Patents Assigned to SAFRAN
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Patent number: 10202859Abstract: A stator blades of an axial turbomachine intended to be fitted on a ferrule in an annular row of identical blades. Each blade includes a platform with opposed lateral edges and a screw to the ferrule. The contour of the platform has, at each of the lateral edges, an angular profile designed to mate with the contiguous edge of the platform of an adjacent blade. This feature enables the angular position or pitch of the blade to be set. In a blade row fixed on a stator, mechanical clearances J1, J2, J3 and the fixation screws cause an average angular orientation error. The blades are made with a compensatory angle to offset the angular orientation error.Type: GrantFiled: November 27, 2013Date of Patent: February 12, 2019Assignee: SAFRAN AERO BOOSTERS SAInventor: Guy Biemar
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Patent number: 10202868Abstract: A discharge conduit suitable for use with a turbine engine. The discharge conduit includes an air intake end, an air outlet end and a tubular duct for guiding air between the air intake and air outlet ends. The air intake end is equipped with attachment elements for attachment to an intermediate casing of the turbine engine. The attachment element can be of the resilient snap-in type.Type: GrantFiled: April 22, 2015Date of Patent: February 12, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Florian Benjamin Kévin Lacroix, Frédéric Jacques Eugène Goupil, Noël Joseph Camille Robin, Julien Vitra
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Patent number: 10203422Abstract: A method for calibrating an ionizing radiation detector, with the aim of determining a correction factor in order to establish an amplitude-energy correspondence The invention first relates to a method for calibrating a device for detecting ionizing radiation, the detector comprising a semiconductor or scintillator detection material capable of generating a signal S of amplitude A upon interaction between ionizing radiation and the detection material, the method including the determination of a weighting factor of amplitude A.Type: GrantFiled: December 18, 2015Date of Patent: February 12, 2019Assignees: COMMISSARIAT ÀL'ÉNERGIE ATOMIQUE ET AUX ÉNERGIES ALTERNATIVES, SAFRAN IDENTITY & SECURITYInventors: Sylvain Stanchina, Guillaume Montemont
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Patent number: 10203276Abstract: A method for non-destructively testing the heating of a determined zone of a part made of a polymer material, comprising: a) taking at least one colorimetric measurement on said determined zone to be tested and obtaining the values ap, bp and Lp of the parameters a, b and L of the CIELAB colorimetric space; b) taking at least one colorimetric measurement on said reference zone of the part and obtaining the values ap/ref, bp/ref and Lp/ref of the parameters a, b and L of the CIELAB colorimetric space; c) calculating the colour difference ?Ep between the colorimetric measurements obtained in steps a) and b); and d) from the value ?Ep, determining the time period during which said zone to be tested of the part has been subjected to a determined heating temperature, by using a reference database.Type: GrantFiled: February 21, 2018Date of Patent: February 12, 2019Assignee: Safran Aircraft EnginesInventors: Jean-Louis Romero, Jean-Pierre Coulette, Angélique Melody Marine Alexia Mainczyk
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Patent number: 10203010Abstract: A method for ventilating discs (11) of a brake (10) fitted to an aircraft wheel (1) having a rim (2) mounted so as to rotate on an axle (4) of a landing gear of the aircraft. The brake discs are threaded onto a torsion tube (12) of the brake which extends around the axle. The method comprises the step of integrating a compressor (20; 30; 40) into a space extending inside the torsion tube in order to draw in air beneath the torsion tube and to return the air thus drawn in by the compressor over the torsion tube towards the brake discs.Type: GrantFiled: August 26, 2016Date of Patent: February 12, 2019Assignee: SAFRAN LANDING SYSTEMSInventors: Vincent Gonzalez, Arnaud Gapin
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Publication number: 20190039265Abstract: The present disclosure relates to a preform that includes layers of textile reinforcements that are arranged in a mold by an automatic placement head and are connected to each other, and which can be dry or pre-impregnated, in order to form a part made of composite materials after curing of an impregnating resin. The part includes a folding produced by conformation of the preform after the placement of the layers of textile reinforcements. At the folding, there are spacings between at least some of the layers of textile reinforcements.Type: ApplicationFiled: October 9, 2018Publication date: February 7, 2019Applicant: Safran NacellesInventors: Bertrand DESJOYEAUX, Benjamin PROVOST, Sébastien LOUCHARD, Fabien DEPEUX
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Publication number: 20190040816Abstract: An aircraft propulsion assembly including a bypass turbojet having a stationary inter-compressor casing positioned upstream from a space between passages, a nacelle including at its downstream end an inner wall that defines the outside of the space between passages and the inside of the bypass stream flow passage, and an outer wall arranged around the inner wall and that defines the outside of the bypass stream flow passage, at least a portion of the inner wall being suitable for moving between a maintenance position and a working position, and a thrust-reverser including a downstream element of the outer wall that is movable in translation between a retracted position and a thrust-reversal position in which it allows bypass stream deflector elements to be deployed in a radial direction, the deployment of the stream deflector elements being controlled by guide rods.Type: ApplicationFiled: February 3, 2017Publication date: February 7, 2019Applicants: SAFRAN AIRCRAFT ENGINES, SAFRAN NACELLESInventors: Carmen Gina ANCUTA, Kevin Morgane LEMARCHAND, Olivier KERBLER, Melody SERISET
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Publication number: 20190044163Abstract: A fuel cell including at least one sealing gasket (10), said sealing gasket (10) comprising a main body (12) and a heater member (14) having a heater element (16) and a power supply portion (18), the heater element (16) being embedded in the main body (12) and the power supply portion (18) being accessible from outside the main body (12).Type: ApplicationFiled: February 3, 2017Publication date: February 7, 2019Applicant: SAFRAN POWER UNITSInventor: Antoine ROMET
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Publication number: 20190039339Abstract: A device for confining a given zone of a part. The device having a first rigid sleeve open to a first end which is capable of being applied around said given zone of the part. The device further having a second flexible and elastic sleeve open to a same first end as the first sleeve and intended to be applied on the part. The second sleeve remotely surrounds the first rigid sleeve so as to form an annular space which is connected to the means for depressing the annular space.Type: ApplicationFiled: September 13, 2016Publication date: February 7, 2019Applicant: Safran Aircraft EnginesInventors: Damien Lamouche, Pierre Antoine BOSSAN
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Publication number: 20190040795Abstract: The invention relates to an assembly for a turbine engine (1), the assembly including: a casing (20) extending along a longitudinal axis (X-X?) of the turbine engine (1), a surface heat exchanger (100) arranged along an inner edge (22) of said casing (20) and including a plurality of cooling fins (110) extending radially inwards and longitudinally, and a central body (30) partially concentrically arranged within said casing (20), said casing (20) and the central body (30) defining between one another an annular air channel (Va), the width (hVa) of which is substantially constant in the region of the heat exchanger (100). The assembly is characterized in that the fins (110) are distributed over more than 180° of the inner edge (22) of the casing (20) and in that the mean height ((hMOV) of the fms (110) is more than 5% of the width (hVa) of the annular air channel (Va) in the region the heat exchanger (100).Type: ApplicationFiled: January 25, 2017Publication date: February 7, 2019Applicant: SAFRAN AIRCRAFT ENGINESInventors: Josselin David Florian REGNARD, Laurent Louis Robert BAUDOIN, Hélène Monique ORSI
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Publication number: 20190040758Abstract: A turbine ring assembly including both a plurality of ring sectors together forming a turbine ring and also a ring support structure including an upstream annular flange and a downstream annular flange, each ring sector having a first horizontal sealing tongue, an upstream vertical sealing tongue, and a first downstream vertical sealing tongue. Each ring sector also includes a second horizontal sealing tongue over the first horizontal sealing tongue in the radial direction of the ring. A first angled sealing element is housed both in a vertical groove present in the upstream tab and in a second horizontal groove, and a second angled sealing element is received both in a first horizontal groove and in a first vertical groove present in the downstream tab.Type: ApplicationFiled: October 4, 2016Publication date: February 7, 2019Applicant: SAFRAN AIRCRAFT ENGINESInventors: Lucien Henri Jacques QUENNEHEN, Sebastien Serge Francis CONGRATEL, Clement Jean Pierre DUFFAU, Matthieu SIMON
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Publication number: 20190044166Abstract: A pressure regulator system (100) for regulating a pressure in a fluid line (16A) in such a manner that the pressure complies with a predetermined regulation criterion. The system comprises a valve (20A) that is controllable in on/off mode arranged at a downstream end of the line (16A) and suitable for oscillating between an open position and a closed position; a pressure sensor (40A) connected to the line (16A) and serving to measure the pressure in the line upstream from the valve (20A); and a regulator unit (50) configured to transmit to the valve (20A) open/close commands that are determined as a function of the measured pressure. A constant frequency imposes open periods (Oi) on the valve. The durations of the open periods are modulated in such a manner that the pressure in the line complies with said predetermined criterion.Type: ApplicationFiled: January 26, 2017Publication date: February 7, 2019Applicant: SAFRAN POWER UNITSInventor: Serge Daniel LE GONIDEC
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Publication number: 20190040761Abstract: A turbine ring sector made of ceramic matrix composite material has a portion forming an annular base with an inner face for defining the inner face of a turbine ring when the ring sector is mounted on a ring support structure and an outer face from which there extends an attachment portion for attaching the ring sector to the ring support structure, the ring sector further including inter-sector faces, each for facing a neighboring ring sector when the ring sector is mounted on the ring support structure; wherein the inter-sector faces are coated in an environmental barrier that is doped with an electrically-conductive compound and that presents at least one slot.Type: ApplicationFiled: February 16, 2017Publication date: February 7, 2019Applicant: SAFRAN CERAMICSInventors: Maxime CARLIN, Lisa PIN
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Publication number: 20190039723Abstract: A torque link assembly for a shock strut includes an upper torque link that is selectively retained in a stowed position when uncoupled from a lower torque link. The upper torque link includes first and second coaxial lugs that rotatably couple the upper torque link to an alignment feature. A latch mechanism includes a latch fitting rotatably coupled to either the upper torque link or the alignment feature. The latch mechanism further includes a stop fitting fixedly coupled to the other of the upper torque link and the alignment feature. The latch fitting engages the stop fitting to maintain the upper torque link in the stowed position. At least one of the latch fitting and stop fitting is positioned between the first and second lugs of the upper torque link.Type: ApplicationFiled: August 1, 2017Publication date: February 7, 2019Applicant: Safran Landing Systems Canada Inc.Inventors: Vladimir Dubrovsky, Peter Yu, Chris Bryant
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Publication number: 20190041191Abstract: The invention relates to a method of inspecting the wear of a turbine engine part, wherein the method comprises stages in which, by means of a calculator: a reference plane is available; by measuring said part to be inspected, modelling of at least a portion of said part is acquired in the form of a three-dimensional inspection grid (8); the three-dimensional inspection grid (8) is inspected with the reference plane (5), using a dedicated algorithm using a projection of points (10; 10.1, 10.2, . . . , 10.n); if the result of the comparison is included in a predetermined tolerance range, the part is defined as compliant; otherwise, the part is non-compliant.Type: ApplicationFiled: January 27, 2017Publication date: February 7, 2019Applicant: Safran Aircraft EnginesInventor: Fabien Jean-Guillaume Arquie
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Patent number: 10195680Abstract: An anti-vibration device for the machining of a shaft includes a first fixed ring intended to be kept inside a shaft by a shoulder, the anti-vibration device including: at least one first external groove and at least one first external seal for forming at least one contact with the internal surface of the shaft; at least one first internal circumferential groove and at least one first internal seal for forming at least one contact with the external surface of the bar; an internal circumferential cavity that is able to cause the circulation of a fluid arriving through a first duct and leaving through a second duct, the first duct and second duct passing through the radial thickness of the anti-vibration device, the internal circumferential cavity making it possible to realize a vibration-damping function when a fluid passes through it.Type: GrantFiled: April 8, 2015Date of Patent: February 5, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Claude Dejaune, Cyril Douady
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Patent number: 10196147Abstract: Described is a stowable display apparatus (200) suitable for stowing a display, such as an in-flight entertainment monitor, in a storage module (110) located above a spreader or a seat bottom of a passenger seat (102). The stowable display apparatus can include an arm (228, 236) pivotally coupled to a mounting plate (222) at a pivot point (250) that is located above the spreader or seat bottom and proximate the forward end of the seat (102), thus enabling a display bracket of the arm to pivot upwards and out of an armrest assembly before rotating into a deployed position. The display arm (228, 236) can provide an easy, safe, and low-cost mechanism for stowing and deploying a display. The thin profile of the display arm allows a storage module (110) two inches wide or less to stow both a display and a table surface, each independently deployable and stowable irrespective of the other's position.Type: GrantFiled: June 7, 2016Date of Patent: February 5, 2019Assignee: Safran Seats USA LLCInventor: Raul G. Reyes
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Patent number: 10196907Abstract: A turbomachine rotor blade includes an outer part at its distal end. The outer part includes a platform defining an outside surface of a passage for gas passing through a turbomachine and presenting first and second opposite side edges; and upstream and downstream sealing wipers extending outwards from the platform, each wiper extending between two lateral faces situated respectively at the first and second side edges. The two lateral faces of the upstream or the downstream wiper are covered at least in part in an anti-wear material.Type: GrantFiled: January 16, 2013Date of Patent: February 5, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Slim Bensalah, Arnaud Negri, Sebastien Digard Brou De Cuissart, Guillaume Klein, Ba-Phuc Tang, David Mathieu, Sibylle Doremus
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Patent number: 10197467Abstract: A calibration rotor for a horizontal balancer, configured to be driven by a driver. The calibration rotor includes a main barrel that has a longitudinal axis and the periphery of which includes points for attaching balance weights that are evenly distributed in an axial and angular manner about the axis. A rotation guide is arranged at each end of the main barrel. The rotor is modular, and the rotation guide includes adapters (40, 42) which are capable of being configured to be attached to the ends of the barrel. The guide is of a first type, suitable for rotatably guiding the barrel on rollers, or of a second type, suitable for rotatably guiding the half-shell barrel. Each type of adapter has the same predetermined moment of inertia and is interchangeable on the barrel.Type: GrantFiled: June 29, 2016Date of Patent: February 5, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Alain Roland Luinaud, Alain Decocq, Christophe Guengant
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Patent number: 10196132Abstract: An aircraft landing gear assembly having a main strut configured to move between a deployed condition and a stowed condition, a damping device to oppose movement of the main strut as it approaches the deployed condition, a retraction actuator and a mechanical retraction linkage coupled between the aircraft and the main strut, and a locking device. The locking device is operable to change the retraction linkage between a locking condition in which the retraction actuator can apply a stowing force to the main strut through the retraction linkage to move the main strut from the deployed condition to the stowed condition, and an extensible condition in which the retraction linkage permits the main strut to be deployed by way of gravity.Type: GrantFiled: August 17, 2016Date of Patent: February 5, 2019Assignee: SAFRAN LANDING SYSTEMS UK LTDInventor: Robert Kyle Schmidt