Patents by Inventor Adrien Louis SIMON

Adrien Louis SIMON 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).

  • Patent number: 11913385
    Abstract: A propulsion system includes a drive shaft that rotates about an axis, a fan, a fan shaft that drives the fan about the axis, a reduction mechanism coupling the drive and fan shafts, a compression section driven by the drive shaft, and an inlet channel that extends between the fan and the compression section. The inlet channel includes inner and outer ferrules delimiting an air inlet flow path, the inner ferrule having a minimum radius. The reduction mechanism includes two reduction stages including two or more planet gears circumferentially distributed around the axis, each planet gear including a first portion meshed with the drive shaft and a second portion meshed with the fan shaft and being mounted fixed with respect to the inner ferrule and having a maximum radius greater than the minimum radius such that the air inlet flow path extends partly between the two or more planet gears.
    Type: Grant
    Filed: October 8, 2021
    Date of Patent: February 27, 2024
    Assignees: SAFRAN AIRCRAFT ENGINES, SAFRAN TRANSMISSION SYSTEMS
    Inventors: Caroline Marie Frantz, Gilles Alain Marie Charier, Matthieu Bruno François Foglia, Adrien Louis Simon
  • Patent number: 11867259
    Abstract: A mechanical gearbox for turbomachine, in particular for aircraft. The gearbox includes a sun gear including an external toothing, a ring gear including an internal toothing, and planet gears which are meshed with the sun gear and the stationary ring gear. The planet gears are carried by a movable planet carrier and each having external toothings of different diameters. The movable planet carrier includes a movable ring gear which carries an internal toothing and which is independent of the stationary ring gear, each of the planet gears being meshed with the sun gear and the stationary and movable ring gears.
    Type: Grant
    Filed: November 4, 2021
    Date of Patent: January 9, 2024
    Assignee: SAFRAN TRANSMISSION SYSTEMS
    Inventors: Guillaume Pierre Mouly, Adrien Louis Simon, Dhafer Ghribi
  • Patent number: 11859560
    Abstract: A power transmission module for an aircraft, the module including a torque input connected to a turbine shaft, a first torque output and a second torque output, the power transmission module including a mechanical reducer including a sun gear forming the torque input, and planet gears carried by a planet carrier, wherein each of the planet gears includes at least three independent toothings and further includes a first toothing meshed with the sun gear, a second toothing meshed with an element forming one of the torque outputs, and a third toothing meshed with another element.
    Type: Grant
    Filed: September 20, 2022
    Date of Patent: January 2, 2024
    Assignee: SAFRAN TRANSMISSION SYSTEMS
    Inventors: Guillaume Pierre Mouly, Adrien Louis Simon, Guillaume Julien Beck, Simon Loic Clement Lefebvre
  • Publication number: 20230383698
    Abstract: A propulsion system includes a drive shaft that rotates about an axis, a fan, a fan shaft that drives the fan about the axis, a reduction mechanism coupling the drive and fan shafts, a compression section driven by the drive shaft, and an inlet channel that extends between the fan and the compression section. The inlet channel includes inner and outer ferrules delimiting an air inlet flow path, the inner ferrule having a minimum radius. The reduction mechanism includes two reduction stages including two or more planet gears circumferentially distributed around the axis, each planet gear including a first portion meshed with the drive shaft and a second portion meshed with the fan shaft and being mounted fixed with respect to the inner ferrule and having a maximum radius greater than the minimum radius such that the air inlet flow path extends partly between the two or more planet gears.
    Type: Application
    Filed: October 8, 2021
    Publication date: November 30, 2023
    Applicants: SAFRAN AIRCRAFT ENGINES, SAFRAN TRANSMISSION SYSTEMS
    Inventors: Caroline Marie FRANTZ, Gilles Alain Marie CHARIER, Matthieu Bruno Francois FOGLIA, Adrien Louis SIMON
  • Publication number: 20230356858
    Abstract: A pre-assembly method for an aircraft turbomachine, having preliminary assembling, outside the turbomachine, the following components with each other a reduction gear configured to transmit a rotation between at least two rotors of the turbomachine while modifying the speed and torque ratio from one to the other of said at least two rotors, a shaft kinematically coupled to the reduction gear and configured to be kinematically coupled to one of said at least two rotors, a bearing support, and at least one bearing mounted on the bearing support and configured to rotatably support the shaft.
    Type: Application
    Filed: May 3, 2023
    Publication date: November 9, 2023
    Applicant: SAFRAN TRANSMISSION SYSTEMS
    Inventors: Adrien Louis SIMON, Guillaume Julien BECK, Yohan DOUY, Jordane Emile André PELTIER, Jérémy David SEBAN
  • Patent number: 11808344
    Abstract: A planet carrier for a mechanical gearbox for a turbomachine includes a one-piece cage that extends about an axis of rotation defining an internal housing configured to receive a sun gear and planet gears of the gearbox. The planet carrier further includes a lubrication system with at least one bore formed in the cage and extending parallel to the axis over more than 30% of a maximum axial dimension (Lmax) of the cage. The lubrication system also includes for the at least one bore, at least two sprinklers which are fitted to the cage and which are each mounted in a recess of the cage.
    Type: Grant
    Filed: January 4, 2022
    Date of Patent: November 7, 2023
    Assignee: SAFRAN TRANSMISSION SYSTEMS
    Inventors: Guillaume Pierre Mouly, Frederic Nicolas François Laisnez, Adrien Louis Simon
  • Patent number: 11808213
    Abstract: The present invention relates to a mechanical reducer (6) for a turbomachine, in particular an aircraft, this reducer (6) including: a sun gear extending around an axis (61) of rotation, a crown which extends around the sun gear and which is configured to be fixed in rotation around said axis (61), planet gears which are meshed with the sun gear and the crown and which are held by a planet carrier (62) which is configured to be movable in rotation about said axis (61), In addition, the oil distributor (65) comprises a plurality of oil distribution modules (67) assembled together, each module (67) comprising at least one lubrication pipe (68) having an inlet intended to receive oil and an outlet (69) adapted to lead the oil into an opening (63) of the planet carrier (62), the opening (63) being intended for lubricating the reducer.
    Type: Grant
    Filed: January 24, 2022
    Date of Patent: November 7, 2023
    Assignee: SAFRAN TRANSMISSION SYSTEMS
    Inventors: Guillaume Pierre Mouly, Frédéric Nicolas François Laisnez, Adrien Louis Simon
  • Patent number: 11802515
    Abstract: A propulsion system includes a drive shaft, a fan, a fan shaft, and a reduction device coupling the drive and fan shafts. The reduction device includes a first reduction stage and a second reduction state, and include a sun gear, centered on an axis of rotation of the drive and fan shafts and driven in rotation by the drive shaft, a ring gear, coaxial with the sun gear and that drives the fan shaft in rotation about the axis, and planet gears distributed circumferentially about the axis between the sun and ring gears, each planet gear including a first portion which is meshed with the sun gear and a second portion which is meshed with the ring gear, a diameter of the first portion being different from a diameter of the second portion, and an oil transfer bearing positioned between the fan and the reduction device.
    Type: Grant
    Filed: December 11, 2020
    Date of Patent: October 31, 2023
    Assignees: SAFRAN AIRCRAFT ENGINES, SAFRAN TRANSMISSION SYSTEMS
    Inventors: Caroline Marie Frantz, Gilles Alain Marie Charier, Maeva Daphné Gros-Borot, Matthieu Bruno François Foglia, Adrien Louis Simon
  • Publication number: 20230340912
    Abstract: A mechanical reducer for a turbomachine for an aircraft, this reducer having a sun gear with internal splines and an external toothing, a ring gear which extends around the sun gear and which has an internal toothing, planet gears which are arranged between the sun gear and the ring gear and which each have at least one external toothing meshing with the external toothing of the sun gear and the internal toothing of the ring gear, and a planet carrier which carries first bearings for guiding the planet gears in rotation. The reducer can further include at least one second bearing for guiding the sun gear in rotation. The at least one second bearing can be mounted between the sun gear and the planet carrier.
    Type: Application
    Filed: April 21, 2023
    Publication date: October 26, 2023
    Inventors: Adrien Louis SIMON, Luc Henri CHATENET, Boris Pierre Marcel MORELLI, Jonathan Jean-Pierre ROUFFET
  • Patent number: 11795875
    Abstract: The present invention relates to an oil transfer device (1) for lubricating a planet carrier, movable in rotation, of an epicyclic gear train for a turbomachine, the device (1) extending around an axis (A) and having: an annular casing (11) which extends around the axis (A), the casing (11) comprising a plurality of oil feed grooves (14), axially juxtaposed, each having an oil ejection opening configured to lead radially to a lubrication circuit of the planet carrier to be lubricated, the device (1) being characterized in that one of the oil feed grooves (14) is a high-pressure oil feed groove (14), called a high-pressure groove (14a), and another of the other oil feed grooves (14) is a low-pressure oil feed groove (14), called a low-pressure groove (14b), axially juxtaposed to the high-pressure groove (14a), the grooves (14) being arranged axially along the axis (X) so that the oil is able to be transferred axially from the high-pressure groove (14a) to the low-pressure groove (14b).
    Type: Grant
    Filed: April 15, 2021
    Date of Patent: October 24, 2023
    Assignee: SAFRAN TRANSMISSION SYSTEMS
    Inventors: Adrien Louis Simon, Patrice Jocelyn Francis Gedin, Bálint Pap
  • Patent number: 11739829
    Abstract: A mechanical reduction gear for a turbomachine, in particular for an aircraft, the reduction gear including a sun gear, a ring gear, planet gears which are meshed with the sun gear and the ring gear, hydrodynamic bearings for guiding the planet gears in rotation, these bearings being carried by a planet carrier and including cylindrical bodies which are engaged in the planet gears and which are configured so as to be supplied with oil and so as to form guiding oil films between the bodies and the planet gears, wherein each of the planet gears is guided by two hydrodynamic bearings independent of each other and disposed on either side of the plane.
    Type: Grant
    Filed: November 9, 2021
    Date of Patent: August 29, 2023
    Assignee: SAFRAN TRANSMISSION SYSTEMS
    Inventors: Guillaume Julien Beck, Patrice Jocelyn Francis Gedin, Simon Loic Clement Lefebvre, Balint Pap, Quentin Pierre Henri Pigott, Adrien Louis Simon
  • Publication number: 20230265813
    Abstract: A propulsion system includes a drive shaft movable in rotation about an axis of rotation, a low-pressure compressor driven in rotation by the drive shaft, the low-pressure compressor having a mean radius, a fan shaft, a fan driven in rotation by the fan shaft, a reduction mechanism coupling the drive shaft and the fan shaft, having a reduction ratio, and an inlet channel which extends between the fan and the low-pressure compressor, the inlet channel having an inlet adjacent to the fan and an outlet opposite the inlet and adjacent to the low-pressure compressor, the inlet having a mean radius. A first ratio between a ratio of a mean radius of the inlet channel and the mean radius of the low-pressure compressor, and the reduction ratio of the reduction mechanism, is strictly less than 0.35.
    Type: Application
    Filed: April 11, 2023
    Publication date: August 24, 2023
    Applicants: SAFRAN AIRCRAFT ENGINES, SAFRAN TRANSMISSION SYSTEMS
    Inventors: Maeva Daphné GROS-BOROT, Gilles Alain Marie CHARIER, Matthieu Bruno Francois FOGLIA, Coroline Marie FRANTZ, Adrien Louis SIMON
  • Patent number: 11725592
    Abstract: A propulsion system includes a drive shaft movable about an axis of rotation, a fan, a fan shaft that drives the fan, and a reduction device coupling the drive shaft and the fan shaft. The reduction device has first and second reduction stages and includes a sun gear, centered on the axis and driven by the drive shaft, a ring gear that is coaxial with the sun gear and that drives the fan shaft about the axis, and planet gears distributed circumferentially about the axis between the sun gear and the ring gear. Each planet gear includes a first portion meshed with the sun gear and a second portion meshed with the ring gear. A diameter of the first portion is different from a diameter of the second portion, and the first portion of the planet gears extend between the second portion of the planet gears and the fan.
    Type: Grant
    Filed: December 11, 2020
    Date of Patent: August 15, 2023
    Assignees: SAFRAN AIRCRAFT ENGINES, SAFRAN TRANSMISSION SYSTEMS
    Inventors: Caroline Marie Frantz, Gilles Alain Marie Charier, Adrien Louis Simon
  • Patent number: 11686255
    Abstract: A method for manufacturing a mechanical reducer for an aircraft turbomachine including a central pinion, an outer crown, N planet pinions, where N?3, each planet pinion including a first stage meshing with the central pinion, and a second stage meshing with the outer crown, the method including the assembly marking, wherein N teeth of the central pinion are marked, and N pairs of teeth of the first stage of each planet pinion are marked, the N planet pinions each being marked identically, and the assembly of the mechanical reducer, so that the teeth of the pairs of marked teeth of the first stage of each planet pinion are disposed on either side of a marked tooth of the central pinion.
    Type: Grant
    Filed: September 21, 2022
    Date of Patent: June 27, 2023
    Assignee: SAFRAN TRANSMISSION SYSTEMS
    Inventors: Adrien Louis Simon, Dhafer Ghribi
  • Publication number: 20230160345
    Abstract: An arrangement for an aircraft turbine engine, including a shaft and a follower element rotatably coupled to the shaft by a spline connection, the arrangement including upstream and downstream connections for radially centring the follower element relative to the shaft; means for spraying a lubricant into a collection cavity; a passage for receiving lubricant, which passage opens into the collection cavity and into a cavity for lubricating the splines which is partially defined by the upstream and downstream radial centring connections; and a passage for discharging lubricant, which passage opens into the cavity for lubricating the splines and outside the arrangement.
    Type: Application
    Filed: April 23, 2021
    Publication date: May 25, 2023
    Applicants: SAFRAN AIRCRAFT ENGINES, SAFRAN TRANSMISSION SYSTEMS
    Inventors: Matthieu Bruno François FOGLIA, Serge René MORREALE, Adrien Louis SIMON
  • Patent number: 11635028
    Abstract: A lubricating oil distributor for a mechanical reduction gear of a turbomachine, in particular of an aircraft, includes a body of generally annular shape around an axis X and includes first and second independent oil circuits. The first oil circuit has a first oil inlet connected by a first chamber to several oil outlets distributed on the body around the axis X. The second oil circuit has a second oil inlet connected by a second chamber to several oil outlets distributed on the body around the axis X. The first and second chambers extend circumferentially around the axis X at different diameters, wherein the first and second oil circuits are formed in the body and are respectively a recovery circuit and an oil supply circuit for toothing of the reduction gear.
    Type: Grant
    Filed: November 20, 2020
    Date of Patent: April 25, 2023
    Assignee: SAFRAN TRANSMISSION SYSTEMS
    Inventor: Adrien Louis Simon
  • Publication number: 20230102913
    Abstract: A method for manufacturing a mechanical reducer for an aircraft turbomachine including a central pinion, an outer crown, N planet pinions, where N?3, each planet pinion including a first stage meshing with the central pinion, and a second stage meshing with the outer crown, the method including the assembly marking, wherein N teeth of the central pinion are marked, and N pairs of teeth of the first stage of each planet pinion are marked, the N planet pinions each being marked identically, and the assembly of the mechanical reducer, so that the teeth of the pairs of marked teeth of the first stage of each planet pinion are disposed on either side of a marked tooth of the central pinion.
    Type: Application
    Filed: September 21, 2022
    Publication date: March 30, 2023
    Applicant: SAFRAN TRANSMISSION SYSTEMS
    Inventors: Adrien Louis SIMON, Dhafer GHRIBI
  • Publication number: 20230091328
    Abstract: A power transmission module for an aircraft, the module including a torque input connected to a turbine shaft, a first torque output and a second torque output, the power transmission module including a mechanical reducer including a sun gear forming the torque input, and planet gears carried by a planet carrier, wherein each of the planet gears includes at least three independent toothings and further includes a first toothing meshed with the sun gear, a second toothing meshed with an element forming one of the torque outputs, and a third toothing meshed with another element
    Type: Application
    Filed: September 20, 2022
    Publication date: March 23, 2023
    Inventors: Guillaume Pierre MOULY, Adrien Louis SIMON, Guillaume Julien BECK, Simon Loic Clement LEFEBVRE
  • Patent number: 11608785
    Abstract: A mechanical reduction gear of a turbomachine, in particular of an aircraft. The reduction gear includes a sun gear, a ring gear surrounded by a ring gear carrier, and planet gears meshed with the sun gear and the ring gear. The ring gear carrier includes an axial abutment on which the ring gear is configured to bear, and helical external splines which are engaged in complementary internal splines of the ring gear carrier and which are configured to cooperate by sliding with the internal splines so as to force the ring gear to be held against the abutment in operation.
    Type: Grant
    Filed: April 8, 2021
    Date of Patent: March 21, 2023
    Assignee: SAFRAN TRANSMISSION SYSTEMS
    Inventors: Adrien Louis Simon, Simon Loic Clement Lefebvre
  • Patent number: 11591972
    Abstract: A mechanical gearbox for an aircraft turbomachine includes a sun gear having an axis (X) of rotation, a ring gear around the sun gear, and planet gears meshed with the sun gear and the ring gear. Each planet gear has a first toothing meshed with the sun gear and a second loathing meshed with the ring gear. The first toothing includes a series of upstream teeth and a series of downstream teeth located on either side of a plane (H) perpendicular to the axis (X) of rotation of the sun gear. The second toothing includes a series of upstream teeth and a series of downstream teeth located on either side of the plane (H) and separated from one another by the first toothing, these teeth being parallel to one another and to the axis (Y) of rotation of the planet gear.
    Type: Grant
    Filed: June 11, 2021
    Date of Patent: February 28, 2023
    Assignee: SAFRAN TRANSMISSION SYSTEMS
    Inventors: Guillaume Julien Beck, Dhafer Ghribi, Simon Loïc Clément Lefebvre, Quentin Pierre Henri Pigott, Adrien Louis Simon