Patents by Inventor Fabrice Michel Olivier Cot

Fabrice Michel Olivier Cot 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).

  • Linking arrangement of a turbine stator ring to a support strut
    Patent number: 6699011
    Abstract: A strut (1) fixed to a main portion of turbojet stator carries a ring (5) by a pair of hooks (4, 6) on one side and joining lips (7 and 8) on the other side. In accordance with the invention, the seal is made on the flat sides (10, 11) adjacent to the lips by elastic deflection of the tabs (13) pushing back one of the lips (7). The tabs (13) can also determine the tangential positioning of the ring (5).
    Type: Grant
    Filed: October 15, 2001
    Date of Patent: March 2, 2004
    Assignee: SNECMA Moteurs
    Inventors: Fabrice Michel Olivier Cot, Alain Dominique Gendraud, Philippe Jean-Pierre Pabion
  • Linking arrangement of a turbine stator ring to a support strut
    Publication number: 20020048512
    Abstract: A strut (1) fixed to a main portion of turbojet stator carries a ring (5) by a pair of hooks (4, 6) on one side and joining lips (7 and 8) on the other side. In accordance with the invention, the seal is made on the flat sides (10, 11) adjacent to the lips by elastic deflection of the tabs (13) pushing back one of the lips (7). The tabs (13) can also determine the tangential positioning of the ring (5).
    Type: Application
    Filed: October 15, 2001
    Publication date: April 25, 2002
    Applicant: SNECMA MOTEURS
    Inventors: Fabrice Michel Olivier Cot, Alain Dominique Gendraud, Philippe Jean-Pierre Pabion
  • Converging exhaust nozzle fitted with translating cold flaps
    Patent number: 6164563
    Abstract: A gas-flow exhaust assembly for a jet propulsion system of an aircraft in which a converging exhaust nozzle (4) is fitted with translating cold flaps (21, 22). The primary exhaust nozzle (4) comprises two hot-flaps (5, 6) situated beyond a primary duct (1) enclosed by an aircraft fairing (2). The fairing (2) is extended by a secondary exhaust nozzle (20) which is supported by the primary duct (1) and which is translatable by a control mechanism (27a, 27b). The secondary exhaust nozzle (20) comprises cold flaps (21, 22) which are driven by another control mechanism (29a, 29b) independently of the angular positions of the hot flaps (5, 6). Preferably, there are two eyelid-shaped cold-flaps (21, 22) hinging and supported on horizontal transverse shafts (23a, 23b). The shafts (23a, 23b) are preferably affixed on two lateral slides (24a, 24b) which slide on the primary duct (1) and are displaceable by the control mechanism (27a, 27b) which translates the secondary exhaust nozzle (20).
    Type: Grant
    Filed: July 16, 1999
    Date of Patent: December 26, 2000
    Assignee: Societe Nationale d'Etude et de Construction de Moteurs d'Aviation "Snecma"
    Inventors: Philippe Pierre Vincent Bouiller, Pierre-Yves Bourquin, Fabrice Michel Olivier Cot, Daniel Kettler, Jean-Pierre Ruis