Patents by Inventor Benjamin Frantz Karl VILLENAVE

Benjamin Frantz Karl VILLENAVE 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).

  • Patent number: 11971174
    Abstract: A turbomachine has the upstream portion of the annular combustion chamber is fixed to the outer housing via individual pins with a swivel connection. The swivel connection is established between the pin and a part of the outer housing. The pin is slidable radially, or with a radial component, by a slide established between the pin and a tubular part of the outer annular shroud and/or the annular wall of the chamber bottom.
    Type: Grant
    Filed: May 14, 2020
    Date of Patent: April 30, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Dan-Ranjiv Joory, Jacques Marcel Arthur Bunel, Benjamin Frantz Karl Villenave
  • Patent number: 11808456
    Abstract: A combustion chamber includes a bottom wall having at least one opening, at least one sleeve mounted upstream of the bottom wall and fixed to the bottom wall, a closing ring defining an annular groove with the sleeve and fixed to the sleeve, and at least one air and fuel injection system having an axis, mounted in the opening of the bottom wall. The injection system has an annular flange extending radially with respect to the axis and is mounted in the groove with radial clearance. A baffle is situated downstream of the bottom wall and is fixed to the sleeve and/or to the bottom wall.
    Type: Grant
    Filed: February 19, 2020
    Date of Patent: November 7, 2023
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Jacques Marcel Arthur Bunel, William Louis Rodolphe Dousse, Benjamin Frantz Karl Villenave
  • Patent number: 11802512
    Abstract: The invention relates to a combustion chamber for a gas turbine engine, in which two openings extend through a metal wall (58) and a wall made of a refractory material (16). A device (76) guides a spark plug (48) in said two orifices, the guiding device comprising a metal flange (80) and a floating ring (82), the flange being shrunk onto or welded to the metal wall (58).
    Type: Grant
    Filed: April 13, 2021
    Date of Patent: October 31, 2023
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Jacques Marcel Arthur Bunel, William Louis Rodolphe Dousse, Dan-Ranjiv Joory, Benjamin Frantz Karl Villenave
  • Patent number: 11725822
    Abstract: The invention concerns a turbo engine comprising a combustion chamber (110) arranged inside the outer housing (112) and comprising an internal revolution wall (118) and an external revolution wall (116). First stop parts (54) and second stop parts (56) fixed respectively to the outer housing and to the combustion chamber are provided, the first and second stop parts being adapted to come to a substantially axial stop two by two by forming stop pairs (58).
    Type: Grant
    Filed: May 28, 2019
    Date of Patent: August 15, 2023
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Romain Nicolas Lunel, Damien Bonnefoi, Christophe Pieussergues, Luc Namer, Dominique Raulin, Dan Ranjiv Joory, Benjamin Frantz Karl Villenave
  • Publication number: 20230151770
    Abstract: The invention relates to a combustion chamber for a gas turbine engine, in which two openings extend through a metal wall (58) and a wall made of a refractory material (16). A device (76) guides a spark plug (48) in said two orifices, the guiding device comprising a metal flange (80) and a floating ring (82), the flange being shrunk onto or welded to the metal wall (58).
    Type: Application
    Filed: April 13, 2021
    Publication date: May 18, 2023
    Inventors: Jacques Marcel Arthur BUNEL, William Louis Rodolphe DOUSSE, Dan-Ranjiv JOORY, Benjamin Frantz Karl VILLENAVE
  • Publication number: 20220196243
    Abstract: A turbomachine has the upstream portion of the annular combustion chamber is fixed to the outer housing via individual pins with a swivel connection. The swivel connection is established between the pin and a part of the outer housing. The pin is slidable radially, or with a radial component, by a slide established between the pin and a tubular part of the outer annular shroud and/or the annular wall of the chamber bottom.
    Type: Application
    Filed: May 14, 2020
    Publication date: June 23, 2022
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Dan-Ranjiv JOORY, Jacques Marcel Arthur BUNEL, Benjamin Frantz Karl VILLENAVE
  • Patent number: 11333358
    Abstract: A combustion chamber for a gas turbomachine. The combustion chamber comprising inner and outer walls, a chamber bottom, and a heat shield arranged downstream of the chamber bottom, to protect it thermally. The inner and outer walls and the heat shield form a one-piece unit.
    Type: Grant
    Filed: July 24, 2019
    Date of Patent: May 17, 2022
    Assignee: Safran Aircraft Engines
    Inventors: Jacques Marcel Arthur Bunel, William Louis Rodolphe Dousse, Dan Ranjiv Joory, Benjamin Frantz Karl Villenave
  • Publication number: 20220018543
    Abstract: A combustion chamber includes a bottom wall having at least one opening, at least one sleeve mounted upstream of the bottom wall and fixed to the bottom wall, a closing ring defining an annular groove with the sleeve and fixed to the sleeve, and at least one air and fuel injection system having an axis, mounted in the opening of the bottom wall. The injection system has an annular flange extending radially with respect to the axis and is mounted in the groove with radial clearance. A baffle is situated downstream of the bottom wall and is fixed to the sleeve and/or to the bottom wall.
    Type: Application
    Filed: February 19, 2020
    Publication date: January 20, 2022
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: JACQUES MARCEL ARTHUR BUNEL, WILLIAM LOUIS RODOLPHE DOUSSE, BENJAMIN FRANTZ KARL VILLENAVE
  • Patent number: 11085640
    Abstract: A method for producing an annular combustion chamber of a turbojet using CMC. For this, a shaping tool with movable slides is used and said chamber is produced around the tool, thereby producing a fibrous preform of which the shape is consolidated by drape moulding on the tool and pyrolysis, which is then densified by CVI. Several slides have back drafts, at least one other of such slides having a draft or neither a draft nor a back draft. Then, the slides are removed in a predetermined order imposed by the back drafts and the relative positions of the slides.
    Type: Grant
    Filed: July 24, 2019
    Date of Patent: August 10, 2021
    Assignee: Sanfran Aircraft Engines
    Inventors: Jacques Marcel Arthur Bunel, William Louis Rodolphe Dousse, Dan Ranjiv Joory, Benjamin Frantz Karl Villenave
  • Publication number: 20200103111
    Abstract: A method for producing an annular combustion chamber of a turbojet using CMC. For this, a shaping tool with movable slides is used and said chamber is produced around the tool, thereby producing a fibrous preform of which the shape is consolidated by drape moulding on the tool and pyrolysis, which is then densified by CVI. Several slides have back drafts, at least one other of such slides having a draft or neither a draft nor a back draft. Then, the slides are removed in a predetermined order imposed by the back drafts and the relative positions of the slides.
    Type: Application
    Filed: July 24, 2019
    Publication date: April 2, 2020
    Applicant: Safran Aircraft Engines
    Inventors: Jacques Marcel Arthur Bunel, William Louis Rodolphe Dousse, Dan Ranjiv Joory, Benjamin Frantz Karl Villenave
  • Publication number: 20200033004
    Abstract: A combustion chamber for a gas turbomachine. The combustion chamber comprising inner and outer walls, a chamber bottom, and a heat shield arranged downstream of the chamber bottom, to protect it thermally. The inner and outer walls and the heat shield form a one-piece unit.
    Type: Application
    Filed: July 24, 2019
    Publication date: January 30, 2020
    Applicant: Safran Aircraft Engines
    Inventors: Jacques Marcel Arthur Bunel, William Louis Rodolphe Dousse, Dan Ranjiv Joory, Benjamin Frantz Karl Villenave
  • Publication number: 20190383489
    Abstract: The invention concerns a turbo engine comprising a combustion chamber (110) arranged inside the outer housing (112) and comprising an internal revolution wall (118) and an external revolution wall (116). First stop parts (54) and second stop parts (56) fixed respectively to the outer housing and to the combustion chamber are provided, the first and second stop parts being adapted to come to a substantially axial stop two by two by forming stop pairs (58).
    Type: Application
    Filed: May 28, 2019
    Publication date: December 19, 2019
    Inventors: Romain Nicolas LUNEL, Damien BONNEFOI, Christophe PIEUSSERGUES, Luc NAMER, Dominique RAULIN, Dan Ranjiv JOORY, Benjamin Frantz Karl VILLENAVE