Patents by Inventor Matthieu Bruno Francois FOGLIA

Matthieu Bruno Francois FOGLIA 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: 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
  • 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: 20230313739
    Abstract: The invention relates to a turbine engine module, comprising: - a fan shaft (6), - a power shaft (15) rotating the fan shaft via a speed reducer (21) arranged in a lubrication chamber (22), - a lubrication system (50) for the speed reducer (21) having a main circuit (51), which is closed, for supplying the lubrication chamber, and an auxiliary circuit (60), which is closed, for supplying the lubrication chamber when the main circuit is inactive, the auxiliary circuit comprising an auxiliary pump (61) driven by an electric motor (63), and - an electric machine (65) configured to power the electric motor (63), the electric machine having a rotor connected to the fan shaft in order to be rotated and a stator mounted on a stationary member at least partially supporting the electric machine.
    Type: Application
    Filed: March 26, 2021
    Publication date: October 5, 2023
    Inventors: Julien Fabien Patrick BECOULET, Didier Gabriel Bertrand DESOMBRE, Matthieu Bruno Francois FOGLIA
  • 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
  • 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
  • Publication number: 20230019277
    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: Application
    Filed: December 11, 2020
    Publication date: January 19, 2023
    Applicants: 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: 20230013650
    Abstract: An aero-propulsion system includes a drive shaft, a low-pressure compressor, a fan shaft driving a fan, a reduction device that couples the drive shaft and the fan shaft, and an inlet channel which extends between the fan and the low-pressure compressor, the inlet having a predetermined mean radius, a ratio between a mean radius of the inlet channel and the mean radius of the low-pressure compressor, on the one hand, and the reduction ratio of the reduction mechanism, on the other hand, being less than 0.35.
    Type: Application
    Filed: December 11, 2020
    Publication date: January 19, 2023
    Inventors: Maeva Daphné GROS-BOROT, Gilles Alain Marie CHARIER, Matthieu Bruno François FOGLIA, Caroline Marie FRANTZ, Adrien Louis SIMON
  • Patent number: 11396846
    Abstract: A turbine engine mechanical reduction gear, for example, of an aircraft, the reduction gear comprising: a sun gear having an axis of rotation; a ring gear which extends around the sun gear and which is configured to be immobile in rotation about the axis; planetary gears which are meshed with the sun gear and the ring gear and which are supported by a planetary carrier which is configured to be mobile in rotation about the axis; at least one lubrication oil distributor which comprises a stator portion immobile in rotation and a rotating integral rotor portion of the planetary carrier; and an annular oil deflector which is integral with the ring gear, wherein the stator portion of the distributor is integral with the deflector.
    Type: Grant
    Filed: March 5, 2020
    Date of Patent: July 26, 2022
    Assignees: SAFRAN AIRCRAFT ENGINES, SAFRAN TRANSMISSION SYSTEMS
    Inventors: Adrien Louis Simon, Matthieu Bruno François Foglia
  • Publication number: 20200284203
    Abstract: A turbine engine mechanical reduction gear, for example, of an aircraft, the reduction gear comprising: a sun gear having an axis of rotation; a ring gear which extends around the sun gear and which is configured to be immobile in rotation about the axis; planetary gears which are meshed with the sun gear and the ring gear and which are supported by a planetary carrier which is configured to be mobile in rotation about the axis; at least one lubrication oil distributor which comprises a stator portion immobile in rotation and a rotating integral rotor portion of the planetary carrier; and an annular oil deflector which is integral with the ring gear, wherein the stator portion of the distributor is integral with the deflector.
    Type: Application
    Filed: March 5, 2020
    Publication date: September 10, 2020
    Applicants: SAFRAN AIRCRAFT ENGINES, SAFRAN TRANSMISSION SYSTEMS
    Inventors: Adrien Louis Simon, Matthieu Bruno François Foglia