2018
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Tewfik BOUDEBIZA, Olivier BELMONTE, Gilles CHARIER, Emmanuel Pierre Dimitri PATSOURIS, Pierre-Alain REIGNER
  • Patent number: 9903375
    Abstract: A fan including a system for holding blades having variable pitch, in which the bases of the blades are mounted onto radial shafts of a rotor of the fan by pivots, is provided. The system includes a main body capable of being attached onto the rotor; and at least one holding arm mounted onto the main body and capable of extending inside a pivot so as to engage with the pivot in order to lock the movement of the pivot along the axis of the shaft on which the holding arm is mounted.
    Type: Grant
    Filed: September 18, 2013
    Date of Patent: February 27, 2018
    Assignee: SNECMA
    Inventors: Olivier Belmonte, Augustin Curlier