Patents by Inventor Frederic Chelin

Frederic Chelin 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: 10377503
    Abstract: An engine assembly comprising an engine and a pod surrounding the engine that is equipped, upstream according to the direction of entry of air into the engine, with a fan provided with blades, the pod having an upstream air intake. The engine assembly also comprises a display unit including at least one light ring arranged in the air intake upstream of the fan, the light ring including at least one row of light-emitting diodes and being configured to emit at least one light beam and to project it on the blades of the fan.
    Type: Grant
    Filed: June 2, 2016
    Date of Patent: August 13, 2019
    Assignee: Airbus Operations SAS
    Inventors: Alain Porte, Frederic Chelin, Wolfgang Rehm, Nathalie Papin, Irene Moreno Gonzalez
  • Patent number: 9719422
    Abstract: A process for the production of an acoustic treatment panel that includes an acoustically resistive layer (24), at least one alveolar structure (26), and a reflective layer (28), as well as at least one channel that is bordered at least in part by a wall (32) that is secant with at least one wall of a cell of the alveolar structure (26), includes elevating the temperature of the wall (32) and the ends of the cells of the alveolar structure (26) and injecting a pressurized gas into the channel (30) so as to expand the wall (32) of the channel so as to flatten it against the ends of the cells of the alveolar structure (26) in such a way as to produce a weld by continuous diffusion between the ends of the walls of the cells of the alveolar structure (26) and the wall (32) of the channel (30).
    Type: Grant
    Filed: June 19, 2012
    Date of Patent: August 1, 2017
    Assignee: AIRBUS OPERATIONS SAS
    Inventors: Alain Porte, Frederic Chelin
  • Publication number: 20160355276
    Abstract: An engine assembly comprising an engine and a pod surrounding the engine that is equipped, upstream according to the direction of entry of air into the engine, with a fan provided with blades, the pod having an upstream air intake. The engine assembly also comprises a display unit including at least one light ring arranged in the air intake upstream of the fan, the light ring including at least one row of light-emitting diodes and being configured to emit at least one light beam and to project it on the blades of the fan.
    Type: Application
    Filed: June 2, 2016
    Publication date: December 8, 2016
    Inventors: Alain Porte, Frederic Chelin, Wolfgang Rehm, Nathalie Papin, Irene Moreno Gonzalez
  • Patent number: 9284060
    Abstract: An aircraft nacelle includes a lip whose surface contacts with the aerodynamic streams extends inside the nacelle by an inside wall that delimits a layer that empties at a power plant and outside of the nacelle by an outside wall, a first front frame connects the inside and outside walls, delimiting an annular pipe with the lip, and a rear frame connects the inside and outside walls at a junction zone between the inside pipe and power plant pipe, for a given cross-section of the nacelle along a plane that contains the longitudinal axis of the nacelle, a point A at the intersection between the rear frame and the inside wall, and a point B at the intersection between the rear frame and the outside wall, with B being offset toward the rear of the nacelle relative to A over more than 50% of the rear frame's periphery.
    Type: Grant
    Filed: October 11, 2011
    Date of Patent: March 15, 2016
    Assignee: AIRBUS OPERATIONS (S.A.S)
    Inventors: Alain Porte, Jacques Lalane, Frederic Chelin
  • Patent number: 9261021
    Abstract: An internal wall of an air intake and a housing of a fan form a single tubular piece made from a fiber/resin composite material. A rear end has the single tubular component connected by a flange and bolts to an external cowl of the fan duct, such that the rear end of the tubular component is uniform and the flange is attached and fixed to the rear end.
    Type: Grant
    Filed: July 4, 2007
    Date of Patent: February 16, 2016
    Assignee: AIRBUS OPERATIONS (SAS)
    Inventors: Alain Porte, Fabrice Gantie, Frederic Chelin, Patrick Oberle
  • Patent number: 9003810
    Abstract: An aircraft nacelle includes at its outside wall a cowl moveable relative to the nacelle so as to block or unblock an opening. The cowl includes an articulation and locking/unlocking elements distant from the upstream edge of the cowl that include elements for limiting the appearance of scooping phenomena. The limiting elements include at least one lock integral with the rest of the nacelle or respectively the cowl that can occupy a locked state in which part of the lock interferes with the cowl or respectively the rest of the nacelle and prevents a deformation that includes a radial component of the cowl, and another free state in which the part no longer interferes with the cowl or respectively the rest of the nacelle and allows the opening movement of the cowl, with the switch from one state to the next being generated by a gas pressure variation.
    Type: Grant
    Filed: October 19, 2011
    Date of Patent: April 14, 2015
    Assignee: Airbus Operations (S.A.S.)
    Inventors: Alain Porte, Frederic Chelin, Thierry Surply
  • Patent number: 8991054
    Abstract: A process for the production of an acoustic treatment panel that can be connected at a surface of an aircraft, in particular at a leading edge such as an air intake of an aircraft nacelle, whereby the panel includes an acoustically resistive layer (24), at least one alveolar structure (26), and a reflective layer (28), and channels (30) placed between the alveolar structure and the acoustically resistive layer, each channel being bordered by a wall (32), the process including deforming a layer so as to produce furrows at one of its surfaces, flattening and making integral the deformed layer (34) with the acoustically resistive layer so as to border the channels, and removing material in such a way as to eliminate at least a portion of the thickness of the deformed layer (34) in which the furrows are formed between the channels, prior to the assembly of the alveolar structure.
    Type: Grant
    Filed: June 19, 2012
    Date of Patent: March 31, 2015
    Assignee: Airbus Operations SAS
    Inventors: Alain Porte, Frederic Chelin, Gregory Albet
  • Patent number: 8851416
    Abstract: An aircraft nacelle that makes it possible to channel a stream of air in a longitudinal direction and that includes at least two panels (50, 50?) placed end to end in the longitudinal direction, each including a so-called aerodynamic surface (52, 52?) that is in contact with the air stream and an edge (54, 54?) that is in contact with the edge of the other panel, characterized in that at least one of the panels includes—at its edge (54, 54?)—at least one partition (58) that projects relative to the edge that extends in the direction of the edge of the other panel, in a manner that is secant to the aerodynamic surface and in a plane that contains the longitudinal direction, so as to limit the circulation of air between the edges of the panels.
    Type: Grant
    Filed: October 11, 2011
    Date of Patent: October 7, 2014
    Assignee: Airbus Operations (S.A.S.)
    Inventors: Alain Porte, Jacques Lalane, Frederic Chelin, Thierry Surply
  • Patent number: 8794572
    Abstract: An air intake of an aircraft nacelle includes: on the one hand, a lip (42) that is defined by a wall (52) whose surface that is in contact with the aerodynamic flows is extended on the inside of the nacelle by an inside wall (44) that borders a pipe that empties out at a power plant and on the outside of the nacelle by an outside wall (46), and, on the other hand, a surface-type Joule-effect defrosting system (58); at least a first alveolar structure (60.1) that is made of a material that conducts the heat and that is flattened against the inside surface of the wall (52) and inserted between the wall (52) and the defrosting system (58), and at least one second alveolar structure (60.2) that is made of composite material that is adjacent to the first structure (60.1).
    Type: Grant
    Filed: June 14, 2012
    Date of Patent: August 5, 2014
    Assignee: Airbus Operations S.A.S.
    Inventors: Alain Porte, Frederic Chelin
  • Patent number: 8628635
    Abstract: A process for producing a panel for acoustic treatment including a resistive porous layer, an alveolar structure, a reflective layer with openings, and a drainage plate having a furrow for delimiting at least one evacuation pipe when the drainage plate is flattened against the free surface of the reflective layer, includes: shaping the reflective layer according to its final geometry, affixing a demolding film on at least one portion of the free surface of the reflective layer, positioning on the demolding film a core whose cross-section is adapted to that of the evacuation pipe so that the core covers the openings of the reflective layer, molding the drainage plate on the demolding film and the core, demolding the drainage plate and removing the core and the demolding film, and making the drainage plate integral with the free surface of the reflective layer.
    Type: Grant
    Filed: January 29, 2010
    Date of Patent: January 14, 2014
    Assignee: Airbus Operations SAS
    Inventors: Frederic Chelin, Christophe Menier, Jean Yves Thomy, Etienne Bertin, Thierry Surply, Dominique Haro, Fabrice Gantie
  • Publication number: 20120318924
    Abstract: An air intake of an aircraft nacelle includes: on the one hand, a lip (42) that is defined by a wall (52) whose surface that is in contact with the aerodynamic flows is extended on the inside of the nacelle by an inside wall (44) that borders a pipe that empties out at a power plant and on the outside of the nacelle by an outside wall (46), and, on the other hand, a surface-type Joule-effect defrosting system (58); at least a first alveolar structure (60.1) that is made of a material that conducts the heat and that is flattened against the inside surface of the wall (52) and inserted between the wall (52) and the defrosting system (58), and at least one second alveolar structure (60.2) that is made of composite material that is adjacent to the first structure (60.1).
    Type: Application
    Filed: June 14, 2012
    Publication date: December 20, 2012
    Applicant: AIRBUS OPERATIONS SAS
    Inventors: Alain PORTE, Frederic CHELIN
  • Publication number: 20120152443
    Abstract: A process for producing a panel for acoustic treatment including an acoustically resistive porous layer, at least one alveolar structure, a reflective layer with openings, and a drainage plate having at least one furrow for delimiting at least one evacuation pipe when the drainage plate is flattened against the free surface of the reflective layer, includes: shaping, if necessary, the reflective layer according to its final geometry, affixing a demolding film on at least one portion of the free surface of the reflective layer, positioning on the demolding film at least one core whose cross-section is adapted to that of the evacuation pipe so that the at least one core covers the openings of the reflective layer, molding the drainage plate on the demolding film and the at least one core, demolding the drainage plate and removing the at least one core and the demolding film, and making the drainage plate integral with the free surface of the reflective layer.
    Type: Application
    Filed: January 29, 2010
    Publication date: June 21, 2012
    Applicant: AIRBUS OPERATIONS SAS
    Inventors: Frederic Chelin, Christophe Menier, Jean Yves Thomy, Etienne Bertin, Thierry Surply, Dominique Haro, Fabrice Gantie
  • Publication number: 20120090694
    Abstract: An aircraft nacelle includes a lip whose surface contacts with the aerodynamic streams extends inside the nacelle by an inside wall that delimits a layer that empties at a power plant and outside of the nacelle by an outside wall, a first front frame connects the inside and outside walls, delimiting an annular pipe with the lip, and a rear frame connects the inside and outside walls at a junction zone between the inside pipe and power plant pipe, for a given cross-section of the nacelle along a plane that contains the longitudinal axis of the nacelle, a point A at the intersection between the rear frame and the inside wall, and a point B at the intersection between the rear frame and the outside wall, with B being offset toward the rear of the nacelle relative to A over more than 50% of the rear frame's periphery.
    Type: Application
    Filed: October 11, 2011
    Publication date: April 19, 2012
    Applicant: AIRBUS OPERATIONS (S.A.S)
    Inventors: Alain PORTE, Jacques LALANE, Frederic CHELIN
  • Publication number: 20120090695
    Abstract: An aircraft nacelle that makes it possible to channel a stream of air in a longitudinal direction and that includes at least two panels (50, 50?) placed end to end in the longitudinal direction, each including a so-called aerodynamic surface (52, 52?) that is in contact with the air stream and an edge (54, 54?) that is in contact with the edge of the other panel, characterized in that at least one of the panels includes—at its edge (54, 54?)—at least one partition (58) that projects relative to the edge that extends in the direction of the edge of the other panel, in a manner that is secant to the aerodynamic surface and in a plane that contains the longitudinal direction, so as to limit the circulation of air between the edges of the panels.
    Type: Application
    Filed: October 11, 2011
    Publication date: April 19, 2012
    Applicant: AIRBUS OPERATIONS (S.A.S)
    Inventors: Alain PORTE, Jacques LALANE, Frederic CHELIN, Thierry SURPLY
  • Publication number: 20120091285
    Abstract: An aircraft nacelle includes a lip that is extended inside the nacelle by an inside wall that delimits a pipe that empties at a power plant and outside of the nacelle by an outside wall, a first frame called a front frame that connects the inside wall and the outside wall, delimiting an annular pipe with the lip, and a second frame called a rear frame that connects the inside wall and the outside wall close to the power plant, characterized in that it includes at least one junction zone—at at least one cross-section of the nacelle along a plane that contains the longitudinal axis of the nacelle—an element that constitutes at least one part of the outside wall and at least one part of the front frame and that includes an offset whose shapes are suitable for accommodating a panel that forms the lip.
    Type: Application
    Filed: October 11, 2011
    Publication date: April 19, 2012
    Applicant: AIRBUS OPERATIONS (S.A.S)
    Inventors: Alain PORTE, Frederic CHELIN
  • Patent number: 8142144
    Abstract: Disclosed is an aircraft turbine engine. The turbine engine includes an air intake having a tubular internal wall and a fan enclosed by a tubular fan casing, and the rear end of the said air intake internal wall and the front end of the fan casing are joined together by at least one fastener. The air intake internal wall, the fan casing, or both, are comprised of a resin/fiber composite. The rear end of the air intake internal wall and the front end of the fan casing are uniform, and have no projections that join the internal wall and casing together.
    Type: Grant
    Filed: July 4, 2007
    Date of Patent: March 27, 2012
    Assignee: Airbus Operations SAS
    Inventors: Alain Porte, Frederic Chelin, David Lambert
  • Publication number: 20110139927
    Abstract: An acoustic treatment panel includes an acoustically resistive layer that defines a surface of an aircraft that is in contact with an aerodynamic stream, a reflective layer (50) between which are arranged at least one alveolar structure (52) with a number of cells dedicated to the acoustic treatment, and de-icing cavities (58) in which hot air circulates in contact with the acoustically resistive layer to ensure a frost treatment, characterized in that it includes holes for supplying de-icing cavities (58) with hot air and in that the capacity to treat the frost is adjusted along the zones by modifying the open surface ratio that results from the holes.
    Type: Application
    Filed: December 15, 2010
    Publication date: June 16, 2011
    Applicant: AIRBUS OPERATIONS SAS
    Inventors: Alain PORTE, Frederic CHELIN, Stephane DIDA, Arnaud HORMIERE
  • Publication number: 20100327120
    Abstract: An aircraft leading edge is extended by an aerodynamic surface providing an aerodynamic flow and where air discharges are arranged preventing separation of the aerodynamic flow. The air discharges are arranged in at least two rows essentially parallel to the leading edge and in an offset manner for at least two consecutive rows. At least one block is inserted between two walls that form the aerodynamic surface. The block includes, on the one hand, an outside surface extending the aerodynamic surface, a first inclined surface contacting the first wall forming the aerodynamic surface, and a second inclined surface contacting the second wall that forms the aerodynamic surface, and, on the other hand, projecting and/or hollow shapes that are made at the inclined surfaces and that are arranged in an alternating fashion from one surface to the next, allowing air to pass on both sides of the aerodynamic surface.
    Type: Application
    Filed: December 1, 2008
    Publication date: December 30, 2010
    Applicant: AIRBUS OPERATIONS SAS
    Inventors: Frederic Chelin, Thierry Surply, Christophe Bourdeau
  • Publication number: 20090290978
    Abstract: According to the invention, the internal wall (5.1) of the air intake (2) and the housing (12.1) for the fan (3) are pieces of composite fibre/resin material, overlap-jointed at the ends thereof (5.1R) and (12.1A).
    Type: Application
    Filed: July 4, 2007
    Publication date: November 26, 2009
    Inventors: Alain Porte, Frederic Chelin, David Lambert
  • Publication number: 20090277181
    Abstract: A propulsion unit includes at least one exhaust pipe (62, 76) that includes an air discharge that is delimited by a trailing edge (78, 82). The end part of the exhaust pipe (62, 76) includes two scalloped shapes (84) that each correspond to a preferred acoustic radiation direction, separated by advanced parts (86) that can limit the acoustic radiation, whereby the scalloped shapes are offset upward relative to the horizontal median plane.
    Type: Application
    Filed: June 13, 2007
    Publication date: November 12, 2009
    Applicant: AIRBUS FRANCE, SOCIETE PAR ACTIONS SIMPLIFIEE
    Inventors: Yann Druon, Frederic Chelin, Fabrice Gantie