Patents by Inventor Rémi Philippe Guy ONFRAY

Rémi Philippe Guy ONFRAY 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: 10934884
    Abstract: An assembly (50) for a turbine engine includes an annular row of stator blades with a longitudinal axis (B) having variable pitch blades each comprising a radial vane (6), at least one of its ends of which is connected to a radially extending pivot (14) and being engaged in rotation around its axis (A) in a ring (16), characterised in that a tubular component (26) is mounted coaxially around the pivot (14), wherein said tubular component (26) comprises a first annular zone (26a) mounted tightly on the pivot (14) and a second annular zone (26b) comprising an annular bulge (28) extending substantially radially outwards in relation to the axis (A) of the pivot (14), wherein the annular bulge (28) and the pivot (14) define an annular space (30).
    Type: Grant
    Filed: March 29, 2019
    Date of Patent: March 2, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Rémi Philippe Guy Onfray, Benoit André Pierre Frossard, Clément Miraton
  • Patent number: 10584720
    Abstract: A blade portion of a vane is assembled to a platform portion by insertion into a cavity in the latter, in a lateral direction from an opening in the cavity, where the cavity possesses a back wall over at least a portion of its surface area. The bonding surface area between the portions of the vane is increased. The back wall of the cavity includes an inclined portion against which the portion of the blade makes contact at the end of its insertion movement, ensuring surface contact which is favorable to achieving an increased bonding area.
    Type: Grant
    Filed: October 10, 2017
    Date of Patent: March 10, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Remi Philippe Guy Onfray, Baptiste Rene Roger Batonnet
  • Patent number: 10471556
    Abstract: The invention proposes a method for producing a protective reinforcement for the leading edge (BA) or trailing edge of a blade (P), the leading edge (BA) or trailing edge being curved, the method comprising steps of flattening (102) a hollow tube (1) so as to form at least one fold line (6) extending along the tube (1), opening (104) the flattened tube (1) by cutting the tube (1) along a cutting line (8) opposite the fold line (6) with respect to the tube (1), so as to form two flanks (16, 18) linked at the fold line (6) and intended to be mounted on the pressure side and the suction side of the blade (P), the method being characterised by a preliminary step (100) of bending the hollow tube (1) carried out before the flattening (102) and adapted such that the fold line (6) after flattening (102) is curved and substantially matches the curved leading edge (BA) of the blade (P).
    Type: Grant
    Filed: September 8, 2016
    Date of Patent: November 12, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Remi Philippe Guy Onfray, Maxime Briend, Didier Pelletier
  • Publication number: 20190301299
    Abstract: The invention relates to an assembly (50) for a turbine engine comprising an annular row of stator blades with a longitudinal axis (B) having variable pitch blades each comprising a radial vane (6), at least one of its ends of which is connected to a radially extending pivot (14) and being engaged in rotation around its axis (A) in a ring (16), characterised in that a tubular component (26) is mounted coaxially around the pivot (14), wherein said tubular component (26) comprises a first annular zone (26a) mounted tightly on the pivot (14) and a second annular zone (26b) comprising an annular bulge (28) extending substantially radially outwards in relation to the axis (A) of the pivot (14), wherein the annular bulge (28) and the pivot (14) define an annular space (30).
    Type: Application
    Filed: March 29, 2019
    Publication date: October 3, 2019
    Inventors: Rémi Philippe Guy ONFRAY, Benoit André Pierre FROSSARD, Clément MIRATON
  • Publication number: 20180257185
    Abstract: The invention proposes a method for producing a protective reinforcement for the leading edge (BA) or trailing edge of a blade (P), the leading edge (BA) or trailing edge being curved, the method comprising steps of flattening (102) a hollow tube (1) so as to form at least one fold line (6) extending along the tube (1), opening (104) the flattened tube (1) by cutting the tube (1) along a cutting line (8) opposite the fold line (6) with respect to the tube (1), so as to form two flanks (16, 18) linked at the fold line (6) and intended to be mounted on the pressure side and the suction side of the blade (P), the method being characterised by a preliminary step (100) of bending the hollow tube (1) carried out before the flattening (102) and adapted such that the fold line (6) after flattening (102) is curved and substantially matches the curved leading edge (BA) of the blade (P).
    Type: Application
    Filed: September 10, 2015
    Publication date: September 13, 2018
    Inventors: Remi Philippe Guy ONFRAY, Maxime BRIEND, Didier PELLETIER
  • Publication number: 20180100516
    Abstract: A blade portion of a vane is assembled to a platform portion by insertion into a cavity in the latter, in a lateral direction from an opening in the cavity, where the cavity possesses a back wall over at least a portion of its surface area. The bonding surface area between the portions of the vane is increased. The back wall of the cavity includes an inclined portion against which the portion of the blade makes contact at the end of its insertion movement, ensuring surface contact which is favorable to achieving an increased bonding area.
    Type: Application
    Filed: October 10, 2017
    Publication date: April 12, 2018
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Remi Philippe Guy ONFRAY, Baptiste Rene Roger Batonnet