Patents by Inventor Ollivier Carletti

Ollivier Carletti 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: 5467592
    Abstract: A sectorized tubular structure able to resist implosion pressures, especially at the links between annular sectors. The tubular structure includes annular sectors interconnected by flat linking elements, each including at its ends at least one projection whose end enables the annular sectors to be supported. Thus, each linking element ensures the transmission of forces from one annular element to another. The unit is supported by fixing screws which are never in contact with the two annular sectors to be kept assembled.
    Type: Grant
    Filed: June 29, 1994
    Date of Patent: November 21, 1995
    Assignee: Societe Nationale d'Etude et de Construction de Moteurs d'Aviation "Snecma"
    Inventor: Ollivier Carletti
  • Patent number: 5437412
    Abstract: A variable cross-section nozzle for a jet engine is disclosed having main inner (hot) flaps defining an inner nozzle and main outer (cold) flaps defining an outer nozzle with adjacent main flaps interconnected by secondary flaps, such that actuators connected to two of the main flaps can vary the cross-sectional configuration of the exhaust nozzle outlet between a substantially circular configuration to one which is subsequentally or completely closed. The actuator is mechanically connected to the main inner and main outer flaps such that the nozzle configuration may be varied using a minimum number of actuators. A single outer nozzle may surround a pair of inner nozzles such as utilized on a dual jet engine aircraft.
    Type: Grant
    Filed: June 23, 1994
    Date of Patent: August 1, 1995
    Assignee: Societe Nationale d'Etude et de Construction de Moteurs d'Aviation (S.N.E.C.M.A.)
    Inventor: Ollivier Carletti
  • Patent number: 5421704
    Abstract: A separate inter-blade platform for a turbomachine rotor comprises a structural rectilinear longitudinal member formed by a foam core, plies of a carbon/epoxy type material in bidirectional layers of crossed fibres oriented at 45.degree. laid around the core and around an insert at each end of the longitudinal member, each insert being made of juxtaposed radial plies of a carbon/epoxy type material in bidirectional layers of fibres crossed at .+-.45 degrees, and further plies of a carbon/epoxy type material in unidirectional layers oriented in the direction of the major axis of the longitudinal member covering the upper and lower faces of the member, the platform further comprising lateral packing cores made of a foam material, plies of a glass/epoxy type material covering the lateral faces of the longitudinal member and connecting it to the lateral foam cores, and peripheral plies of a glass/epoxy type material covering the assembly formed by the longitudinal member and the lateral cores connected thereto.
    Type: Grant
    Filed: June 10, 1994
    Date of Patent: June 6, 1995
    Assignee: Societe Nationale d'Etude et de Construction de Moteurs d'Aviation "SNECMA"
    Inventors: Ollivier Carletti, Gerard F. Inizan, Gerard E. A. Jourdain, Francois M. P. Marlin, Philippe J. P. Pabion, Thierry G. Pancou, Laurence Prato, Dominique Raulin, Christine J. G. Ruffier
  • Patent number: 5094563
    Abstract: A device for use in fixing an element to a panel of sandwich or hollow construction comprising two parallel skins, the device acting as a spacer and comprising two bushes each having a plurality of circumferentially spaced fingers extending axially from a tubular part at one end of the bush, the bushes being placed head to tail in such a way that the fingers of each bush alternate with the fingers of the other. The free ends of the fingers of each bush spread outwards and act upon the inner face of the opposite skin, the tubular part of the bush being located in a hole of the respective skin and having an axial face forming a bearing surface for the fastening member or the element.
    Type: Grant
    Filed: February 1, 1991
    Date of Patent: March 10, 1992
    Assignee: Societe Nationale d'Etude et de Construction de Moteurs d'Aviation "S.N.E.C.M.A."
    Inventor: Ollivier Carletti
  • Patent number: 5083900
    Abstract: A turbo-machine stator element comprising an array of fixed blades mounted on a ring has the head of each blade embedded in an aperture in the ring by fixing member comprising first and second interfitting members each consisting of a plate portion and an integral socket portion. The socket of one of the members fits into the aperture, and the socket of the other member fits into the socket of the first member and houses the head of the blade. The plate portions of the two members sandwich the ring around the aperture.
    Type: Grant
    Filed: November 1, 1990
    Date of Patent: January 28, 1992
    Assignee: Societe Nationale d'Etude et de Construction de Moteurs d'Aviation "S.N.E.C.M.A."
    Inventors: Ollivier Carletti, Michel, E. A. J. Thomas