Patents by Inventor Sébastien Baboeuf

Sébastien Baboeuf 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).

  • Method of improving the ignition performance of an after-burner device for a bypass turbojet, and an after-burner device of improved ignition performance
    Patent number: 7584615
    Abstract: The after-burner device receives a “hot” central primary flow from the turbine of the turbojet and a “cold” peripheral secondary flow, and it has an after-burner ignition zone situated in the secondary flow that reaches the after-burner device. A fraction of the primary flow is brought into the after-burner ignition zone in order to raise the temperature in said zone to a value that is higher than that of the secondary flow so as to encourage after-burner ignition.
    Type: Grant
    Filed: February 24, 2005
    Date of Patent: September 8, 2009
    Assignee: SNECMA
    Inventors: Sébastien Baboeuf, Sabine Charpenel, Eric Maingre, Alain Page, Jacques Roche
  • After-burner chamber with secure ignition
    Publication number: 20060292504
    Abstract: A turbojet having an after-burner chamber presenting a specific injector opening into the burner ring to provide secure ignition. The after-burner chamber has an annular fuel injection duct, an ignition spark plug, and an ignition injector installed facing the spark plug and connected to specific fuel feed means.
    Type: Application
    Filed: July 15, 2005
    Publication date: December 28, 2006
    Applicant: SNECMA MOTEURS
    Inventors: Sebastien Baboeuf, Sabine Charpenel, Didier Durand, Jacques Roche
  • Ventilation channels in an afterburner chamber confluence sheet
    Patent number: 6976361
    Abstract: The invention relates to ventilating the confluence sheet of an afterburner chamber of an aviation turbomachine, including, upstream from the afterburner chamber: a diffuser defined by a confluence sheet disposed inside a casing, said casing and said confluence sheet defining between them an annular channel for a cold secondary flow, upstream fuel injectors being disposed at the inlet to said diffuser and flame-catchers being disposed downstream from said upstream injectors, said confluence sheet presenting, between the radial plane containing said upstream injectors and the radial plane situated at the rear ends of said flame-catchers two bends so as to flare downstream in order to slow down the primary flow F1 downstream from said upstream injectors.
    Type: Grant
    Filed: June 22, 2004
    Date of Patent: December 20, 2005
    Assignee: Snecma Moteurs
    Inventors: Thierry Cortes, Alain Page, Sébastien Baboeuf, Jacques Roche
  • VENTILATION CHANNELS IN AN AFTERBURNER CHAMBER CONFLUENCE SHEET
    Publication number: 20050274114
    Abstract: The invention relates to ventilating the confluence sheet of an afterburner chamber of an aviation turbomachine, including, upstream from the afterburner chamber: a diffuser defined by a confluence sheet disposed inside a casing, said casing and said confluence sheet defining between them an annular channel for a cold secondary flow, upstream fuel injectors being disposed at the inlet to said diffuser and flame-catchers being disposed downstream from said upstream injectors, said confluence sheet presenting, between the radial plane containing said upstream injectors and the radial plane situated at the rear ends of said flame-catchers two bends so as to flare downstream in order to slow down the primary flow F1 downstream from said upstream injectors.
    Type: Application
    Filed: June 22, 2004
    Publication date: December 15, 2005
    Applicant: SNECMA MOTEURS
    Inventors: Thierry Cortes, Alain Page, Sebastien Baboeuf, Jacques Roche
  • Method of improving the ignition performance of an after-burner device for a bypass turbojet, and an after-burner device of improved ignition performance
    Publication number: 20050257527
    Abstract: The after-burner device receives a “hot” central primary flow from the turbine of the turbojet and a “cold” peripheral secondary flow, and it has an after-burner ignition zone situated in the secondary flow that reaches the after-burner device. A fraction of the primary flow is brought into the after-burner ignition zone in order to raise the temperature in said zone to a value that is higher than that of the secondary flow so as to encourage after-burner ignition.
    Type: Application
    Filed: February 24, 2005
    Publication date: November 24, 2005
    Applicant: SNECMA MOTEURS
    Inventors: Sebastien Baboeuf, Sabine Charpenel, Eric Maingre, Alain Page, Jacques Roche