Patents by Inventor Kaelig Merwen ORIEUX
Kaelig Merwen ORIEUX 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: 11814987Abstract: 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: GrantFiled: October 23, 2018Date of Patent: November 14, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Cédric Zaccardi, Kaëlig Merwen Orieux, William Henri Joseph Riera
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Publication number: 20230228201Abstract: An annular intermediate casing for a turbomachine through which an aerodynamic airstream circulates, including a radially internal shroud (31), a radially external shroud, at least one stator blade including a vane with a leading edge, and at least one aero-dynamic member which is formed of a structural arm extending radially at least in part between the radially internal shroud and the radially external shroud. The aerodynamic member includes a leading edge which is aligned with the leading edge of the stator blade in one plane and which is borne by a profiled portion positioned upstream of the structural arm in the direction of circulation of the aerodynamic airstream, the profiled portion, the structural arm, the radially internal shroud and the radially external shroud being monobloc.Type: ApplicationFiled: April 22, 2021Publication date: July 20, 2023Inventors: Frederic Jacques Eugene GOUPIL, Francois Marie Paul MARLIN, Kaelig Merwen ORIEUX, Philippe VERSEUX, Yacine CHERAGA
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Patent number: 11525366Abstract: The invention concerns a flow straightener unit (1) for a fan module of a turbomachine, the straightener unit (1) comprising a plurality of blades (2) distributed about an axis of rotation, each blade (2) is made of a composite material and comprises an aerofoil (21) and a root (22) intended to be assembled on a hub (4) of the turbomachine. The unit (1) comprises a centring and attachment plate (3) of the blade (2) on the turbomachine intended to be attached to the hub (4) at a determined azimuthal position and to the root (22) of the blade (2), the plate (3) is designed to be screwed to the hub (4) by screws (51a) that are longitudinal with respect to the axis of rotation of the unit (1) and screwed to the root (22) of the blade (2) by screws (52) that are radial with respect to the axis of rotation of the unit (1).Type: GrantFiled: November 8, 2019Date of Patent: December 13, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Alexandre Bernard Marie Boisson, Kaëlig Merwen Orieux
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Patent number: 11280204Abstract: 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: GrantFiled: April 27, 2017Date of Patent: March 22, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Cédric Zaccardi, Kaëlig Merwen Orieux, William Henri Joseph Riera
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Publication number: 20210396143Abstract: The invention concerns a flow straightener unit (1) for a fan module of a turbomachine, the straightener unit (1) comprising a plurality of blades (2) distributed about an axis of rotation, each blade (2) is made of a composite material and comprises an aerofoil (21) and a root (22) intended to be assembled on a hub (4) of the turbomachine. The unit (1) comprises a centring and attachment plate (3) of the blade (2) on the turbomachine intended to be attached to the hub (4) at a determined azimuthal position and to the root (22) of the blade (2), the plate (3) is designed to be screwed to the hub (4) by screws (51a) that are longitudinal with respect to the axis of rotation of the unit (1) and screwed to the root (22) of the blade (2) by screws (52) that are radial with respect to the axis of rotation of the unit (1).Type: ApplicationFiled: November 8, 2019Publication date: December 23, 2021Applicant: SAFRAN AIRCRAFT ENGINESInventors: Alexandre Bernard Marie BOISSON, Kaelig Merwen ORIEUX
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Patent number: 11149570Abstract: An outlet guide vane for a fan of a turbomachine is provided. The outlet guide vane includes a blade made of composite material and having a radial inner end, a first metal fastener portion fastened to the radial inner end, a first platform extending transversely with respect to the blade in the vicinity of the radial inner end. The first metal fastener portion is to be mounted on and fastened to an upstream flange and to a downstream flange of a hub. The first platform is monolithic with the first metal fastener portion or with the blade. A rectifier wheel and a turbomachine including the outlet guide vane are also provided.Type: GrantFiled: July 16, 2019Date of Patent: October 19, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Alexandre Bernard Marie Boisson, Larry Sylvio Laborieux, Kaëlig Merwen Orieux
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Patent number: 10907489Abstract: A vaned ring for a turbomachine stator includes an outer shell, a vane having a vane head, and two platforms arranged circumferentially on either side of the vane head, and fixed on a radially inner face of the outer shell by detachable fasteners. The vane head has first conical seatings bearing on respective second conical seatings of the two platforms so as to prevent a displacement of the vane radially inwards and along the circumferential direction. The vaned ring includes a frangible pin including a base mounted on the outer shell and a head projecting radially inwards with respect to the outer shell and having a head surface forming, vis-à-vis a top surface of the vane head, a stop opposing a displacement of the vane radially outwards.Type: GrantFiled: February 11, 2019Date of Patent: February 2, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Thierry Georges Paul Papin, Kaelig Merwen Orieux, Jean-Marc Claude Perrollaz
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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: 10584606Abstract: A case of a turbomachine including an inner wall of revolution coaxial with a principal longitudinal axis of the turbomachine, an acoustic insulation structure installed inside the inner wall of revolution that has an annular principal shape centred on the longitudinal axis, and an abradable annular element, wherein the abradable element is fixed on an inner annular face of the acoustic insulation structure.Type: GrantFiled: November 29, 2017Date of Patent: March 10, 2020Assignee: SAFRAN AIRCRAFT ENGINESInventors: Remi Roland Robert Mercier, Kaelig Merwen Orieux
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Publication number: 20200025001Abstract: The invention describes an outlet guide vane (1) for a fan (2) of a turbomachine, comprising: a blade (10) made of composite material and having a radial inner end (101), a first metal fastener portion (11) fastened to the radial inner end (101), at least a first platform (13) extending transversely with respect to the blade (10) in the vicinity of its radial inner end (101), the first metal fastener portion (11) being configured to be mounted on and fastened to an upstream flange (62) and to a downstream flange (63) of a hub (6), the first platform (13) being monolithic with the first metal fastener portion (11) or with the blade (10). The invention also relates to a rectifier wheel (3) and to a turbomachine comprising such an outlet guide vane (1).Type: ApplicationFiled: July 16, 2019Publication date: January 23, 2020Applicant: SAFRAN AIRCRAFT ENGINESInventors: Alexandre Bernard Marie BOISSON, Larry Sylvio Laborieux, Kaëlig Merwen Orieux
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Publication number: 20200024997Abstract: A vaned ring for a turbomachine stator includes an outer shell (42), a vane (46) having a vane head (52), and two platforms (60) arranged circumferentially on either side of the vane head, and fixed on a radially inner face (61) of the outer shell by means of detachable fasteners. The vane head has first conical seatings (70) bearing on respective second conical seatings (72) of the two platforms so as to prevent a displacement of the vane radially inwards and along the circumferential direction. The vaned ring comprises a frangible pin (73) including a base (73A) mounted on the outer shell and a head (73B) projecting radially inwards with respect to the outer shell and having a head surface (73C) forming, vis-a-vis a top surface (74) of the vane head, a stop opposing a displacement of the vane radially outwards.Type: ApplicationFiled: February 11, 2019Publication date: January 23, 2020Applicant: SAFRAN AIRCRAFT ENGINESInventors: Thierry Georges Paul Papin, Kaelig Merwen Orieux, Jean-Marc Claude Perrollaz
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Patent number: 10392955Abstract: A turbomachine fan frame including a central hub, a plurality of radial vanes installed on the hub and distributed around the hub, each vane including an inner radial end root at which the vane is fixed to the hub, a plurality of flow stream reconstitution platforms, each platform being installed between the roots of two adjacent vanes and radially at a distance from the hub, wherein each platform is fixed to the hub by at least one support element associated with the platform, the support element located between the associated platform and the hub and located between the roots of two adjacent vanes.Type: GrantFiled: August 2, 2016Date of Patent: August 27, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Thierry Georges Paul Papin, Kaelig Merwen Orieux, Virginie Guilbert, Lise Lacroix
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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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Publication number: 20180156237Abstract: 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: ApplicationFiled: December 1, 2017Publication date: June 7, 2018Inventors: Thierry Georges Paul PAPIN, Marc-Antoine Anatole GOT, Kaelig Merwen ORIEUX, Cedric ZACCARDI
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Publication number: 20180149033Abstract: A case of a turbomachine including an inner wall of revolution coaxial with a principal longitudinal axis of the turbomachine, an acoustic insulation structure installed inside the inner wall of revolution that has an annular principal shape centred on the longitudinal axis, and an abradable annular element, wherein the abradable element is fixed on an inner annular face of the acoustic insulation structure.Type: ApplicationFiled: November 29, 2017Publication date: May 31, 2018Applicant: SAFRAN AIRCRAFT ENGINESInventors: Remi Roland Robert MERCIER, Kaelig Merwen ORIEUX
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Patent number: 9945261Abstract: A support structure suitable for interposing between the engine and the nacelle of an aeroengine and suitable for being fastened on an intermediate casing is provided. The structure includes a shroud having a plurality of sectors, a plurality of radial arms each installed between two adjacent shroud sectors, and a plurality of fasteners for fastening the plurality of shroud sectors to the plurality of radial arms. The shroud sectors and radial arms form a skeleton for transmitting structural forces within the intermediate casing. The structure includes non-structural fairings mounted on the skeleton and suitable for reconstituting the airflow passage. Each of the shroud sectors and radial arms is formed by a metal frame without mechanical discontinuity, each shroud sector metal frame defining at least one opening that is closed by a cover and each radial arm metal frame defining at least one orifice for receiving a closure plate.Type: GrantFiled: November 19, 2015Date of Patent: April 17, 2018Assignee: SNECMAInventors: Thierry Georges Paul Papin, Kaelig Merwen Orieux, Regis Eugene Henri Servant
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Patent number: 9797266Abstract: A closer for an attachment orifice of an OGV in a turbine engine, the vane having a blade fixed to a root provided with attachment orifices, the closer including a cup adapted to be fixed in the attachment orifice of an OGV; a cylindrical shaped plug engaging in the cup, the plug including an upper face inclined relative to the ground plane of the plug; a guide adapted to position the plug on the cup by rotation into a working position, in which the upper face of the plug coincides with the surface level of the vane root; a blocking system to block the plug in the working position.Type: GrantFiled: June 2, 2015Date of Patent: October 24, 2017Assignee: SNECMAInventors: Kaëlig Merwen Orieux, Thierry Georges Paul Papin
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Publication number: 20170037871Abstract: A turbomachine fan frame including a central hub, a plurality of radial vanes installed on the hub and distributed around the hub, each vane including an inner radial end root at which the vane is fixed to the hub, a plurality of flow stream reconstitution platforms, each platform being installed between the roots of two adjacent vanes and radially at a distance from the hub, wherein each platform is fixed to the hub by at least one support element associated with the platform, the support element located between the associated platform and the hub and located between the roots of two adjacent vanes.Type: ApplicationFiled: August 2, 2016Publication date: February 9, 2017Applicant: SAFRAN AIRCRAFT ENGINESInventors: Thierry Georges Paul PAPIN, Kaelig Merwen ORIEUX, Virginie GUILBERT, Lise LACROIX
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Publication number: 20160146054Abstract: A support structure suitable for interposing between the engine and the nacelle of an aeroengine and suitable for being fastened on an intermediate casing, the structure comprising a shroud having a plurality of sectors (12A, 12B, 12C, 12D), a plurality of radial arms (14A, 14B, 14C, 14D) each installed between two adjacent shroud sectors, and a plurality of fastener means (16) for fastening the plurality of shroud sectors to the plurality of radial arms, the shroud sectors and radial arms forming a skeleton (10) suitable for transmitting structural forces within the intermediate casing, the structure including non-structural fairings mounted on the skeleton and suitable for reconstituting the airflow passage.Type: ApplicationFiled: November 19, 2015Publication date: May 26, 2016Applicant: SNECMAInventors: Thierry Georges Paul PAPIN, Kaelig Merwen ORIEUX, Regis Eugene Henri SERVANT