Patents by Inventor Maeva Daphné GROS-BOROT

Maeva Daphné GROS-BOROT 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: 20230399960
    Abstract: A device for pressurizing a turbomachine downstream enclosure, the device being fed by means of a pressurizing air flow and including: a first shaft portion, a second shaft portion coupled to the first shaft portion via internal splines and external splines and extending, at a distance, inside the first shaft portion. The device includes at least a first passage made through the splines, and at least one orifice passing right through the second shaft portion, the orifice being arranged upstream of the first passage, in fluidic communication with the first passage, and opening out inside the second shaft portion so as to allow the pressurizing air flow to circulate from the first passage, between the first and second shaft portions, towards the downstream enclosure.
    Type: Application
    Filed: October 22, 2021
    Publication date: December 14, 2023
    Inventors: Maeva Daphne GROS-BOROT, Clementine Charlotte Marie MOUTON
  • 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: 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: 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
  • 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