Patents Assigned to CENAERO
  • Propulsion device having unducted counter-rotating and coaxial rotors
    Patent number: 9593582
    Abstract: A propulsion device including an unducted upstream propeller and a counter-rotating and coaxial downstream propeller. At least one blade of the upstream propeller is configured to generate a corotating secondary vortex for acting upstream of the downstream propeller to destabilize a blade tip vortex of the same at least one blade.
    Type: Grant
    Filed: April 13, 2012
    Date of Patent: March 14, 2017
    Assignees: SNECMA, CENAERO
    Inventors: Clement Marcel Maurice Dejeu, Sebastien Pascal, Jerome Talbotec, Michael Leborgne, Ingrid Irene Catherine Lepot
  • Rotor of a turbomachine compressor, with an optimised inner end wall
    Patent number: 9200638
    Abstract: A rotor of a turbomachine compressor, including a bladed rotor disk fitted at its radially external end with a wall forming the inner end of an annual flow channel of a primary gas flow, and formed from multiple angular sectors, each of which is delimited between two blades of the disk which are consecutive in a circumferential direction and includes a bulging portion which is convex in the axial direction and in the circumferential direction, together with, upstream from the bulging portion, a troughed portion which is concave in the axial direction and in the circumferential direction and which has a base which is roughly punctiform.
    Type: Grant
    Filed: October 1, 2010
    Date of Patent: December 1, 2015
    Assignees: SNECMA, CENAERO
    Inventors: Eric Jacques Boston, Alexandre Franck Arnaud Chartoire, Vasiliki Iliopoulou, Ingrid Lepot, Thierry Jean-Jacques Obrecht
  • PROPULSION DEVICE HAVING UNDUCTED COUNTER-ROTATING AND COAXIAL ROTORS
    Publication number: 20140133982
    Abstract: A propulsion device including an unducted upstream propeller and a counter-rotating and coaxial downstream propeller. At least one blade of the upstream propeller is configured to generate a corotating secondary vortex for acting upstream of the downstream propeller to destabilize a blade tip vortex of the same at least one blade.
    Type: Application
    Filed: April 13, 2012
    Publication date: May 15, 2014
    Applicants: CENTRE DE RECHERCHE EN AERONAUTIQUE ASBL-CENAERO, SNECMA
    Inventors: Clement Marcel, Maurice Dejeu, Sebastien Pascal, Jerome Talbotec, Michael Leborgne, Ingrid Irene, Catherine Lepot
  • ROTOR OF A TURBOMACHINE COMPRESSOR, WITH AN OPTIMISED INNER END WALL
    Publication number: 20120201692
    Abstract: A rotor of a turbomachine compressor, including a bladed rotor disk fitted at its radially external end with a wall forming the inner end of an annual flow channel of a primary gas flow, and formed from multiple angular sectors, each of which is delimited between two blades of the disk which are consecutive in a circumferential direction and includes a bulging portion which is convex in the axial direction and in the circumferential direction, together with, upstream from the bulging portion, a troughed portion which is concave in the axial direction and in the circumferential direction and which has a base which is roughly punctiform.
    Type: Application
    Filed: October 1, 2010
    Publication date: August 9, 2012
    Applicants: CENAERO, SNECMA
    Inventors: Eric Jacques Boston, Alexandre Franck Arnaud Chartoire, Vasiliki Iliopoulou, Ingrid Lepot, Thierry Jean-Jacques Obrecht