Patents by Inventor Jean-Francois Antoine, Christian Rios

Jean-Francois Antoine, Christian Rios 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).

  • Turbomachine centre blade comprising a curved portion
    Patent number: 10309419
    Abstract: A turbomachine compressor blade of main radial orientation with respect to a main axis of the turbomachine. The blade includes a radially internal root portion, a radially external tip portion, a radially intermediate portion, a curved portion tangentially in a direction, and at least one straight portion on the root portion and/or on the tip portion.
    Type: Grant
    Filed: October 11, 2012
    Date of Patent: June 4, 2019
    Assignee: SAFRAN AIRCARFT ENGINES
    Inventors: Damien Cellier, Alicia Lise Julia Dufresne, Philippe Pierre Marcel Marie Pelletrau, Vincent Paul Gabriel Perrot, Jean-Francois Antoine Christian Rios, Laurent Christophe Francis Villaines
  • Turbine engine blade, in particular for a one-piece bladed disk
    Patent number: 9556740
    Abstract: A turbine engine blade comprising an airfoil extending axially between a leading edge and a trailing edge and extending radially between a root and a tip. The leading edge of the airfoil presents a sweep angle that is positive and that increases continuously from the root to a first radial height of the airfoil situated in the range 20% to 40% of the total radial height of the airfoil as measured from the root to the tip, and decreases continuously from this first radial height of the airfoil to the tip.
    Type: Grant
    Filed: November 22, 2012
    Date of Patent: January 31, 2017
    Assignee: SNECMA
    Inventors: Vincent Paul Gabriel Perrot, Damien Cellier, Alicia Lise Julia Dufresne, Philippe Pierre Marcel Marie Pelletrau, Jean-Francois Antoine Christian Rios, Laurent Christophe Francis Villaines
  • TURBINE ENGINE BLADE, IN PARTICULAR FOR A ONE-PIECE BLADED DISK
    Publication number: 20140341749
    Abstract: A turbine engine blade comprising an airfoil extending axially between a leading edge and a trailing edge and extending radially between a root and a tip. The leading edge of the airfoil presents a sweep angle that is positive and that increases continuously from the root to a first radial height of the airfoil situated in the range 20% to 40% of the total radial height of the airfoil as measured from the root to the tip, and decreases continuously from this first radial height of the airfoil to the tip.
    Type: Application
    Filed: November 22, 2012
    Publication date: November 20, 2014
    Applicant: SNECMA
    Inventors: Vincent Paul Gabriel Perrot, Damien Cellier, Alicia Lise, Julia Dufresne, Philippe Pierre Marcel Marie Pelletrau, Jean-Francois Antoine Christian Rios, Laurent Christophe Francis Villaines
  • TURBOMACHINE CENTRE BLADE COMPRISING A CURVED PORTION
    Publication number: 20140248144
    Abstract: A turbomachine compressor blade of main radial orientation with respect to a main axis of the turbomachine. The blade includes a radially internal root portion, a radially external tip portion, a radially intermediate portion, a curved portion tangentially in a direction, and at least one straight portion on the root portion and/or on the tip portion.
    Type: Application
    Filed: October 11, 2012
    Publication date: September 4, 2014
    Applicant: SNECMA
    Inventors: Damien Cellier, Alicia Lise, Julia Dufresne, Philippe Pierre Marcel, Marie Pelletrau, Vincent Paul, Gabriel Perrot, Jean-Francois Antoine, Christian Rios, Laurent Christophe, Francis Villaines