Patents by Inventor Francois Pierre Ribassin

Francois Pierre Ribassin 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).

  • Configuring and positioning air passage holes in a combustion chamber wall
    Patent number: 11441779
    Abstract: The provision of air passage holes through a wall of a gas turbomachine combustion chamber. Multi-perforations are virtually positioned and distributed, even in a first safety zone without air passage openings. Multi-perforations with a virtual inlet or outlet in this first security zone are virtually removed. According to certain criteria, at least some of said removed multi-perforations are then virtually reintegrated, and, from then on a perimeter passing through the virtual inlets and outlets of all the multi-perforations present is defined, in the direction of a primary or dilution hole to be installed, a modified safety zone is defined, then, respecting around said hole and with the freedom to reposition it within this limit, the shape of this hole is redefined.
    Type: Grant
    Filed: April 16, 2020
    Date of Patent: September 13, 2022
    Assignee: Safran Aircraft Engines
    Inventors: François Pierre Ribassin, Patrice André Commaret, Romain Nicolas Lunel, Christophe Pieussergues
  • CONFIGURING AND POSITIONING AIR PASSAGE HOLES IN A COMBUSTION CHAMBER WALL
    Publication number: 20200333008
    Abstract: The provision of air passage holes through a wall of a gas turbomachine combustion chamber. Multi-perforations are virtually positioned and distributed, even in a first safety zone without air passage openings. Multi-perforations with a virtual inlet or outlet in this first security zone are virtually removed. According to certain criteria, at least some of said removed multi-perforations are then virtually reintegrated, and, from then on a perimeter passing through the virtual inlets and outlets of all the multi-perforations present is defined, in the direction of a primary or dilution hole to be installed, a modified safety zone is defined, then, respecting around said hole and with the freedom to reposition it within this limit, the shape of this hole is redefined.
    Type: Application
    Filed: April 16, 2020
    Publication date: October 22, 2020
    Applicant: Safran Aircraft Engines
    Inventors: François Pierre Ribassin, Patrice André Commaret, Romain Nicolas Lunel, Christophe Pieussergues
  • NOZZLE RING ADHESIVE BONDED BLADING FOR AIRCRAFT ENGINE COMPRESSOR
    Publication number: 20090148283
    Abstract: A compressor nozzle ring for an aircraft includes an inner shroud, an outer shroud and a multiplicity of blades extending from the inner shroud to the outer shroud. Each blade passes through the inner shroud and is attached to it with sealing cement containing an organic polymer adhesive. The adhesive is polyimide based.
    Type: Application
    Filed: September 20, 2006
    Publication date: June 11, 2009
    Applicant: SNECMA MOTEURS
    Inventors: Claude Marcel Mons, Sandra Andrieu, Manuel Girard, Francois Pierre Ribassin
  • Nozzle ring with adhesive bonded blading for aircraft engine compressor
    Publication number: 20050129514
    Abstract: Blades (3) extending radially from the inner shroud (1) to the outer shroud (2) are attached to the inner shroud by means of a sealing cement containing an organic polyimide-based polymer adhesive.
    Type: Application
    Filed: June 28, 2004
    Publication date: June 16, 2005
    Applicant: SNECMA MOTEURS
    Inventors: Claude Mons, Sandra Andrieu, Manuel Girard, Francois Pierre Ribassin