Patents by Inventor Raphael Curtelin

Raphael Curtelin 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).

  • Ventilation system for a convergent divergent exhaust nozzle
    Patent number: 7296397
    Abstract: The invention relates to a ventilation system for a convergent divergent exhaust nozzle in a bypass turbojet comprising an afterburn chamber surrounded by an annular passage through which circulates a stream of cooling air, a convergent divergent axisymmetric nozzle arranged downstream of said afterburn chamber, each circle of flaps comprising alternately a plurality of controlled flaps, and a plurality of follower flaps, a circle of cold flaps arranged radially outside said nozzle and hinged at their upstream end to a conical shell linked to the downstream part of the casing.
    Type: Grant
    Filed: September 22, 2004
    Date of Patent: November 20, 2007
    Assignee: SNECMA Moteurs
    Inventors: Raphael Curtelin, Marc Doussinault, Guy Lapergue, Didier Durand
  • Device for supplying cooling air to exhaust nozzle flaps
    Patent number: 7213393
    Abstract: A device for supplying cooling air to a hollow flap of an exhaust nozzle in a turbojet engine. The device includes a tube connecting the hollow flap to a cooling air source. The tube comprises at least one telescopic portion and at least one ball-joint connection.
    Type: Grant
    Filed: January 3, 2005
    Date of Patent: May 8, 2007
    Assignee: Snecma Moteurs
    Inventors: Guy Lapergue, Raphael Curtelin, Didier Feder
  • Convergent-divergent turbojet nozzle
    Patent number: 6993914
    Abstract: The present invention relates to a convergent-divergent turbojet nozzle (1) comprising driven divergent flaps (4a), follower divergent flaps (4b) interposed between the driven flaps, and means (32) for supplying cooling air to the follower flaps (4b), said follower flaps (4b) having a box structure and having lateral openings for delivering cooling air towards the inner face of said driven flaps (4a), in such a way as to limit the heating up of these flaps when the turbojet is in operation.
    Type: Grant
    Filed: August 11, 2004
    Date of Patent: February 7, 2006
    Assignee: Snecma Moteurs
    Inventors: Jackie Prouteau, Raphaël Curtelin, Guy Lapergue, Didier Feder
  • Device for supplying cooling air to exhaust nozzle flaps
    Publication number: 20050210864
    Abstract: The device of the invention for supplying cooling air to a flap of an exhaust nozzle in a gas turbine, comprises a tube connecting the flap to a cooling air source. The tube comprises at least one telescopic portion and one ball-joint connection.
    Type: Application
    Filed: January 3, 2005
    Publication date: September 29, 2005
    Applicant: SNECMA MOTEURS
    Inventors: Guy Lapergue, Raphael Curtelin, Didier Feder
  • Ventilation system for a convergent divergent exhaust nozzle
    Publication number: 20050091964
    Abstract: The invention relates to a ventilation system for a convergent divergent exhaust nozzle in a bypass turbojet comprising an afterburn chamber surrounded by an annular passage through which circulates a stream of cooling air, a convergent divergent axisymmetric nozzle arranged downstream of said afterburn chamber, each circle of flaps comprising alternately a plurality of controlled flaps, and a plurality of follower flaps, a circle of cold flaps arranged radially outside said nozzle and hinged at their upstream end to a conical shell linked to the downstream part of the casing.
    Type: Application
    Filed: September 22, 2004
    Publication date: May 5, 2005
    Applicant: SNECMA MOTEURS
    Inventors: Raphael Curtelin, Marc Doussinault, Guy Lapergue, Didier Durand
  • Convergent-divergent turbojet nozzle
    Publication number: 20050060984
    Abstract: The present invention relates to a convergent-divergent turbojet nozzle (1) comprising driven divergent flaps (4a), follower divergent flaps (4b) interposed between the driven flaps, and means (32) for supplying cooling air to the follower flaps (4b), said follower flaps (4b) having a box structure and having lateral openings for delivering cooling air towards the inner face of said driven flaps (4a), in such a way as to limit the heating up of these flaps when the turbojet is in operation.
    Type: Application
    Filed: August 11, 2004
    Publication date: March 24, 2005
    Applicant: SNECMA MOTEURS
    Inventors: Jackie Prouteau, Raphael Curtelin, Guy Lapergue, Didier Feder