Patents by Inventor Philippe Fessou

Philippe Fessou 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).

  • Publication number: 20080063515
    Abstract: The bypass turbomachine comprises, between a primary flowpath (2) and a secondary flowpath (3), a structural intermediate casing (14). A bleed passage (29) allows the diversion of a portion of the gas stream toward the secondary flowpath (3), downstream of support arms (18) situated at the periphery of the intermediate casing. A bleed opening (28) emerges upstream of the support arms (18). A slide valve (22) slides between three positions, namely a closed position in which the slide valve (22) completely blocks off the bleed passage and opening, an intermediate position in which the bleed opening (28) emerging upstream of the support arms (18) is blocked off, while the bleed passage (29) for diverting a portion of the gas stream downstream of the support arms (18) is open, and an open position in which the bleed opening (28) emerging upstream of the support arms (18) and the bleed passage (29) emerging downstream of the support arms are both open.
    Type: Application
    Filed: May 31, 2007
    Publication date: March 13, 2008
    Applicant: SNECMA
    Inventors: Eric BIL, Gilles Charier, Philippe Fessou, Patrick Morel
  • Patent number: 7121792
    Abstract: A nozzle vane for a rotary disk of a turbomachine, the vane comprising pressure side and suction side surfaces extending radially between a base and a tip and longitudinally between a leading edge and a trailing edge, with a plurality of vane sections having centers of gravity aligned along a stacking axis, the vane presenting a lower portion, an intermediate portion, and an upper portion, the lower portion extending radially between the base of the vane and a lower limit of the intermediate portion, and the upper portion extending radially between an upper limit of the intermediate portion and the tip of the vane, the stacking axis presenting, in the lower and upper portions, a tangential component that is substantially radial, and in the intermediate portion, a tangential component with two slopes.
    Type: Grant
    Filed: March 25, 2004
    Date of Patent: October 17, 2006
    Assignee: SNECMA Moteurs
    Inventors: Philippe Fessou, Mario Blozovski, Herve Quiniou
  • Publication number: 20060222488
    Abstract: A nozzle vane for a rotary disk of a turbomachine, the vane comprising pressure side and suction side surfaces extending radially between a base and a tip and longitudinally between a leading edge and a trailing edge, with a plurality of vane sections having centers of gravity aligned along a stacking axis, the vane presenting a lower portion, an intermediate portion, and an upper portion, the lower portion extending radially between the base of the vane and a lower limit of the intermediate portion, and the upper portion extending radially between an upper limit of the intermediate portion and the tip of the vane, the stacking axis presenting, in the lower and upper portions, a tangential component that is substantially radial, and in the intermediate portion, a tangential component with two slopes.
    Type: Application
    Filed: March 25, 2004
    Publication date: October 5, 2006
    Applicant: SNECMA MOTEURS
    Inventors: Philippe Fessou, Mario Blozovski, Herve Quiniou
  • Patent number: 7108486
    Abstract: A rotary turbojet blade comprises a plurality of blade sections extending along a line of the centers of gravity of said sections between a base and a tip, said blade presenting along a radial axis a bottom portion, an intermediate portion, and a top portion, said bottom portion presenting a longitudinal angle of inclination for a leading edge line, said intermediate portion presenting a backward longitudinal angle of inclination for said leading edge line, and said top portion presenting a backward longitudinal angle of inclination for said leading edge line and a tangential angle of inclination for said line of the centers of gravity in a direction opposite to the direction of rotation of said blade.
    Type: Grant
    Filed: February 12, 2004
    Date of Patent: September 19, 2006
    Assignee: Snecma Moteurs
    Inventors: Jerome Talbotec, Philippe Fessou, Herbert Joly, Beatrice Bois
  • Patent number: 5740674
    Abstract: The arrangement of a gas turbine engine suitable for high bypass ratio aircraft engines in which gases circulate in a primary air channel (7) and a secondary channel (8) concentric to said primary air channel, is characterized in that structural vanes (22) connecting the channel delimitation casings (2, 10, 14, 5) with each other, alternate with aerodynamic vanes (20) for guiding the gases on a common circumference of the engine bypass air channel (8), and in that the structural channels branch out between the two channels. The resulting advantages are simplicity of construction associated with a reduction in the space required for housing the channels and good resistance without notable increase of the total mass.
    Type: Grant
    Filed: August 15, 1996
    Date of Patent: April 21, 1998
    Assignee: Societe Nationale d'Etude Et de Construction de Moteurs d'Aviation "Sherma"
    Inventors: Bruno Beutin, Jean-Louis Charbonnel, Andre Collot, Claude Dejaune, Alain Espenel, Philippe Fessou, Jean-Claude Gregoire, Daniel Martin, Herve Paitre, Jean-Francois Ranvier, Monique Thore