Patents Assigned to SAFRAN
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Patent number: 10220948Abstract: A tray table for use with a passenger seat of a transportation vehicle is provided. The tray table may be moveable between a deployed position and a stowed position relative to a seat. The tray table may include a storage compartment for storing belongings of a passenger. A lid may be provided for covering an opening of the storage compartment. A portion of the lid may be transparent such that contents of the storage compartment may be readily viewed by a passenger when the tray table is in the deployed position. A portion of a storage compartment bottom may be transparent such that contents of the storage compartment may be readily viewed by a passenger when the tray table is in the stowed position. The tray table may have any number of storage compartments and a single lid or multiple lids may be used to cover the storage compartment openings.Type: GrantFiled: May 2, 2016Date of Patent: March 5, 2019Assignee: Safran Seats USA LLCInventor: Udo W. Schultheis
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Publication number: 20190061259Abstract: A method of unclogging ducts in a part made by additive manufacturing, the ducts running from at least one well that opens out into the surface of the part, the method comprising the steps of: fabricating a guide with a body that is designed to fit in the well, the guide having internal channels that extend from a base of the guide that is accessible by a user to an outside wall of the body; cleaning the well and inserting the body of the guide in the well so that channels in the guide open out in register with inlets of ducts that are to be unclogged; and inserting a thin flexible tool, e.g. a metal cable, through the base of the guide into at least one channel therein and causing the tool to penetrate into the duct in register in the part so as to unclog it.Type: ApplicationFiled: August 29, 2018Publication date: February 28, 2019Applicant: SAFRAN LANDING SYSTEMSInventors: Olivier Rigo, Thomas Kairet, Denis Luttenbacher, Stéphane Lambre, Stefano Argentero, Gérard Balducci
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Publication number: 20190064054Abstract: A peel testing device designed to test the resistance to peeling of test pieces each formed from a support and from a reinforcement glued to this support, and comprising a frame with a face roller and at least one guide roller, a traction machine configured to peel the reinforcement from the surface of the support in a peeling direction tangential to the face roller and a sensor for measuring the force exerted by the traction machine during peeling, the device also comprising a fastening cable connected, on the one hand, to the traction machine and on the other hand to the face roller with which it forms a pulley system and the face roller which has a greater diameter than that of the guide roller comprises a mounting element for holding the reinforcement fixedly there.Type: ApplicationFiled: August 28, 2018Publication date: February 28, 2019Applicant: SAFRAN AIRCRAFT ENGINESInventors: Vincent JOUDON, Pierre Antoine BOSSAN, Matthew SAVAGE
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Publication number: 20190063244Abstract: A sector of a sectorized annular nozzle of a turbine of a turbomachine comprises an outer platform having an outer wall connected to a coaxial inner wall via at least one straightening fixed blade. The outer platform includes hooking means that hook the outer platform to a turbine fixed casing. The outer platform includes an outer circular shell, axially offset with respect to the outer wall and integrally formed with the outer wall, and the outer shell is intended to surround an angular portion of a rotor wheel. The hooking means includes an upstream circular edge and a downstream circular edge extending axially, said upstream and downstream edges being respectively configured to attach to an upstream hook and a downstream hook of said turbine casing, and said upstream and downstream edges being oriented in the downstream direction.Type: ApplicationFiled: August 23, 2018Publication date: February 28, 2019Applicant: SAFRAN AIRCRAFT ENGINESInventors: Lucien Henri Jacques Quennehen, Sébastien Serge Francis Congratel, Antoine Claude Michel Etienne Danis, Clément Jarrossay, Nicolas Paul Tableau
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Publication number: 20190063238Abstract: An assembly for a turbine engine or turbine engine test bed, including a hub defined about a longitudinal axis, a blade, including a blade root, extending in a radial direction to the longitudinal axis, the hub including a recess capable of receiving the blade root by insertion in the radial direction, wherein the recess includes a groove, the blade root including a groove, so that the two grooves are facing each other when the blade root is inserted into the recess, the assembly further includes a seal located in the two grooves.Type: ApplicationFiled: August 22, 2018Publication date: February 28, 2019Applicant: SAFRAN AIRCRAFT ENGINESInventors: Benjamin BULOT, Claire Marie FIGEUREU
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Publication number: 20190063234Abstract: A turbine includes a stator and a movable rotor, rotating around an axis, in relation to the stator. The rotor comprises at least one disc, the radially outer periphery of which comprises cavities. The rotor further includes blades, each having a blade root axially engaged in a cavity of the disc so as to radially hold the blade on the disc. At least one of the blade roots has an axially flaring shape, with the corresponding cavity having a matching shape so as to axially lock the blade root in the cavity in a first axially oriented direction. Locking means lock the blade root in the cavity in a second axially oriented direction, opposite the first direction.Type: ApplicationFiled: August 17, 2018Publication date: February 28, 2019Applicant: Safran Aircraft EnginesInventors: Antoine Frederic Jean Satre, Simon Jean-Marie Bernard Cousseau, Erwan Perrot
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Publication number: 20190063314Abstract: An aircraft propulsion unit including two distinct fan spools, and including a first duct and a second duct extending downstream of the two fan spools, the propulsion unit including a control ring disposed on one of the ducts, downstream of one of the fan spools, with at least one annular internal wall extending in an interior space of the duct, the control unit of the control ring being configured to modify the shape of the internal wall, and to cause an air passage cross section in the duct to vary at the ring, a device for acquiring acoustic signals generated by acoustic waves propagating downstream of the fan spools, and a device for processing the acoustic signals, configured to measure a dephasing between the acoustic waves and to control the control ring depending on the dephasing.Type: ApplicationFiled: July 31, 2018Publication date: February 28, 2019Applicant: Safran Aircraft EnginesInventors: Jean Michel Roux, Norman Bruno Andre Jodet, Laurent Louis Robert Baudoin
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Patent number: 10215092Abstract: A constant-volume combustion chamber for an aircraft turbine engine, including a compressed gas intake valve configured to adopt an open position and a closed position, and in the closed position blocking intake of compressed gas into the chamber, and a combusted gas exhaust valve configured to adopt a closed position, in the closed position blocking exhaust of combusted gas outside the chamber. At least one of the intake and exhaust valves includes at least one spherical plug.Type: GrantFiled: July 30, 2013Date of Patent: February 26, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventor: Bernard Robic
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Patent number: 10216867Abstract: A method for modeling at least part of a non-axisymmetric surface (5) of one portion (2) of a part (1). The portion (2) is bounded by first and second extremal planes (PS, PR). The method includes processing data from a device (10), by: (a) modeling at least two basic non-axisymmetric surfaces (Sk, SI, SE) making up the surface, each of the basic surfaces (Sk, SI, SE) extending between both extremal planes (PS, PR) of the portion (S); (b) constructing at least one connection curve (CR) tangential to the first and second surfaces; (c) locally modifying the first and second basic surfaces (Sk, SI, SE) to keep to the connection curve (CR) near a discontinuity; and (d) restoring, at least part of the obtained surface (5).Type: GrantFiled: July 7, 2014Date of Patent: February 26, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Damien Joseph Cellier, Vincent Perrot, Matthieu Jean Luc Vollebregt, Nicolas Jean Fernand Pignier
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Patent number: 10214040Abstract: A method of marking the surface of a mechanical part with a predefined graphic having a holographic type effect, the method including using a laser source to apply a succession of laser pulses to the outside surface of a part for marking, with different masks being interposed between the laser source and the outside surface of the part, each mask having a particular pattern, each laser pulse having a power density of at least 20 MW/cm2 and a duration that is less than or equal to 100 ns.Type: GrantFiled: March 26, 2015Date of Patent: February 26, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Pascal Fabrice Bilhe, Geoffrey Begue-Duthu
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Patent number: 10213882Abstract: A method for repairing a fan casing in which the inner surface is damaged, includes attaching a reinforcement element to the fan casing, the reinforcement element being attached to the outer surface of the fan casing opposite the damage.Type: GrantFiled: December 16, 2015Date of Patent: February 26, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Antoine Patrice Marie Desreumaux, Patrick Jean-Louis Reghezza, Sébastien Marc Jean-Michel Perez
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Patent number: 10214127Abstract: Described are passenger seat assemblies including spreaders with a transitional region having a forward surface with a radius of curvature of about 3.5 to 3.7 inches and an aft surface with an angular profile configured so that the aft surface is located forward of a plane formed by a surface of the at least one seat back in a fully upright position. The passenger seat assemblies also include leg assemblies with a forward leg portion having a forward surface that is substantially aligned with a forward base frame tube, and an aft surface with an angular profile having a shape of an “r.Type: GrantFiled: May 17, 2017Date of Patent: February 26, 2019Assignee: Safran Seats USA LLCInventors: Jeffrey P. Wegenka, Allen Shirey, Aram Krikorian
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Patent number: 10214296Abstract: The invention relates to an architecture of a propulsion system of a multi-engine helicopter, comprising turboshaft engines (1, 2) that are connected to a power transmission gearbox (3), and comprising a low DC voltage onboard network (7) for supplying helicopter equipment during flight, characterized in that it comprises: a hybrid turboshaft engine (1) that is capable of operating in at least one standby mode during a stable flight of the helicopter; an electrotechnical pack (20) for quickly restarting said hybrid turboshaft engine in order to bring said engine out of said standby mode and to reach a mode in which it provides mechanical power, said restart pack (20) being connected to said onboard network (7); and at least two sources (4, 16, 18) of electrical power for said onboard network (7).Type: GrantFiled: March 20, 2015Date of Patent: February 26, 2019Assignee: SAFRAN HELICOPTER ENGINESInventors: Fabien Mercier-Calvairac, Sophie Humbert, Stephane Beddok
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Patent number: 10215055Abstract: A transmission assembly including a transmission member and an oil distribution system. The transmission member includes a rotary pivot, and a pivot portion for pivoting about the rotary pivot; the oil distribution system is to receive oil feed and to transfer it to an oil reception chamber of the rotary pivot; the rotary pivot includes injection orifices putting the oil reception chamber into fluid flow communication with the gap between the rotary pivot and the pivot portion to form a fluid bearing; and the transmission assembly is for injecting oil into the gap at a first pressure into an outer portion of the gap, and at a second pressure into an inner portion of the gap, the second injection pressure being different from the first injection pressure.Type: GrantFiled: March 19, 2015Date of Patent: February 26, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Augustin Curlier, Yassine Krid
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Publication number: 20190055854Abstract: An aircraft bypass turbojet engine lubrication unit includes from three to five superposed pumps, a body housing the pumps and an internal passage in the body for communicating with each of the pumps. The material of the body exhibits a stack of layers in a direction of stacking, the pumps being housed in the said stack of layers. The passage exhibits an end in the direction of stacking of the layers and an internal profile, for example triangular, with two straight lines which form the said end and which are inclined with respect to the stacked layers. The lubrication unit may be manufactured by additive manufacturing in layers.Type: ApplicationFiled: July 30, 2018Publication date: February 21, 2019Applicant: SAFRAN AERO BOOSTERS SAInventors: Mathieu Chenoux, Nicolas Fellin
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Publication number: 20190054555Abstract: Tooling (10) for making slots in a multistage disk (1) by electrochemical machining. The tooling comprises first and second rings (20) arranged coaxially about a disk axis and configured to act as cathodes, each ring having an inside periphery with a plurality of radial machining projections. The first and second rings (20) are rigidly secured relative to each other. A method of making slots in a multistage disk by electrochemical machining using such a tool.Type: ApplicationFiled: October 7, 2016Publication date: February 21, 2019Applicants: SAFRAN AIRCRAFT ENGINES, PEMTECInventors: Janvier LECOMTE, Mickael RANCIC, Sophie TALLON, Juri KRAFT, Andreas GRUTZMACHER
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Publication number: 20190054537Abstract: The invention relates to a method for manufacturing a turbine shroud (24) for a turbomachine, the method comprising manufacturing at least one turbine shroud sector (28), positioning the turbine shroud sector (26) in a bottom mold so that an outer surface of the turbine shroud sector is in contact at least in part with the bottom mold, and depositing a powder layer on an inner surface (28) of the turbine shroud sector (26). Thereafter, a top mold is positioned on the powder layer and an abradable layer (32) is made by subjecting the powder layer to a method of SPS sintering, the abradable layer (32) being for being disposed facing a turbine wheel.Type: ApplicationFiled: March 10, 2017Publication date: February 21, 2019Applicants: SAFRAN AIRCRAFT ENGINES, CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE, UNIVERSITE PAUL SABATIER - TOULOUSE IIIInventors: Jean-Baptiste MOTTIN, Yannick Marcel BEYNET, Geoffroy CHEVALLIER, Romain EPHERRE, Claude ESTOURNES
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Publication number: 20190055847Abstract: A platform suitable for being interposed between two adjacent blades of a fan, and including a passage wall, a bottom wall, and axial and radial retention surfaces. The passage wall defines a fan air flow passage, the bottom wall presents a main surface for bearing against a fan disk, and the axial and radial retention surfaces are arranged at the two axial ends of the platform. The radial retention surface arranged at the upstream axial end of the platform is radially offset from the main surface of the bottom wall in the direction in which the bottom wall bears against the disk.Type: ApplicationFiled: March 20, 2017Publication date: February 21, 2019Applicant: SAFRAN AIRCRAFT ENGINESInventors: Thomas Alain DE GAILLARD, ALEXANDRE Bernard Marie BOISSON
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Publication number: 20190055011Abstract: A drive train for a helicopter, which includes an engine, a reduction gear and a main gearbox, the reduction gear including an output shaft, which are received in assembled front and rear housings, the output shaft being supported and guided rotatably by a plurality of rolling bearings, mounted in the housings. The drive train includes a redundant mount arranged around the output shaft and between a wall of the main gearbox and the front end of the front housing, and the redundant mount is configured, sized and attached to the wall of the main gearbox and to the front end of the front housing so as to create, if the front housing breaks, a secondary path for absorbing loads passing via the redundant mount, via the output shaft of the reduction gear and via the bearings.Type: ApplicationFiled: February 7, 2017Publication date: February 21, 2019Applicant: SAFRAN TRANSMISSION SYSTEMSInventors: Thomas Marie Joseph DE DREUILLE DE LONGEVILLE, Frederic Nicolas Francois LAISNEZ
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Patent number: 10208669Abstract: A method for regulating oil cooling within an oil cooling device of a turbomachine including a first heat exchanger mounted in series with a second heat exchanger, the first heat exchanger being an oil/air exchanger while the second heat exchanger is an oil/fuel exchanger, each heat exchanger having an oil inlet and an oil outlet, a bypass directly connecting the oil inlet of the first heat exchanger to the oil outlet of the first heat exchanger, and a flow regulator to regulate the flow rate of oil flowing through the bypass. Circulation of oil though the bypass is allowed by means of the flow regulator when the oil temperature is less than or equal to a predetermined temperature comprised between 70° C. and 90° C., preferably equal to about 80° C.Type: GrantFiled: February 24, 2014Date of Patent: February 19, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Sebastien Gameiro, Brice Andre, Guillaume Mathon Margueritte, Nicolas Potel
