Patents by Inventor Christophe PAUL
Christophe PAUL 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: 11008942Abstract: The present disclosure describes a lubrication oil piping gutter of an aircraft turbomachine. The lubrication oil piping gutter can be used for a sun gear train reducer of the turbomachine. The gutter may include two lateral annular walls connected at their outer periphery by an annular bottom wall. In some embodiments, the annular bottom wall may include at least one oil evacuation opening in which is located a deflector configured to facilitate the flow of oil radially from the inside to the outside of the gutter.Type: GrantFiled: July 25, 2019Date of Patent: May 18, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Christophe Paul Jacquemard, Didier Gabriel Bertrand Desombre, Serge René Morreale
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Publication number: 20200378311Abstract: The invention relates to an assembly for holding (42) an epicyclic gear train in a turbomachine comprising an annular housing (50) in which are engaged a first annular part (44) and a second annular part (46) which are locked against rotation in the housing (50) by first annular interlocking means and second annular interlocking means, respectively, wherein: the first annular interlocking means are configured to allow a first circumferential clearance between the first annular part (44) and the housing (50); the second annular interlocking means are configured to allow a second circumferential clearance between the second annular part (48) and the housing (50); the first circumferential clearance is strictly less than the second circumferential clearance.Type: ApplicationFiled: February 18, 2019Publication date: December 3, 2020Inventors: Christophe Paul JACQUEMARD, Didier Gabriel Bertrand DESOMBRE, François Marie Paul MARLIN
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Patent number: 10794392Abstract: A hub for a propeller having variable-pitch blades for a turbomachine with longitudinal rotation axis, including a plurality of blade platforms, each one being designed to receive a blade root, the platforms being distributed around the annular outer periphery of the hub concentrically with the longitudinal rotation axis, wherein each blade platform has the general geometric shape of a spherical cap, and wherein, between two adjacent blade platforms around the longitudinal rotation axis, the transverse dimension, in particular the diameter, of the hub can vary axially and radially.Type: GrantFiled: February 20, 2017Date of Patent: October 6, 2020Assignee: SAFRAN AIRCRAFT ENGINESInventors: Paul Antoine Foresto, Vivien Mickaël Courtier, Christophe Paul Jacquemard
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Patent number: 10740670Abstract: The invention relates to a method for fabricating chip cards. According to this method, an antenna and a chip card module are provided. This chip card module includes a dielectric substrate and conducting tracks at least on a face of this substrate. A connection unit is used to establish a connection between the antenna and conducting tracks of the module. The invention also relates to a method for fabricating an antenna support including such a connection unit. The invention also relates to a chip card and an antenna support which are obtained by the aforementioned methods.Type: GrantFiled: March 30, 2017Date of Patent: August 11, 2020Assignee: Linxens HoldingInventors: Cyril Proye, Valerie Mousque, Christophe Paul
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Patent number: 10730608Abstract: A pivot for an adjustable-pitch blade for a turbine engine fan hub, the pivot including a stud having coupling device for transmitting a twisting torque and an outside thread, a force-decoupling part positioned around the stud, provided with an outside thread, pressing transversely against the stud at its radially outer end, an outer rolling bearing having an inside ring mounted to press transversely against the force-decoupling part, an inner rolling bearing assembled around the force-decoupling part and held thereby, a pitch transmission ring provided with a coupling device co-operating, with the coupling device of the stud, a first clamping nut screwed onto the outside thread of the force-decoupling part in order to clamp the outer and inner rolling bearings around the fan hub, and a second clamping nut screwed onto the outside thread of the stud in order to provide clamping between the stud, the force-decoupling part, and the pitch transmission ring.Type: GrantFiled: January 4, 2017Date of Patent: August 4, 2020Assignee: SAFRAN AIRCRAFT ENGINESInventors: Olivier Belmonte, Christophe Paul Jacquemard, Clementine Charlotte Marie Mouton, Emmanuel Pierre Dimitri Patsouris
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Patent number: 10711643Abstract: A turbine engine is provided with a longitudinal rotation axis having at least one shaft with a radial axis, in particular a pitch change system for the blades of a propeller, said shaft traversing a radial passage of a substantially cylindrical case around the longitudinal axis. The turbine engine includes an annular oil guiding device around the radial shaft. The device has first and second annular parts nested in one another and secured to one another by hooping. The first part is secured by hooping to the radial shaft, and the second part is configured so as to be separated from the first part under the action of a force oriented along the radial axis and exerted on the second part by a member of the turbine engine forming a stop during a radial movement of the radial shaft.Type: GrantFiled: August 25, 2017Date of Patent: July 14, 2020Assignee: SAFRAN AIRCRAFT ENGINESInventors: Clément Cottet, Fabrice Michel François René Cretin, Christophe Paul Jacquemard, Christophe Marcel Lucien Perdrigeon, Leny Toribio
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Publication number: 20200182073Abstract: The invention relates to a vane (7) comprising: a structure made of composite material, a vane (7) root (16) attachment (9) comprising a base having a radial outer face (20) and in which a slot (24) configured to receive the vane (7) root (16) is formed and two platforms (26), extending on either side of the blade (18) opposite the radial outer face (20), and two stiffening parts (30), added and fixed on the radial outer face (20) on either side of the stilt (17) so as to tightly abut against the stilt (17).Type: ApplicationFiled: October 29, 2019Publication date: June 11, 2020Applicant: SAFRAN AIRCRAFT ENGINESInventors: Vivien Mickaël COURTIER, Anthony BINDER, Christophe Paul JACQUEMARD
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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: 10592796Abstract: A chip card manufacturing method. A module includes a substrate supporting contacts on one surface and conductive paths and a chip on another; and an antenna on a holder, the antenna including a contact pad for respectively connecting to each of the ends thereof. A solder drop is placed on each of the contact pads of the antenna. The holder of the antenna is inserted between plastic layers. A cavity is provided, in which the module can be accommodated and the solder drops remain accessible. The height of the solder drops before heating is suitable for projecting into the cavity. A module is placed in each cavity. The areas of the module that are located on the solder drops are heated to melt the solder and to solder the contact pads of the antenna to conductive paths of the module.Type: GrantFiled: September 30, 2015Date of Patent: March 17, 2020Assignee: Linxens HoldingInventors: Eric Eymard, Cyril Proye, Nicolas Guerineau, Christophe Paul
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Publication number: 20200034679Abstract: The invention relates to a method for fabricating chip cards. According to this method, an antenna and a chip card module are provided. This chip card module includes a dielectric substrate and conducting tracks at least on a face of this substrate. A connection unit is used to establish a connection between the antenna and conducting tracks of the module. The invention also relates to a method for fabricating an antenna support including such a connection unit. The invention also relates to a chip card and an antenna support which are obtained by the aforementioned methods.Type: ApplicationFiled: March 30, 2017Publication date: January 30, 2020Inventors: Cyril PROYE, Valerle MOUSQUE, Christophe PAUL
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Publication number: 20200032710Abstract: The present disclosure describes a lubrication oil piping gutter of an aircraft turbomachine. The lubrication oil piping gutter can be used for a sun gear train reducer of the turbomachine. The gutter may include two lateral annular walls connected at their outer periphery by an annular bottom wall. In some embodiments, the annular bottom wall may include at least one oil evacuation opening in which is located a deflector configured to facilitate the flow of oil radially from the inside to the outside of the gutter.Type: ApplicationFiled: July 25, 2019Publication date: January 30, 2020Applicant: SAFRAN AIRCRAFT ENGINESInventors: Christophe Paul Jacquemard, Didier Gabriel Bertrand Desombre, Serge René Morreale
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Patent number: 10293918Abstract: The invention relates to a device (12) for a non-streamlined propeller (6, 7) with blades (10) having variable pitch of a turbomachine (1), the device comprising a support (15) intended to support a blade (10) and including a cylindrical foot (17), a bearing comprising a radially internal annular section (20) and a radially external annular section (21) capable of pivoting with respect to each other, the foot (17) being mounted in said internal section (20) of the bearing. The device comprises a hub (27) mounted in the foot (17), said hub (27) including a rim (29) comprising a face (30) coming to bear on the radially internal annular section (20) of the bearing, the hub (27) and the foot (17) of the support (15) comprising complementary engagement elements (18, 28) interacting with a locking component (23).Type: GrantFiled: February 10, 2015Date of Patent: May 21, 2019Assignee: Safran Aircraft EnginesInventors: Charles-Henri Michel Marie Derrez, Adrien Jacques Philippe Fabre, Christophe Paul Jacquemard, Régis Eugène Henri Servant, Sébastien Emile Philippe Tajan
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Publication number: 20190048888Abstract: A hub for a propeller having variable-pitch blades for a turbomachine with longitudinal rotation axis, including a plurality of blade platforms, each one being designed to receive a blade root, the platforms being distributed around the annular outer periphery of the hub concentrically with the longitudinal rotation axis, wherein each blade platform has the general geometric shape of a spherical cap, and wherein, between two adjacent blade platforms around the longitudinal rotation axis, the transverse dimension, in particular the diameter, of the hub can vary axially and radially.Type: ApplicationFiled: February 20, 2017Publication date: February 14, 2019Applicant: Safran Aircraft EnginesInventors: Paul Antoine FORESTO, Vivien Mickaël COURTIER, Christophe Paul JACQUEMARD
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Publication number: 20190010957Abstract: A pivot for an adjustable-pitch blade for a turbine engine fan hub, the pivot including a stud having coupling device for transmitting a twisting torque and an outside thread, a force-decoupling part positioned around the stud, provided with an outside thread, pressing transversely against the stud at its radially outer end, an outer rolling bearing having an inside ring mounted to press transversely against the force-decoupling part, an inner rolling bearing assembled around the force-decoupling part and held thereby, a pitch transmission ring provided with a coupling device co-operating, with the coupling device of the stud, a first clamping nut screwed onto the outside thread of the force-decoupling part in order to clamp the outer and inner rolling bearings around the fan hub, and a second clamping nut screwed onto the outside thread of the stud in order to provide clamping between the stud, the force-decoupling part, and the pitch transmission ring.Type: ApplicationFiled: January 4, 2017Publication date: January 10, 2019Applicant: SAFRAN AIRCRAFT ENGINESInventors: Olivier BELMONTE, Christophe Paul JACQUEMARD, Clementine Charlotte Marie MOUTON, Emmanuel Pierre Dimitri PATSOURIS
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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
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Publication number: 20180058260Abstract: A turbine engine is provided with a longitudinal rotation axis having at least one shaft with a radial axis, in particular a pitch change system for the blades of a propeller, said shaft traversing a radial passage of a substantially cylindrical case around the longitudinal axis. The turbine engine includes an annular oil guiding device around the radial shaft. The device has first and second annular parts nested in one another and secured to one another by hooping. The first part is secured by hooping to the radial shaft, and the second part is configured so as to be separated from the first part under the action of a force oriented along the radial axis and exerted on the second part by a member of the turbine engine forming a stop during a radial movement of the radial shaft.Type: ApplicationFiled: August 25, 2017Publication date: March 1, 2018Applicant: SAFRAN AIRCRAFT ENGINESInventors: Clément Cottet, Fabrice Michel François René Cretin, Christophe Paul Jacquemard, Christophe Marcel Lucien Perdrigeon, Leny Toribio
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Publication number: 20180023406Abstract: The invention relates to an intermediate case (25) for a twin spool turbomachine for an aircraft, comprising a hub (26), an outer shell (23) and outlet guide vanes (24) installed at their ends on the hub and on the outer shell, and each of at least some of the outlet guide vanes (24) performing a heat exchanger function and comprising a lubricant passage (50a, 50b) designed to be cooled by the fan flow (58) following an outer surface of the outlet guide vane. According to the invention, the case also comprises at least one lubricant duct (55) passing along a circumferential direction of the hub (26) and at least part of which is made from a single casting with the hub, the lubricant duct (55) having at least one lateral opening communicating with the lubricant passage (50a, 50b) of at least one of the vanes (24).Type: ApplicationFiled: July 19, 2017Publication date: January 25, 2018Inventors: Cédric Zaccardi, Christophe Paul Jacquemard, Thierry Georges Paul Papin, Christophe Marcel Lucien Perdrigeon
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Patent number: 9816385Abstract: A control device of the pitch of blades of a rotor of a propeller is provided. The control device includes: a radial shaft; a pivot connected to the blade, the rotation of the radial shaft driving the rotation of the pivot for the modification of the pitch of the blade; an insert fixed rigidly to the pivot so as to block their relative displacement, the radial shaft being configured to drive in rotation the insert; at least one peg passing through the insert and the pivot for transmission of the rotation of the insert to the pivot; and a heat insulation element arranged between the insert and the pivot, whereof the thermal conductivity is less than the thermal conductivity of the pivot and of the radial shaft.Type: GrantFiled: July 24, 2014Date of Patent: November 14, 2017Assignee: SNECMAInventors: Adrien Jacques Philippe Fabre, Sebastien Emile Philippe Tajan, Christophe Paul Jacquemard, Sarah Chartier
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Publication number: 20170166295Abstract: The invention relates to a device (12) for a non-streamlined propeller (6, 7) with blades (10) having variable pitch of a turbomachine (1), the device comprising a support (15) intended to support a blade (10) and including a cylindrical foot (17), a bearing comprising a radially internal annular section (20) and a radially external annular section (21) capable of pivoting with respect to each other, the foot (17) being mounted in said internal section (20) of the bearing. The device comprises a hub (27) mounted in the foot (17), said hub (27) including a rim (29) comprising a face (30) coming to bear on the radially internal annular section (20) of the bearing, the hub (27) and the foot (17) of the support (15) comprising complementary engagement elements (18, 28) interacting with a locking component (23).Type: ApplicationFiled: February 10, 2015Publication date: June 15, 2017Applicant: Safran Aircraft EnginesInventors: Charles-Henri Michel Marie Derrez, Adrien Jacques Philippe Fabre, Christophe Paul Jacquemard, Régis Eugène Henri Servant, Sébastien Emile Philippe Tajan
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Publication number: 20080209220Abstract: There is provided a method of detecting a watermark included in a signal by way of quantization index modulation (QIM). The signal with the embedded watermark may have been geometrically transformed (e.g. spatially or temporally scaled) prior to detection. In order to detect the watermark even in such case, the embedder imposes an autocorrelation structure onto the embedded watermark data, for example by tiling. Initially, the detector applies conventional QIM detection. This step yields a first symbol vector, which corresponds to the embedded data when the signal was not tampered with, but does not correspond to the embedded data when the signal was subject to scaling. For example, when one data bit is embedded in each pixel of an image, 50% upsampling of the image causes a QIM detector to retrieve 3 data bits out of 3 received pixels, that is 3 data bits out of 2 original image pixels. Surprisingly, the autocorrelation of the first symbol vector will give a peak for a particular geometric transformation (e.Type: ApplicationFiled: March 30, 2006Publication date: August 28, 2008Applicant: Koninklijke Philips Electronics, N.V.Inventors: Job Cornelis Oostveen, Jean-Christophe Paul Durand