Patents by Inventor Philippe Gérard Chanez
Philippe Gérard Chanez 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: 11913378Abstract: The invention relates to an assembly for a turbomachine, comprising: —a nacelle comprising an inlet lip which defines an air inlet, and—a device for modifying the geometry of the air inlet, comprising: —a first spout, and—a second spout, the first spout and the second spout being translatably movable in relation the nacelle between: —a first configuration, in which the first spout forms the inlet lip and the second spout extends inside the nacelle, and—a second configuration, in which the first spout extends away from the inlet lip, and the second spout forms the inlet lip so as to define an air flow channel between a downstream surface of the first spout and an upstream surface of the second spout.Type: GrantFiled: October 15, 2020Date of Patent: February 27, 2024Assignees: INSTITUT SUPERIEUR DE L AERONAUTIQUE ET DE L ESPACE, SAFRAN AIRCRAFT ENGINESInventors: Nicolas Jérôme Jean Tantot, Xavier Carbonneau, Philippe Gérard Chanez, Nicolas Garcia Rosa, Alejandro Martin Pleguezuelo, Nicolas Joseph Sirvin
-
Patent number: 11913404Abstract: Disclosed is an air outlet of a nacelle for an aircraft turbojet engine, the nacelle forming a solid of revolution about a longitudinal axis, the air outlet having a straightening device having a plurality of flaps mounted circumferentially and protruding, each flap being mounted pivoting around a pivot axis, forming, with respect to the longitudinal axis, an angle of convergence in a radial plane, between a closed position, in which each flap extends along the pivot axis in the aerodynamic prolongation of the trailing edge in order to support a thrust phase and a deployed position, in which each flap extends in a deployed plane forming an angle of deployment with respect to the closed position about the pivot axis, so as to support a reverse thrust phase.Type: GrantFiled: January 14, 2021Date of Patent: February 27, 2024Assignee: SAFRAN AIRCRAFT ENGINESInventors: Philippe Gérard Chanez, Daniel-Ciprian Mincu
-
Publication number: 20240002036Abstract: An air intake for an aircraft propulsion assembly extending along a longitudinal axis and comprising a turbine engine that comprises a primary flow path and a secondary flow path for respectively guiding a primary air flow and a secondary air flow during a thrust, and thrust reversal means for changing the secondary airflow into a reverse airflow during a thrust reversal. The air intake comprising a peripheral external enclosure comprising, in each plane radial to the axis, a point of maximum curvature for detaching the reverse airflow, an osculating circle defining a radius of curvature that is defined at each of the points of maximum curvature. The average value of the radii of curvature being less than a product of 0.028 times an internal radius of the intake at the fan.Type: ApplicationFiled: October 28, 2021Publication date: January 4, 2024Inventors: Yacine Cheraga, Daniel-Ciprian Mincu, Philippe Gérard Chanez, Jean-Loïc Hervé Lecordix
-
Publication number: 20230407797Abstract: An aircraft dual-flow turbine engine assembly includes: an internal shroud for externally delimiting a primary flow path of the turbine engine gases; an external shroud for internally delimiting a secondary flow path of the turbine engine gas; and at least one air discharge duct extending between the internal shroud and the external shroud, the air discharge duct opening into the secondary flow path through an outlet orifice equipped with discharge fins. At least some of the discharge fins are movably mounted so as to be able to be incidence-control between a propulsion position, and a reverse thrust position.Type: ApplicationFiled: November 2, 2021Publication date: December 21, 2023Applicant: SAFRAN AIRCRAFT ENGINESInventors: Eva Julie LEBEAULT, Philippe Gérard CHANEZ
-
Publication number: 20230349323Abstract: The invention relates to an assembly for a turbomachine, comprising: —a nacelle comprising an inlet lip which defines an air inlet, and—a device for modifying the geometry of the air inlet, comprising: —a first spout, and—a second spout, the first spout and the second spout being translatably movable in relation the nacelle between: —a first configuration, in which the first spout forms the inlet lip and the second spout extends inside the nacelle, and—a second configuration, in which the first spout extends away from the inlet lip, and the second spout forms the inlet lip so as to define an air flow channel between a downstream surface of the first spout and an upstream surface of the second spout.Type: ApplicationFiled: October 15, 2020Publication date: November 2, 2023Applicants: INSTITUT SUPERIEUR DE L AERONAUTIQUE ET DE L ESPACE, SAFRAN AIRCRAFT ENGINESInventors: Nicolas Jérôme Jean TANTOT, Xavier CARBONNEAU, Philippe Gérard CHANEZ, Nicolas GARCIA ROSA, Alejandro MARTIN PLEGUEZUELO, Nicolas Joseph SIRVIN
-
Patent number: 11772779Abstract: Propulsion assembly for an aircraft, comprising a fuselage extending along a longitudinal axis and enclosing an inner enclosure, at least one ducted engine fixed to the fuselage and comprising an air inlet section, the air inlet section being disposed at least partly in the inner enclosure, at least one plenum chamber disposed in the inner enclosure upstream of the air inlet section and in fluid communication with said air inlet section, at least one air intake formed on an outer wall of the fuselage, the inlet of the air intake being partly delimited by said outer wall of the fuselage, the air intake being configured to ingest external air and deflect it towards the plenum chamber.Type: GrantFiled: July 6, 2020Date of Patent: October 3, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Philippe Gérard Chanez, Jean-Michel Daniel Paul Boiteux, Nicolas Jérôme Jean Tantot
-
Publication number: 20230038787Abstract: Disclosed is an air outlet of a nacelle for an aircraft turbojet engine, the nacelle forming a solid of revolution about a longitudinal axis, the air outlet having a straightening device having a plurality of flaps mounted circumferentially and protruding, each flap being mounted pivoting around a pivot axis, forming, with respect to the longitudinal axis, an angle of convergence in a radial plane, between a closed position, in which each flap extends along the pivot axis in the aerodynamic prolongation of the trailing edge in order to support a thrust phase and a deployed position, in which each flap extends in a deployed plane forming an angle of deployment with respect to the closed position about the pivot axis, so as to support a reverse thrust phase.Type: ApplicationFiled: January 14, 2021Publication date: February 9, 2023Applicant: SAFRAN AIRCRAFT ENGINESInventors: Philippe Gérard Chanez, Daniel-Ciprian Mincu
-
Publication number: 20220274687Abstract: Propulsion assembly for an aircraft, comprising a fuselage extending along a longitudinal axis and enclosing an inner enclosure, at least one ducted engine fixed to the fuselage and comprising an air inlet section, the air inlet section being disposed at least partly in the inner enclosure, at least one plenum chamber disposed in the inner enclosure upstream of the air inlet section and in fluid communication with said air inlet section, at least one air intake formed on an outer wall of the fuselage, the inlet of the air intake being partly delimited by said outer wall of the fuselage, the air intake being configured to ingest external air and deflect it towards the plenum chamber.Type: ApplicationFiled: July 6, 2020Publication date: September 1, 2022Applicant: SAFRAN AIRCRAFT ENGINESInventors: Philippe Gérard CHANEZ, Jean-Michel Daniel Paul BOITEUX, Nicolas Jérôme Jean TANTOT
-
Patent number: 11199108Abstract: The outlet of a heat exchange circuit extending under a wall, such as a nacelle cowling of an aircraft engine, is divided into openings in the form of parallel slots which are elongated in the longitudinal direction and successively arranged in the transverse direction to divide the hot gas into streams while facilitating the circulation of fresh gas streams, originating from an external flow, on the intermediate laminates. The hot gas cannot fall back easily onto the outer face of the wall and risk damaging the wall, and the gas mixes more effectively with the fresh outdoor air. The openings are provided with nozzles flaring in the transverse direction and the downstream longitudinal direction to facilitate the mixing of the hot and cold gas streams.Type: GrantFiled: May 24, 2019Date of Patent: December 14, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Romain Jean-Claude Ferrier, Sébastien Christophe Chalaud, Philippe Gérard Chanez, Lauren Davis, Bastien Pierre Verdier, Christian Sylvain Vessot
-
Patent number: 11059597Abstract: An aircraft including a fuselage, a lateral support wing (1) and a propulsion assembly (100) mounted under the wing. The wing includes at least two structural spars (11ba, 11bf) extending from the fuselage toward the tip of the wing, one of these (11ba) being upstream and the other (11bf) downstream. The propulsion assembly includes a gas generator (106) and at least two offset fans (102, 104) arranged on either side of the axis of the gas generator. The offset fans (102, 104) are attached directly to one of the spars (11ba, 11bf) and the gas generator (106) is attached directly to the two spars. The leading edge of the wing forms a given sweep of angle (?) with the axis of the fuselage. The two offset fans (102, 104) are axially offset from one another.Type: GrantFiled: September 29, 2016Date of Patent: July 13, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Bruno Albert Beutin, Nicolas Maurice Herve Aussedat, Nicolas Alain Bader, Philippe Gerard Chanez, Gilles Alain Charier, Mathieu Lallia, Lionel Jean Leon Lefranc, Kevin Morgane Lemarchand, Herve Jean Albert Mouton, Nicolas Joseph Sirvin, Ludovic Michael Laurent Toupet, Christian Sylvain Vessot, Nathalie Nowakowski
-
Publication number: 20210207494Abstract: The outlet of a heat exchange circuit extending under a wall, such as a nacelle cowling of an aircraft engine, is divided into openings in the form of parallel slots which are elongated in the longitudinal direction and successively arranged in the transverse direction to divide the hot gas into streams while facilitating the circulation of fresh gas streams, originating from an external flow, on the intermediate laminates. The hot gas cannot fall back easily onto the outer face of the wall and risk damaging the wall, and the gas mixes more effectively with the fresh outdoor air. The openings are provided with nozzles flaring in the transverse direction and the downstream longitudinal direction to facilitate the mixing of the hot and cold gas streams.Type: ApplicationFiled: May 24, 2019Publication date: July 8, 2021Applicant: SAFRAN AIRCRAFT ENGINESInventors: Romain Jean-Claude FERRIER, Sebastien Christophe CHALAUD, Philippe Gerard CHANEZ, Lauren DAVIS, Bastien Pierre VERDIER, Christian Sylvain VESSOT
-
Patent number: 10859037Abstract: A double flow turbojet includes a fan including a disk centered on an axis of the fan which is provided with fan blades on its periphery, the blades having a leading edge, and an air inlet sleeve extending upstream of the fan and configured to delimit a gas flow designed to enter into the fan the air inlet sleeve having a collecting surface, the turbojet having an aspect ratio S 2 S col included in the interval [ 1.0 ; 1.0 + 0.4 ? ( L D ) ] , where L/D is the form factor of the air inlet sleeve.Type: GrantFiled: July 6, 2018Date of Patent: December 8, 2020Assignee: Safran Aircraft EnginesInventors: Philippe Gerard Chanez, Claude Sensiau
-
Patent number: 10814989Abstract: An aircraft propulsion assembly, comprising a gas generator and two fans rotated by the gas generator and offset on either side of a vertical plane passing through the axis of said gas generator. The propulsion assembly comprises an air inlet sleeve comprising an inlet pipe oriented along a first axis that is substantially parallel and offset with respect to a longitudinal axis of the gas generator, the inlet pipe dividing into a supply pipe that is connected to an inlet opening of the gas generator and a discharge pipe configured such that particles ingested by the inlet pipe are discharged without entering the gas generator.Type: GrantFiled: November 11, 2016Date of Patent: October 27, 2020Assignee: SAFRAN AIRCRAFT ENGINESInventors: Christian Sylvain Vessot, Bruno Albert Beutin, Philippe Gérard Chanez, Mathieu Patrick Jean-Louis Lallia
-
Patent number: 10539155Abstract: A propulsive assembly for an aircraft includes a nacelle and a turbojet. The nacelle includes an upstream air inlet section. The turbojet includes a fan with removable blades. The air inlet section extends longitudinally. The fan includes a rotary disk including an annular peripheral wall and a plurality of curvilinear recesses positioned circumferentially in the wall. Each blade includes a blade body extending between a blade root and a blade head in a blade axis which is roughly radial relative to a fan rotation axis. Each blade root includes a curvilinear attachment housed in a respective recess of the rotary disk. Each attachment has a support surface forming an arc. The function of the support surface is to hold the attachment in the recess. The arc extends in or parallel to an attachment plane containing the blade axis or forming with the blade axis an angle of less than 15°.Type: GrantFiled: October 27, 2016Date of Patent: January 21, 2020Assignee: SAFRAN AIRCRAFT ENGINESInventor: Philippe Gérard Chanez
-
Patent number: 10518890Abstract: The invention relates to an aircraft propulsion assembly (10), comprising a single gas generator (11) and two fans (12) drive in rotation by the gas generator (11) and offset on either side of a vertical plane passing through a longitudinal axis (X) of the gas generator, the rotational axes of the fans lying substantially in the same fan plane. According to the invention, the propulsion assembly (10) comprises an air inlet fairing formed upstream of a nacelle (25) connecting the fans, said fairing (15) having, between the fans (12), an air inlet opening (17, 17?) lying substantially perpendicular to the fan plane and on either side of this plane, the propulsion assembly further comprising an air supply device configured so as to supply the gas generator (11) with a part of the incoming air and to take off, from the remaining part of the incoming air, a cooling airflow intended to cool elements of the propulsion assembly and/or a wing supporting the propulsion assembly.Type: GrantFiled: November 8, 2016Date of Patent: December 31, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Philippe Gerard Chanez, Mathieu Patrick Jean-Louis Lallia, Christian Sylvain Vessot
-
Publication number: 20190010896Abstract: A double flow turbojet includes a fan including a disk centered on an axis of the fan which is provided with fan blades on its periphery, the blades having a leading edge, and an air inlet sleeve extending upstream of the fan and configured to delimit a gas flow designed to enter into the fan the air inlet sleeve having a collecting surface, the turbojet having an aspect ratio S 2 S col included in the interval [ 1.0 ; 1.0 + 0.4 ? ( L D ) ] , where L/D is the form factor of the air inlet sleeve.Type: ApplicationFiled: July 6, 2018Publication date: January 10, 2019Applicant: Safran Aircraft EnginesInventors: Philippe Gerard Chanez, Claude Sensiau
-
Publication number: 20180281978Abstract: The present invention relates to an aircraft comprising a fuselage, a lateral support wing (1) and propulsion assembly (100) mounted under the wing, the wing comprising at least two structural spars (11ba, 11bf) extending from the fuselage toward the tip of the wing, one of these (11ba) being upstream and the other (11bf) downstream, and the propulsion assembly comprising a gas generator (106) and at least two offset fans (102, 104) arranged on either side of the axis of the gas generator. The aircraft is characterized in that the offset fans (102, 104) are attached directly to one of the said spars (11ba, 11bf) and the gas generator (106) is attached directly to the two spars. In particular, with the leading edge of the wing forming a given sweep of angle (?) with the axis of the fuselage, the two offset fans (102, 104) are axially offset from one another.Type: ApplicationFiled: September 29, 2016Publication date: October 4, 2018Inventors: Bruno Albert BEUTIN, Nicolas Maurice Herve AUSSEDAT, Nicolas Alain BADER, Philippe Gerard CHANEZ, Gilles Alain CHARIER, Mathieu LALLIA, Lionel Jean Leon LEFRANC, Kevin Morgane LEMARCHAND, Herve Jean Albert MOUTON, Nicolas Joseph SIRVIN, Ludovic Michael Laurent TOUPET, Christian Sylvain VESSOT, Nathalie NOWAKOWSKI
-
Publication number: 20170137135Abstract: The invention relates to an aircraft propulsion assembly (10), comprising a single gas generator (11) and two fans (12) drive in rotation by the gas generator (11) and offset on either side of a vertical plane passing through a longitudinal axis (X) of the gas generator, the rotational axes of the fans lying substantially in the same fan plane. According to the invention, the propulsion assembly (10) comprises an air inlet fairing formed upstream of a nacelle (25) connecting the fans, said fairing (15) having, between the fans (12), an air inlet opening (17, 17?) lying substantially perpendicular to the fan plane and on either side of this plane, the propulsion assembly further comprising an air supply device configured so as to supply the gas generator (11) with a part of the incoming air and to take off, from the remaining part of the incoming air, a cooling airflow intended to cool elements of the propulsion assembly and/or a wing supporting the propulsion assembly.Type: ApplicationFiled: November 8, 2016Publication date: May 18, 2017Inventors: Philippe Gerard CHANEZ, Mathieu Patrick Jean-Louis LALLIA, Christian Sylvain VESSOT
-
Publication number: 20170137134Abstract: An aircraft propulsion assembly, comprising a gas generator and two fans rotated by the gas generator and offset on either side of a vertical plane passing through the axis of said gas generator. The propulsion assembly comprises an air inlet sleeve comprising an inlet pipe oriented along a first axis that is substantially parallel and offset with respect to a longitudinal axis of the gas generator, the inlet pipe dividing into a supply pipe that is connected to an inlet opening of the gas generator and a discharge pipe configured such that particles ingested by the inlet pipe are discharged without entering the gas generator.Type: ApplicationFiled: November 11, 2016Publication date: May 18, 2017Applicant: SAFRAN AIRCRAFT ENGINESInventors: Christian Sylvain Vessot, Bruno Albert Beutin, Philippe Gérard Chanez, Mathieu Patrick Jean-Louis Lallia
-
Publication number: 20170114799Abstract: A propulsive assembly for an aircraft includes a nacelle and a turbojet. The nacelle includes an upstream air inlet section. The turbojet includes a fan with removable blades. The air inlet section extends longitudinally. The fan includes a rotary disk including an annular peripheral wall and a plurality of curvilinear recesses positioned circumferentially in the wall. Each blade includes a blade body extending between a blade root and a blade head in a blade axis which is roughly radial relative to a fan rotation axis. Each blade root includes a curvilinear attachment housed in a respective recess of the rotary disk. Each attachment has a support surface forming an arc. The function of the support surface is to hold the attachment in the recess. The arc extends in or parallel to an attachment plane containing the blade axis or forming with the blade axis an angle of less than 15°.Type: ApplicationFiled: October 27, 2016Publication date: April 27, 2017Inventor: Philippe Gérard CHANEZ