Patents by Inventor Faouzi ALIOUAT

Faouzi ALIOUAT 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).

  • Air-sealing device intended to be inserted between an aircraft dual-flow turbine engine casing element, and a nacelle element
    Patent number: 11746706
    Abstract: An air-sealing device intended to be inserted between an aircraft dual-flow turbine engine casing element and a nacelle element, the sealing device including an attachment tab at the end of which is located a sealing portion having an outer surface intended to be contacted by the casing element and the nacelle element, and an inner surface defining a cavity. The inner surface defines at least one protuberance extending inside the cavity.
    Type: Grant
    Filed: November 19, 2019
    Date of Patent: September 5, 2023
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Bruno Alexandre Didier Jacon, Baghdad Achbari, Faouzi Aliouat, Hervé Simonotti
  • IMPROVED AIR-SEALING DEVICE INTENDED TO BE INSERTED BETWEEN AN AIRCRAFT DUAL-FLOW TURBINE ENGINE CASING ELEMENT, AND A NACELLE ELEMENT
    Publication number: 20210332762
    Abstract: An air-sealing device intended to be inserted between an aircraft dual-flow turbine engine casing element and a nacelle element, the sealing device including an attachment tab at the end of which is located a sealing portion having an outer surface intended to be contacted by the casing element and the nacelle element, and an inner surface defining a cavity. The inner surface defines at least one protuberance extending inside the cavity.
    Type: Application
    Filed: November 19, 2019
    Publication date: October 28, 2021
    Inventors: Bruno Alexandre Didier JACON, Baghdad ACHBARI, Faouzi ALIOUAT, Hervé SIMONOTTI
  • Annular casting and shrink-fitted part of an aircraft turbine engine
    Patent number: 10920619
    Abstract: A part for a turbine engine, the part having a general annular shape about an axis of revolution, this part including a first annular shrink-fitted mounting flange and comprising an annular row of orifices for the passage of screws, this part being made by casting and including protruding pads required for the control and the manufacture of the part by casting, wherein the pads are located on the flange and in that each comprises a thread configured to engage with an extraction screw of the flange.
    Type: Grant
    Filed: June 19, 2019
    Date of Patent: February 16, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Etienne Gerard Joseph Canelle, Jacques Marcel Arthur Bunel, Faouzi Aliouat
  • ANNULAR CASTING AND SHRINK-FITTED PART OF AN AIRCRAFT TURBINE ENGINE
    Publication number: 20190390571
    Abstract: A part for a turbine engine, the part having a general annular shape about an axis of revolution, this part including a first annular shrink-fitted mounting flange and comprising an annular row of orifices for the passage of screws, this part being made by casting and including protruding pads required for the control and the manufacture of the part by casting, wherein the pads are located on the flange and in that each comprises a thread configured to engage with an extraction screw of the flange.
    Type: Application
    Filed: June 19, 2019
    Publication date: December 26, 2019
    Inventors: Etienne Gerard Joseph CANELLE, Jacques Marcel Arthur BUNEL, Faouzi ALIOUAT