Patents by Inventor Cédric Zaccardi
Cédric Zaccardi 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: 10830076Abstract: A guide vane located in a fan air flow in an aircraft twin-spool turbomachine, the vane being made with an extrados body and an intrados body between which there is a thermal conduction matrix. Furthermore, the attachment devices between the two spools are arranged outside the aerodynamic part of the vane.Type: GrantFiled: February 8, 2019Date of Patent: November 10, 2020Assignee: SAFRAN AIRCRAFT ENGINESInventors: Cedric Zaccardi, Christophe Marcel Lucien Perdrigeon, Paul Antoine Foresto, Adrien Jacques Philippe Fabre
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Publication number: 20200284160Abstract: The invention proposes a turbine engine (10) of an aircraft including a primary air flow duct (16) and a secondary air flow duct (20) which is located around the primary duct (16), the secondary duct (20) including a stator (52) including a plurality of blades distributed around a main axis (A) of the turbine engine (10) and which includes inter-blade platforms (80) each one of which is located between the radially internal ends (56) or between the radially external ends (58) of two adjacent blades (54), each platform (80) including a wall (82) partially delimiting the secondary duct (20), and including a fluid circuit (40), which includes a heat exchanger (44) formed by at least one of the platforms (80), characterised in that the platform (80) includes a line (84) that has an inlet port (90) of the fluid and a fluid outlet port (92), and in that the fluid circuit (40) includes a distributor (104) associated with each port (90, 92) of said at least one platform (80) with the rest of the fluid circuit (40)Type: ApplicationFiled: March 5, 2020Publication date: September 10, 2020Applicant: SAFRAN AIRCRAFT ENGINESInventors: Cedric ZACCARDI, Alexandre Bernard Marie BOISSON, Christophe Marcel Lucien PERDRIGEON, Catherine PIKOVSKY
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Patent number: 10723476Abstract: A ring of vanes for an aircraft turbine engine, the ring presenting an axial direction and a radial direction and including a first annular sheath presenting an inside surface and a second annular sheath presenting an inside surface facing the first inside surface of the first annular sheath, the first and second sheaths being coaxial and defining between them a flow passage for a gas stream. The ring further includes both partially annular acoustic treatment panels including resonant cavities and also vanes extending in the radial direction between the first and second sheaths. Each vane includes a radial airfoil with at least two attachment tabs at each radial end of the airfoil fastened to the first or second sheath, and the inside surface of at least one of the first and second annular sheaths and the corresponding attachment tabs are covered by acoustic treatment panels arranged between the airfoils.Type: GrantFiled: November 9, 2018Date of Patent: July 28, 2020Assignee: SAFRAN AIRCRAFT ENGINESInventors: Cedric Zaccardi, Christophe Marcel Lucien Perdrigeon, Francois Marie Paul Marlin, Thierry Georges Paul Papin, Jacky Novi Mardjono
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Patent number: 10697312Abstract: A guide vane for a twin-spool aircraft turbomachine has an aerodynamic part that includes an internal lubricant cooling passage extending along a principal lubricant flow direction. The aerodynamic part is made in a single piece and also includes heat transfer fins arranged in the passage connecting the intrados and extrados walls and extending approximately parallel to the direction, these fins being distributed in successive rows along the principal direction and made such that for two rows of staggered directly consecutive fins, a first row includes fins forming a positive acute angle A1 with a dummy reference plane, while a second row includes fins forming a negative acute angle A2 with this plane.Type: GrantFiled: March 7, 2018Date of Patent: June 30, 2020Assignee: SAFRAN AIRCRAFT ENGINESInventors: Mohamed-Lamine Boutaleb, Fabien Roger Gaston Caty, Sebastien Vincent Francois Dreano, Thierry Georges Paul Papin, Christophe Marcel Lucien Perdrigeon, Cedric Zaccardi
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Patent number: 10669872Abstract: The invention relates to an intermediate case for a twin spool turbomachine for an aircraft, comprising at least one lubricant passage and piece (88a) associated with at least one of its vanes (24), comprising a lubricant passage (98a) extending along a passage axis (134a) and opening up into the lubricant duct (55a). The passage axis (134a) and the orifice axis (140a) are also at a spacing from each other along a circumferential direction (91), and a connection piece (125a) through which a connection conduit (142a) passes is firstly partially housed in the vane root (34) so as to create a communication between the connection duct (142a) and the lubricant passage orifice (124a), and secondly is partially housed in an end-piece support device (108a) or in the lubricant passage end-piece (88a), such that the connection conduit (142a) communicates with the lubricant passage (98a) in the end-piece.Type: GrantFiled: March 27, 2018Date of Patent: June 2, 2020Assignee: SAFRAN AIRCRAFT ENGINESInventors: Cédric Zaccardi, Laurent Jablonski, Christophe Paul Jacquemard, Christophe Marcel Lucien Perdrigeon
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Patent number: 10662974Abstract: The invention relates to a guide vane intended to be mounted in a turbine engine between an inner shroud (17) and an outer shroud (16), comprising a longitudinal straightening body (41) for an air flow extending between a first end (42) intended to be positioned at the inner shroud (17) and a second end (44) intended to be positioned at the outer shroud (16), the longitudinal straightening body having an aerodynamic profile defined by a leading edge (41a) and a trailing edge (41b) in the flow direction of the air flow, and by a camber line (41c) extending from the leading edge (41a) to the trailing edge (41b).Type: GrantFiled: December 1, 2017Date of Patent: May 26, 2020Assignee: SAFRAN AIRCRAFT ENGINESInventors: Thierry Georges Paul Papin, Marc-Antoine Anatole Got, Kaelig Merwen Orieux, Cedric Zaccardi
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Patent number: 10648356Abstract: A bypass turbine engine is described. The engine includes a system for bleeding gas from a primary stream to a secondary stream. The system may include two coaxial rings extending one around the other. A perforated internal first ring may be situated at the level of an outer casing and may extend substantially in a continuation of the outer casing. A perforated external second ring may be mounted such that it slides circumferentially on the first ring between a first position in which the perforations of the rings do not communicate with one another and a second bleed position in which the perforations of the rings communicate with one another.Type: GrantFiled: November 16, 2017Date of Patent: May 12, 2020Assignee: SAFRAN AIRCRAFT ENGINESInventors: Eric Pierre Georges Le Marechal, Xavier Jean Yves Alain Agneray, Thierry Georges Paul Papin, Mathieu Daniel Marie Van Gansen, Cédric Zaccardi
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Publication number: 20190368372Abstract: A bypass turbine engine is described. The engine includes a system for bleeding gas from a primary stream to a secondary stream. The system may include two coaxial rings extending one around the other. A perforated internal first ring may be situated at the level of an outer casing and may extend substantially in a continuation of the outer casing. A perforated external second ring may be mounted such that it slides circumferentially on the first ring between a first position in which the perforations of the rings do not communicate with one another and a second bleed position in which the perforations of the rings communicate with one another.Type: ApplicationFiled: November 16, 2017Publication date: December 5, 2019Applicant: SAFRAN AIRCRAFT ENGINESInventors: Eric Pierre Georges Le Marechal, Xavier Jean Yves Alain Agneray, Thierry Georges Paul Papin, Mathieu Daniel Marie Van Gansen, Cédric Zaccardi
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Publication number: 20190338661Abstract: The invention relates to a guide vane for a bypass aircraft turbomachine, its aerodynamic part comprising a first lubricant cooling interior passage in which heat transfer structures are arranged and a second lubricant cooling interior passage in which heat transfer structures are arranged, the aerodynamic part comprising a bent area connecting a lubricant output end of the first interior passage to a lubricant input end of the second passage, the bent area extending along a curved generatrix and being partly delimited by the intrados wall and the extrados wall of the vane. According to the invention, the bent area comprises one or more lubricant guide(s) arranged between the intrados and extrados walls of the vane, and each extending substantially parallel to the curved generatrix of the bent area.Type: ApplicationFiled: November 28, 2017Publication date: November 7, 2019Inventors: Cédric ZACCARDI, Christophe Marcel Lucien PERDRIGEON, Mohamed-Lamine BOUTALEB, Sébastien Vincent François DREANO
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Patent number: 10458261Abstract: An outlet guide vane wheel includes guide vanes made of polymer matrix composite material reinforced by fibers, each having a vane root and a vane tip. The vane roots are fastened on a hub of the wheel by a first connection, and the vane tips are fastened on an outer shroud of the wheel by a second connection. The first connection includes a bearing plane secured to the hub and a first backing plate for securing to the hub, with the vane roots being sandwiched between the bearing plane and the first backing plate. The second connection includes a second backing plate for securing to the shroud, with the vane tips being sandwiched between the shroud and the second backing plate.Type: GrantFiled: September 18, 2017Date of Patent: October 29, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Marc-Antoine Anatole Got, Cédric Zaccardi
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Patent number: 10392952Abstract: A guide vane for a dual flow aircraft turbine engine, the aerodynamic part of the vane including an inner duct for lubricant cooling extending in a main direction and being partly bounded by a pressure side wall and a suction side wall of the vane. A heat conduction matrix is lodged in the duct, and presents main heat transfer wings extending parallel to the direction, and laid out in staggered rows.Type: GrantFiled: March 29, 2017Date of Patent: August 27, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Cedric Zaccardi, Mohamed-Lamine Boutaleb, Sebastien Christophe Chalaud, Eric Pierre Georges Lemarechal, Thierry Georges Paul Papin
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Publication number: 20190249558Abstract: The invention relates to a guide vane located in a fan air flow (15) in a aircraft twin-spool turbomachine, the vane being made with an extrados body (32a) and an intrados body (32b) between which there is a thermal conduction matrix (80). Furthermore, the attachment means between the two spools (32a, 32b) are arranged outside the aerodynamic part (32) of the vane.Type: ApplicationFiled: February 8, 2019Publication date: August 15, 2019Applicant: SAFRAN AIRCRAFT ENGINESInventors: Cedric ZACCARDI, Christophe Marcel Lucien PERDRIGEON, Paul Antoine FORESTO, Adrien Jacques Philippe FABRE
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Patent number: 10378556Abstract: A guide vane for a dual flow aircraft turbine engine includes an aerodynamic part. The aerodynamic part includes an inner duct for lubricant cooling extending in a main direction and being partly bounded by a pressure side wall and a suction side wall of the vane. The aerodynamic part is embodied as a single piece, and includes heat transfer fins arranged in the duct expanding substantially parallel to a direction of the duct. The fins are spaced from each other depending on the direction of the duct and a transversal direction of the vane, so that at least some of the fins are arranged substantially staggered.Type: GrantFiled: January 11, 2017Date of Patent: August 13, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Cedric Zaccardi, Mohamed-Lamine Boutaleb, Sebastien Christophe Chalaud, Eric Pierre Georges Lemarechal, Thierry Georges Paul Papin
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Publication number: 20190152618Abstract: A ring of vanes for an aircraft turbine engine, the ring presenting an axial direction and a radial direction and including a first annular sheath presenting an inside surface and a second annular sheath presenting an inside surface facing the first inside surface of the first annular sheath, the first and second sheaths being coaxial and defining between them a flow passage for a gas stream. The ring further includes both partially annular acoustic treatment panels including resonant cavities and also vanes extending in the radial direction between the first and second sheaths. Each vane includes a radial airfoil with at least two attachment tabs at each radial end of the airfoil fastened to the first or second sheath, and the inside surface of at least one of the first and second annular sheaths and the corresponding attachment tabs are covered by acoustic treatment panels arranged between the airfoils.Type: ApplicationFiled: November 9, 2018Publication date: May 23, 2019Applicant: SAFRAN AIRCRAFT ENGINESInventors: Cedric ZACCARDI, Christophe Marcel Lucien PERDRIGEON, Francois Marie Paul MARLIN, Thierry Georges Paul PAPIN, Jacky Novi MARDJONO
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Publication number: 20190120071Abstract: The invention relates to a straightening assembly (28) comprising two radially inner and outer coaxial shells (34) between which extend vanes (36) made of composite material, fixed to a first end portion on the radially inner shell and to a second end portion on the radially outer shell, characterized in that: for each vane (36), in a plane perpendicular to the axis of the radially inner and outer shells (34), a straight line passing through a junction between said first and second end portions and the useful part forms an angle ? with a radius of the radially inner shell, passing through the junction between said first end portion and the useful part of said vane (36), such that 0°<??30°; the radially inner shell has a diameter ranging from 1,000 mm to 1,600 mm; and in that the radially outer shell has a diameter ranging from 2,000 to 2,800 mm; the number of vanes (36) ranges from twenty-five to forty-five.Type: ApplicationFiled: October 23, 2018Publication date: April 25, 2019Inventors: Cédric ZACCARDI, Kaëlig Merwen ORIEUX, William Henri Joseph RIERA
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Publication number: 20190106998Abstract: The invention relates to a straightening assembly for an air flow of a turbomachine, comprising two respectively coaxial radially inner and outer shrouds (30), between which extend the vanes (32) made of composite material attached, at a first end portion (42) thereof, to the radially inner shroud and at a second end portion (44) thereof, to the radially outer shroud (30), with the vanes (32) comprising a useful portion extending between the two end portions (42, 44). According to the invention, for each vane (32) in a plane perpendicular to the axis of the radially inner and outer shrouds (30), a straight line passing through a junction between said first and second end portions (42, 44) and the useful portion forms, with a radius of the radially inner shroud passing through the junction between said first end portion and the useful portion of said vane (32), an angle ? such that 0°<??90°.Type: ApplicationFiled: April 27, 2017Publication date: April 11, 2019Inventors: Cédric ZACCARDI, Kaëlig Merwen ORIEUX, William Henri Joseph RIERA
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Patent number: 10233837Abstract: The present invention relates to an assembly (20) for an aircraft turbine engine comprising a fan casing (14) having an inner surface (14b), at least one acoustic panel (26) fastened using fastening elements (48, 54) to the inner surface of the fan casing, and at least one circumferential stiffener (40) of the fan casing (14). According to the invention, the fastening elements (48, 54) connect the fan casing (14) to the stiffener (40) incorporated with the acoustic panel (26).Type: GrantFiled: March 14, 2016Date of Patent: March 19, 2019Assignee: SNECMAInventors: Cédric Zaccardi, Gwenael Sébastien François Marion
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Publication number: 20190078452Abstract: A guide vane arranged in an air flow from a fan of an twin-spool aircraft engine, the aerodynamic part of the vane including an internal lubricant cooling passage partly delimited by an extrados wall and an extrados wall of the vane. The passage is equipped with a heat conduction matrix compressed between the walls and separating a first lubricant circulation space from a second lubricant circulation space. Furthermore, the matrix defines firstly first contact elements of the intrados wall formed in the first space and between which the lubricant from the first space will circulate, and secondly second contact elements of the extrados wall formed in the second space and between which the lubricant from the first space will circulate.Type: ApplicationFiled: September 10, 2018Publication date: March 14, 2019Applicant: SAFRAN AIRCRAFT ENGINESInventors: Cedric ZACCARDI, Christophe Marcel Lucien Perdrigeon, Mohamed-Lamine Boutaleb, Dimitri Marquie
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Publication number: 20190072003Abstract: A gas turbine casing made of composite material, the casing presenting an axisymmetric shape and including, in an axial direction: an upstream flange; a retention zone presenting thickness greater than the remainder of the casing; and a downstream flange. The casing presents, in section on a plane defined by the axial direction and by a radial direction, a profile including at least first and second inclined portions that are inclined relative to each other and relative to the axis of the casing. The first and second inclined portions meet at a point situated between the retention zone and one of the flanges, this point corresponding to the vertex of an angle formed by the first and second inclined portions. The distance between the vertex of the angle and the mean radius of the casing lies in the range 1.5% and 4% of the mean radius of the casing.Type: ApplicationFiled: September 6, 2018Publication date: March 7, 2019Inventors: Cédric ZACCARDI, Mathilde Anaëlle Mélissia SAURAT
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Publication number: 20180306042Abstract: The invention relates to an intermediate case for a twin spool turbomachine for an aircraft, comprising at least one lubricant passage and piece (88a) associated with at least one of its vanes (24), comprising a lubricant passage (98a) extending along a passage axis (134a) and opening up into the lubricant duct (55a). The passage axis (134a) and the orifice axis (140a) are also at a spacing from each other along a circumferential direction (91), and a connection piece (125a) through which a connection conduit (142a) passes is firstly partially housed in the vane root (34) so as to create a communication between the connection duct (142a) and the lubricant passage orifice (124a), and secondly is partially housed in an end-piece support device (108a) or in the lubricant passage end-piece (88a), such that the connection conduit (142a) communicates with the lubricant passage (98a) in the end-piece.Type: ApplicationFiled: March 27, 2018Publication date: October 25, 2018Inventors: Cédric ZACCARDI, Laurent JABLONSKI, Christophe Paul JACQUEMARD, Christophe Marcel Lucien PERDRIGEON