Patents by Inventor Cyril Bonnaud
Cyril Bonnaud 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).
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Patent number: 9708071Abstract: The invention proposes to protect a rear part of a floor of an aft fairing of a pylon of an aircraft bypass turbojet engine using a film of cool air formed of part of a bypass flow of the jet engine which is guided under the floor by two lateral wall portions of this fairing which have been profiled for this purpose. To do that, these two lateral wall portions delimit respective air passage spaces formed between a forward part of the floor and a jetpipe of the turbojet engine and which open laterally and towards the rear.Type: GrantFiled: December 20, 2013Date of Patent: July 18, 2017Assignee: AIRBUS OPERATIONS (S.A.S.)Inventors: Thierry Surply, Cyril Bonnaud, David Grossein, Stéve Bedoin, Amadou AndréSylla, Guillaume Drochon, Marjorie Clottes
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Patent number: 8936213Abstract: The invention relates to a method for manufacturing an engine pylon (7) to be mounted between an engine (1) and an aircraft wing (6), said method comprising: mounting a pylon box (8) around a main structure (9), the box having a substantially oblong shape along which an air boundary layer (C) is formed while in flight; mounting at least one vortex generator (2) onto the pylon box such that a thickness (e) of the boundary layer is changed; and previously determining the shape of the pylon on the basis of the changed thickness of the boundary layer and the position of the vortex generators.Type: GrantFiled: October 27, 2010Date of Patent: January 20, 2015Assignee: Airbus Operations S.A.S.Inventors: Steve Bedoin, Cyril Bonnaud
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Publication number: 20140191080Abstract: The invention proposes to protect a rear part of a floor of an aft fairing of a pylon of an aircraft bypass turbojet engine using a film of cool air formed of part of a bypass flow of the jet engine which is guided under the floor by two lateral wall portions of this fairing which have been profiled for this purpose. To do that, these two lateral wall portions delimit respective air passage spaces formed between a forward part of the floor and a jetpipe of the turbojet engine and which open laterally and towards the rear.Type: ApplicationFiled: December 20, 2013Publication date: July 10, 2014Inventors: Thierry Surply, Cyril BONNAUD, David Grossein, Stève BEDOIN, Amadou André Sylla, Guillaume Drochon, Marjorie Clottes
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Patent number: 8336813Abstract: According to the invention, the engine pylon for the suspension of a turbo engine under an aircraft wing is such that the trailing edge of the rear lower part of the engine pylon is shifted toward the root of the wing.Type: GrantFiled: August 31, 2009Date of Patent: December 25, 2012Assignees: Airbus Operations SAS, Airbus UK LimitedInventors: Cyril Bonnaud, Thierry Fol, Anne Dumoulin, Tom Gibson, Neil Lyons
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Publication number: 20120273610Abstract: The invention relates to a method for manufacturing an engine pylon (7) to be mounted between an engine (1) and an aircraft wing (6), said method comprising: mounting a pylon box (8) around a main structure (9), the box having a substantially oblong shape along which an air boundary layer (C) is formed while in flight; mounting at least one vortex generator (2) onto the pylon box such that a thickness (e) of the boundary layer is changed; and previously determining the shape of the pylon on the basis of the changed thickness of the boundary layer and the position of the vortex generators.Type: ApplicationFiled: October 27, 2010Publication date: November 1, 2012Applicant: AIRBUS OPERATIONS (S.A.S.)Inventors: Steve Bedoin, Cyril Bonnaud
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Airplane engine pylon comprising at least one protruding element to generate a vortex of the airflow
Patent number: 8186619Abstract: A wing arrangement of an aircraft has a wing and at least one pylon for suspending an engine below the wing. The wing has a leading edge with a high-lift device, which is able to move between a deployed position in which the high-lift device projects forward of the leading edge, and which is interrupted in a forward intermediate region of the wing located at the leading edge, the pylon having a forward edge extending forward of the leading edge of the wing between a forward upper portion connected to the wing in the forward intermediate region and a forward lower portion connected to a nacelle of the engine. An element of narrow elongate shape protrudes longitudinally from the forward edge and, during flight at a high angle of attack of the aircraft, generates a vortex of aerodynamic flow that is propagated toward the forward intermediate region above the wing.Type: GrantFiled: March 13, 2009Date of Patent: May 29, 2012Assignee: Airbus Operations SASInventors: Cyril Bonnaud, Stephanie Dantin, Marjorie Defos, Thierry Fol -
Patent number: 8172178Abstract: An aircraft with an outer surface from which flows an aerodynamic stream of cold air and includes at least one hot gas outlet, characterized in that it includes at least one device (16) for generating aerodynamic disturbances so as to mix hot gas and cold air, whereby the at least one device is connected to an outer surface (10) for protection against the heat and/or close to a hot gas outlet (12).Type: GrantFiled: August 15, 2008Date of Patent: May 8, 2012Assignee: Airbus Operations SASInventors: Cyril Bonnaud, Thomas Stevens, Frédéric Roche, Stéphane Dostes
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Patent number: 8146868Abstract: Disclosed is a mast for the suspension of a bypass turbine engine beneath a wing of an aircraft in which the wing has at least one flap. The mast includes a rear fairing that protrudes rearward of a trailing edge of the wing and is mounted so as to tilt in a deployed downward position as the flap is deployed in a downward position. The rear fairing is positioned to enter a cold flow of the turbine engine, when deployed in the downward position. The rear fairing further supports at least one aerodynamic element that generates vortices that reduce, if not eliminates, vibrations to which the rear fairing is subjected.Type: GrantFiled: April 20, 2009Date of Patent: April 3, 2012Assignee: Airbus Operations SASInventors: Cyril Bonnaud, Florent Laporte, Stéve Bedoin
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Patent number: 8100358Abstract: The present invention provides a method of reducing the compressibility drag of wing, and it also provides a container implementing the method. The container (10, 10?, 10?) is provided successively with a front portion (11) in the vicinity of its leading edge (14), then with an intermediate portion (12), and then with a rear portion (13) in the vicinity of its trailing edge (15), said rear portion (13) tapering progressively in a direction going from the leading edge (14) of the container towards its trailing edge (15). Furthermore, said rear portion (13) is extended by connection means (17) enabling the container (10, 10?, 10?) to be connected under the wing (1) in such a manner that said tapering rear portion (13) is partially upstream from the leading edge (2) of the wing (1).Type: GrantFiled: October 21, 2008Date of Patent: January 24, 2012Assignee: Airbus FranceInventors: Thierry Fol, Cyril Bonnaud
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Patent number: 7988092Abstract: A vortex-generating device is presented to reduce a thermal exposure of an aircraft to hot exhaust gases discharged from an aircraft engine. The engine also discharges cold air from a fan of the engine. The aircraft engine may be coupled to the aircraft via a support mast located on a main wing. A portion of the support mast of an aircraft engine is located near a hot gas flow being discharged from the engine. The vortex-generating device is positioned on a surface of the support mast. The device generates a vortex which crosses the hot gases and prevents the hot gas flow from reaching a heat sensitive portion of the support mast. This device is adaptable to the operating conditions of an already-built aircraft without any notable increased weight.Type: GrantFiled: July 10, 2007Date of Patent: August 2, 2011Assignee: Airbus Operations SASInventors: Cyril Bonnaud, Arnaud Hormiere
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Publication number: 20100051744Abstract: According to the invention, the engine pylon for the suspension of a turbo engine under an aircraft wing is such that the trailing edge of the rear lower part of the engine pylon is shifted toward the root of the wing.Type: ApplicationFiled: August 31, 2009Publication date: March 4, 2010Applicants: AIRBUS OPERATIONS, AIRBUS UK LimitedInventors: Cyril BONNAUD, Thierry Fol, Anne Dumoulin, Tom Gibson, Neil Lyons
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Publication number: 20090261198Abstract: Suspension mast for a turbine engine. According to the inventions the tilting rear fairing (6) of said mast (4) supports at least one aerodynamic element (14) that generates vortices.Type: ApplicationFiled: April 20, 2009Publication date: October 22, 2009Applicant: AIRBUS FranceInventors: Cyril BONNAUD, Florent LAPORTE, Steve BEDOIN
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AIRPLANE ENGINE PYLON COMPRISING AT LEAST ONE PROTRUDING ELEMENT TO GENERATE A VORTEX OF THE AIRFLOW
Publication number: 20090230251Abstract: A wing arrangement of an aircraft has a wing and at least one pylon for suspending an engine below the wing. The wing has a leading edge with a high-lift device, which is able to move between a deployed position in which the high-lift device projects forward of the leading edge, and which is interrupted in a forward intermediate region of the wing located at the leading edge, the pylon having a forward edge extending forward of the leading edge of the wing between a forward upper portion connected to the wing in the forward intermediate region and a forward lower portion connected to a nacelle of the engine. An element of narrow elongate shape protrudes longitudinally from the forward edge and, during flight at a high angle of attack of the aircraft, generates a vortex of aerodynamic flow that is propagated toward the forward intermediate region above the wing.Type: ApplicationFiled: March 13, 2009Publication date: September 17, 2009Applicant: AIRBUS FRANCEInventors: Cyril Bonnaud, Stephanie Dantin, Marjorie Defos, Thierry Fol -
Publication number: 20090050742Abstract: An aircraft with an outer surface from which flows an aerodynamic stream of cold air and includes at least one hot gas outlet, characterized in that it includes at least one device (16) for generating aerodynamic disturbances so as to mix hot gas and cold air, whereby the at least one device is connected to an outer surface (10) for protection against the heat and/or close to a hot gas outlet (12).Type: ApplicationFiled: August 15, 2008Publication date: February 26, 2009Applicant: AIRBUS FRANCEInventors: Cyril Bonnaud, Thomas Stevens, Frederic Roche, Stephane Dostes
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Publication number: 20080067292Abstract: In order to reduce the surface of a support mast (2) of an aircraft engine in contact with the hot exhaust gases (18) of said engine, a vortex-generating device (24) is positioned on the surface of the mast (2), near the hot region (22). Thus, the vortex generated in the flow of cold gases (16) crosses the hot air and modifies its path, thus preventing it from reaching zones (22) of the mast that are not predefined. This system makes it possible to adapt to the operating conditions of an already-built aircraft, without any notable increased weight.Type: ApplicationFiled: July 10, 2007Publication date: March 20, 2008Applicant: Airbus FranceInventors: Cyril Bonnaud, Arnaud Hormiere
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Patent number: 7121512Abstract: A drain, for example for an aircraft engine support strut, arranged on the trailing edge of the rear secondary structure of the strut. The drain includes a conduit with a substantially horizontal axis and a substantially rectangular cross-section, taken in a plane parallel to the trailing edge, the conduit closed at an outer extremity by a terminal portion with a substantially ogival cross-section taken in the axis of the conduit and including at least one opening for drainage with an elongated shape on at least one of the opposing lateral walls.Type: GrantFiled: December 17, 2004Date of Patent: October 17, 2006Assignee: Airbus FranceInventor: Cyril Bonnaud
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Publication number: 20060027707Abstract: A drain, for example for an aircraft engine support strut, arranged on the trailing edge of the rear secondary structure of the strut. The drain includes a conduit with a substantially horizontal axis and a substantially rectangular cross-section, taken in a plane parallel to the trailing edge, the conduit closed at an outer extremity by a terminal portion with a substantially ogival cross-section taken in the axis of the conduit and including at least one opening for drainage with an elongated shape on at least one of the opposing lateral walls.Type: ApplicationFiled: December 17, 2004Publication date: February 9, 2006Inventor: Cyril Bonnaud