Patents by Inventor Yves R. J. Berneuil

Yves R. J. Berneuil 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: 5611489
    Abstract: An actuating system for a variable area exhaust nozzle is disclosed having inner and outer flaps pivotally connected to an airframe whose positions may be varied by a single set of control cylinders. The control cylinders have a case in which is slidably mounted a pair of pistons, each having piston rods extending from one side, which piston rods extend through one end of the cylinder case. The piston rods may be arranged coaxially to minimize the bulk of the actuating cylinder. One of the piston rods is connected to the inner flaps, while the other of the piston rods is connected to the outer flaps.
    Type: Grant
    Filed: May 18, 1993
    Date of Patent: March 18, 1997
    Assignee: Societe Nationale d'Etude et de Construction de Moteurs d'Aviation S.N.E.C.M.A.
    Inventors: Yves R. J. Berneuil, Christian W. B. Bettremieux, Daniel G. A. Kettler, Michel M. A. A. Lechevalier, Xavier J. Pasquali, Jean-Marie N. Pincemin
  • Patent number: 5029439
    Abstract: A gas turbine engine is provided with a braking device for stopping the compressor drive turbine if a common shaft interconnecting the turbine and compressor rotors breaks, the braking device including a conical ring carried by the turbine rotor at its downstream end and a structural member of a generally conical shape carried by the upstream end of the turbine exhaust casing such that the ring will frictionally interlock with the structural member if the shaft breaks.
    Type: Grant
    Filed: December 7, 1989
    Date of Patent: July 9, 1991
    Assignee: Societe National d'Etude et de Construction de Moteurs d'Aviation "S.N.E.C.M.A."
    Inventors: Yves R. J. Berneuil, Gilles L. E. Delrieu
  • Patent number: 4817871
    Abstract: The system according to the invention has an annular array of converging flaps, diverging flaps and cold flaps attached to the downstream edge of the turbojet engine exhaust duct by several pairs of longitudinally extending support beams. The pairs of beams are interconnected and the flap actuators are located between such interconnected pairs of support beams. The control system has a plurality of generally straight control shafts extending around the circumference of the converging and diverging flaps. The control shafts are interconnected with the actuators, the support beams, the diverging flaps and the cold flaps to ensure that the flaps are synchronously adjusted to their desired positions. Triangularly shaped link members are attached to each end of the control shafts and serve to interconnect adjacent shafts. A base of each of the link members is pivotally attached to an end of the control shaft, while a universal-type ball joint interconnects the adjacent apexes of the triangular link members.
    Type: Grant
    Filed: July 5, 1988
    Date of Patent: April 4, 1989
    Assignee: Societe Nationale d'Etude et de Consturction de Moteurs d'Aviation (SNECMA)
    Inventors: Yves R. J. Berneuil, Gerard E. A. Jourdain