Patents by Inventor Julien Guillemaut

Julien Guillemaut 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: 10336458
    Abstract: In order to reduce engine deformation, the subject matter disclosed herein provides an assembly for an aircraft, comprising an aircraft rear section, an engine, a nacelle, and a mounting strut for mounting the engine on the rear section, the assembly also comprising mounting for mounting the engine on a rigid structure of the strut, the mounting comprising two engine mounts designed to react the axial thrust forces generated by the engine. According to the subject matter disclosed herein, the rigid structure of the strut comprises a first portion partially enveloping the engine, this first portion comprising an external skin forming part of an external aerodynamic surface of the nacelle, and the two engine mounts are arranged diametrically opposite each other at the rear of the rigid structure, being attached to the first portion.
    Type: Grant
    Filed: December 18, 2014
    Date of Patent: July 2, 2019
    Assignee: AIRBUS OPERATIONS (S.A.S.)
    Inventors: Julien Guillemaut, Sébastien Alby, Jérôme Colmagro, Pascal Pome, Jonathan Blanc, Thomas Robiglio, Tobias Sjostrom
  • Publication number: 20180327104
    Abstract: An aircraft propulsion assembly including a fan. It include a first engine and a second engine which are not coaxial and a mechanical energy transmission device configured to enable the fan to be conjointly rotated by the first engine and the second engine. This allows an aircraft propulsion assembly to be produced of which the fan may be positioned so as to ingest the boundary layer formed at the surface of a member of the aircraft equipped with the propulsion assembly, while allowing operating modes in the case of certain failures, and certification for commercial use of an aircraft equipped with such a propulsion assembly, to which the invention also relates.
    Type: Application
    Filed: March 13, 2018
    Publication date: November 15, 2018
    Inventors: Antoine Abele, Jean-Michel Rogero, Julien Guillemaut, Mathieu Belleville
  • Patent number: 10124876
    Abstract: An aircraft fuselage frame including a central element adapted to be located within the perimeter of the fuselage, and two lateral extensions projecting outside the perimeter of the fuselage from both sides of the central element that are a portion of a longitudinal structure of a lifting surface. The central element and the two lateral extensions are configured as an integrated piece.
    Type: Grant
    Filed: November 25, 2015
    Date of Patent: November 13, 2018
    Assignees: Airbus Operations S.L., Airbus Operations (SAS)
    Inventors: Esteban Martino Gonzalez, Diego Folch Cortes, Pablo Goya Abaurrea, Angel Pascual Fuertes, Sandra Linares Mendoza, Julien Guillemaut, Eric Bouchet, Jerome Colmagro, Jonathan Blanc
  • Patent number: 9902501
    Abstract: A propeller for a turbomachine intended to be driven in rotation about a propeller rotation axis and including variable pitch blades. The propeller further includes a structure for radial retention of the blades in the event of them breaking. The retaining structure extends around the propeller rotation axis and has the aerodynamic part of each blade of the propeller pass through it. Moreover, each aerodynamic part is equipped with an abutment configured to be retained radially by the retaining structure in the event of a blade fracture causing a fracture in the aerodynamic part radially inside the abutment.
    Type: Grant
    Filed: December 21, 2015
    Date of Patent: February 27, 2018
    Assignee: Airbus Operations (SAS)
    Inventors: Julien Guillemaut, Guillaume Gallant
  • Patent number: 9738373
    Abstract: The invention relates to a fish joint device intended to attach securely first and second structural elements of an aircraft to one another, having two fishplates positioned either side of the structural elements, and attached to them by a set of fishplate through fastenings. According to the invention, the fish joint device includes at least one intermediate fish joint plate which is positioned between one of said fishplates and said structural elements which said intermediate plate partly covers, and which is attached to these elements by a set of intermediate plate through fastenings which includes the set of fishplate through fastenings.
    Type: Grant
    Filed: January 17, 2012
    Date of Patent: August 22, 2017
    Assignee: Airbus Operations (S.A.S.)
    Inventors: Julien Guillemaut, Guillaume Gallant
  • Publication number: 20170167437
    Abstract: A jet engine comprises at least three zones including an air intake zone and an exhaust zone. The axis of the air intake zone is not coincident with the axis of the exhaust zone of the engine, the engine as a result, having at least two intersecting axes and being referred to as a multiaxial engine. Therefore, the jet engine has at least two zones with different longitudinal axis orientations: by choosing an axial orientation of the zones of the engine that are more sensitive to a detachment or breakage of elements of the gas generator, it is possible to also choose a direction of the possible paths of these detached elements, to avoid them striking the opposite engine.
    Type: Application
    Filed: December 14, 2016
    Publication date: June 15, 2017
    Inventors: Olivier Cazals, Julien GUILLEMAUT
  • Patent number: 9656742
    Abstract: An air ejection device comprises an aerodynamic profile provided with a slot and an ejection nozzle. The device comprises a flexible tongue fixed flush with the aerodynamic profile in such a way as to obstruct the slot, the tongue being able to lift under the effect of a pressure differential between the air situated in the ejection nozzle and the outside air. The tongue makes it possible for the slot made in the profile to be obstructed during phases of flight during which the ejection of the air is unnecessary, and prevents external air from entering the slot. The flow of air over the aerodynamic profile is unaffected, and there is no increase in drag. Because the tongue lifts as a result of a pressure differential, it does not require any control mechanism to lift it.
    Type: Grant
    Filed: December 5, 2014
    Date of Patent: May 23, 2017
    Assignee: AIRBUS OPERATIONS SAS
    Inventors: Julien Guillemaut, Arnaud Hormiere, Jerome Colmagro, Cesar Garnier
  • Patent number: 9656736
    Abstract: In the case of an aircraft aft portion equipped with an engine mounting structure passing across the fuselage, assembly of the aft portion presents problems caused by the moving of the box structure of the mounting structure through lateral openings in the fuselage. In order to overcome these problems, a method of assembling an aircraft aft portion is proposed, in which method the box structure of the engine mounting structure is inserted into the fuselage through a top opening extending from one side of the fuselage to the other across a vertical midplane of the fuselage such that the top opening opens to the top and to the sides of the fuselage.
    Type: Grant
    Filed: April 24, 2015
    Date of Patent: May 23, 2017
    Assignees: Airbus Operations (S.A.S.), Airbus Operations SL
    Inventors: Julien Guillemaut, Esteban Martino Gonzalez, Diego Folch Cortes, Jerome Colmagro, Jonathan Blanc
  • Patent number: 9638241
    Abstract: The link for an aircraft comprises at least two portions respectively made of metal and of composite material together forming a common section of a middle segment of the link in a plane perpendicular to a longitudinal direction of the link.
    Type: Grant
    Filed: July 18, 2011
    Date of Patent: May 2, 2017
    Assignee: Airbus Operations (S.A.S.)
    Inventors: Guillaume Gallant, Julien Guillemaut
  • Publication number: 20160311515
    Abstract: In the case of an aircraft aft portion equipped with an engine mounting structure passing across the fuselage, assembly of the aft portion presents problems caused by the moving of the box structure of the mounting structure through lateral openings in the fuselage. In order to overcome these problems, a method of assembling an aircraft aft portion is proposed, in which method the box structure of the engine mounting structure is inserted into the fuselage through a top opening extending from one side of the fuselage to the other across a vertical midplane of the fuselage such that the top opening opens to the top and to the sides of the fuselage.
    Type: Application
    Filed: April 24, 2015
    Publication date: October 27, 2016
    Inventors: Julien GUILLEMAUT, Esteban MARTINO GONZALEZ, Diego FOLCH CORTES, Jerome COLMAGRO, Jonathan BLANC
  • Publication number: 20160229513
    Abstract: An aircraft tail cone comprising a fuselage in which avionic equipment is housed. The tail cone comprises two lateral hatches formed in the fuselage, at least one hatch being formed on each of the two opposite sides of the fuselage. Each hatch is mounted removably with respect to the fuselage so as to take up a closed first position in which the hatch closes a lateral opening in the fuselage, and an open second position in which the open hatch allows access to the inside of the tail cone through the corresponding opening The avionic equipment that requires regular inspection and/or maintenance operations is housed in a part of the tail cone which is accessible through the two lateral openings in the fuselage to a person who remains on the outside of the fuselage.
    Type: Application
    Filed: February 8, 2016
    Publication date: August 11, 2016
    Inventors: Henning Scheel, Eric Bouchet, Julien Guillemaut, Esteban Martino-Gonzalez
  • Publication number: 20160176532
    Abstract: A propeller for a turbomachine intended to be driven in rotation about a propeller rotation axis and including variable pitch blades. The propeller further includes a structure for radial retention of the blades in the event of them breaking. The retaining structure extends around the propeller rotation axis and has the aerodynamic part of each blade of the propeller pass through it. Moreover, each aerodynamic part is equipped with an abutment configured to be retained radially by the retaining structure in the event of a blade fracture causing a fracture in the aerodynamic part radially inside the abutment.
    Type: Application
    Filed: December 21, 2015
    Publication date: June 23, 2016
    Inventors: Julien Guillemaut, Guillaume Gallant
  • Publication number: 20160176533
    Abstract: An auxiliary power device may be exteriorly removably connected to an aircraft in order to allow the increase of the performance data of the aircraft, namely at take-off and landing. The auxiliary power device includes a propeller (or fan) connected to an electric engine fed by an electric power supply.
    Type: Application
    Filed: December 18, 2015
    Publication date: June 23, 2016
    Applicant: Airbus Operations SAS
    Inventors: Olivier Cazals, Thierry Druot, Julien Guillemaut
  • Patent number: 9359085
    Abstract: Internal shield in the rear fuselage of an aircraft having a propulsion system formed by two engines mounted on each side of it; the rear fuselage having at least a vertical symmetry plane; the rear fuselage being made of a composite material; the internal shield being located in said vertical symmetry plane and extended in an area that covers the possible trajectories of a set of pre-defined fragments detached from one of said engines in a failure event that would impact on critical elements of the opposite engine; the internal shield having a flat shape and an energy absorption capability that allows stopping said fragments. The invention also refers to a method for determining the area of an internal shield and to an aircraft having said internal shield.
    Type: Grant
    Filed: December 21, 2012
    Date of Patent: June 7, 2016
    Inventors: Diego Folch Cortés, Eduardo Vinué Santolalla, Esteban Martino González, Julien Guillemaut, Pablo Goya Abaurrea
  • Publication number: 20160152315
    Abstract: An aircraft fuselage frame including a central element adapted to be located within the perimeter of the fuselage, and two lateral extensions projecting outside the perimeter of the fuselage from both sides of the central element that are a portion of a longitudinal structure of a lifting surface. The central element and the two lateral extensions are configured as an integrated piece.
    Type: Application
    Filed: November 25, 2015
    Publication date: June 2, 2016
    Inventors: Esteban MARTINO GONZALEZ, Diego FOLCH CORTES, Pablo GOYA ABAURREA, Angel PASCUAL FUERTES, Sandra LINARES MENDOZA, Julien GUILLEMAUT, Eric BOUCHET, Jerome COLMAGRO, Jonathan BLANC
  • Publication number: 20150259074
    Abstract: In order to reduce engine deformation, the subject matter disclosed herein provides an assembly for an aircraft, comprising an aircraft rear section, an engine, a nacelle, and a mounting strut for mounting the engine on the rear section, the assembly also comprising mounting for mounting the engine on a rigid structure of the strut, the mounting comprising two engine mounts designed to react the axial thrust forces generated by the engine. According to the subject matter disclosed herein, the rigid structure of the strut comprises a first portion partially enveloping the engine, this first portion comprising an external skin forming part of an external aerodynamic surface of the nacelle, and the two engine mounts are arranged diametrically opposite each other at the rear of the rigid structure, being attached to the first portion.
    Type: Application
    Filed: December 18, 2014
    Publication date: September 17, 2015
    Inventors: Julien Guillemaut, Sébastien Alby, Jérôme Colmagro, Pascal Pome, Jonathan Blanc, Thomas Robiglio, Tobias Sjostrom
  • Patent number: 9114582
    Abstract: A method for producing a central wing box having an upper panel, a lower panel, a front spar and a rear spar, the upper edges of said spars approximately parallel to an axis Y being connected by the upper panel, and the lower edges of said spars approximately parallel to the axis Y being connected by the lower panel. The method includes producing at least one panel and at least one spar from composite material in one piece.
    Type: Grant
    Filed: June 24, 2011
    Date of Patent: August 25, 2015
    Assignee: Airbus Operations SAS
    Inventors: Philippe Blot, Jerome Colmargo, Denis Soula, Julien Guillemaut, Thomas Le Hetet, Dominique Guittard
  • Publication number: 20150158577
    Abstract: An air ejection device comprises an aerodynamic profile provided with a slot and an ejection nozzle. The device comprises a flexible tongue fixed flush with the aerodynamic profile in such a way as to obstruct the slot, the tongue being able to lift under the effect of a pressure differential between the air situated in the ejection nozzle and the outside air. The tongue makes it possible for the slot made in the profile to be obstructed during phases of flight during which the ejection of the air is unnecessary, and prevents external air from entering the slot. The flow of air over the aerodynamic profile is unaffected, and there is no increase in drag. Because the tongue lifts as a result of a pressure differential, it does not require any control mechanism to lift it.
    Type: Application
    Filed: December 5, 2014
    Publication date: June 11, 2015
    Inventors: Julien GUILLEMAUT, Arnaud HORMIERE, Jerome COLMAGRO, Cesar GARNIER
  • Publication number: 20140263836
    Abstract: The invention relates to a fish joint device intended to attach securely first and second structural elements of an aircraft to one another, having two fishplates positioned either side of the structural elements, and attached to them by a set of fishplate through fastenings. According to the invention, the fish joint device includes at least one intermediate fish joint plate which is positioned between one of said fishplates and said structural elements which said intermediate plate partly covers, and which is attached to these elements by a set of intermediate plate through fastenings which includes the set of fishplate through fastenings.
    Type: Application
    Filed: January 17, 2012
    Publication date: September 18, 2014
    Applicant: Airbus Operations (S.A.S)
    Inventors: Julien Guillemaut, Guillaume Gallant
  • Patent number: 8746621
    Abstract: The stiffening frames (14) of an aircraft fuselage (2) remain continuous while passing through an upper panel (5) of the wing box and extend over the ribs (3) situated in that box. The overall mechanical strength of the assembly is improved, despite the notches it is necessary to make in the panel (5).
    Type: Grant
    Filed: January 11, 2012
    Date of Patent: June 10, 2014
    Assignee: AIRBUS Operations S.A.S.
    Inventors: Jean Pierre Cabanac, Jerome Colmagro, Jean Marc Durand, Ludovic Fournie, Julien Guillemaut, Francois Loyant