Patents Assigned to SAFRAN
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Publication number: 20210261243Abstract: A taxi drive system is disclosed that provides motive force to wheels of an aircraft. The motive force is transferred by a motor powered continuous track (e.g., belt, chain, or other flexible transmission element) directly to the wheel(s) of an aircraft. The system is carried by the landing gear of the aircraft, and is placed in engagement with an aircraft wheel with sufficient force to allow for the track to drive the aircraft wheel. The taxi drive system includes a separate motor from the main aircraft engines so that the aircraft may be taxied while the main engines are shutdown or at idle.Type: ApplicationFiled: February 24, 2020Publication date: August 26, 2021Applicant: Safran Landing Systems Canada Inc.Inventor: Robert Kyle Schmidt
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Publication number: 20210262665Abstract: An injection system for a turbine engine annular combustion chamber includes a support configured to support and to center a fuel injector head. The support includes a frustoconical surface connected at its downstream end of smallest diameter to an upstream end of a cylindrical surface. The system further includes a bowl configured to mix air and fuel arranged downstream of the support and at least one axial swirl inducer extending at least in part around the support. Each swirl inducer includes vanes delimiting between them substantially axial channels for the passage of an air flow. The channels open at their upstream ends on said frustoconical surface.Type: ApplicationFiled: April 10, 2019Publication date: August 26, 2021Applicant: SAFRAN AIRCRAFT ENGINESInventors: Sébastien Alain Christophe Bourgois, Romain Nicolas Lunel, Haris Musaefendic
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Publication number: 20210262358Abstract: A turbine blade for a turbomachine includes a turbine blade with a leading edge and a trailing edge. The blade includes a radially outer platform with at least one lip extending radially towards the outside. The radially outer end of the leading edge and/or of the trailing edge of the turbine blade airfoil extending axially upstream and/or downstream, respectively, in relation to the platform. The blade has at least one partition extending radially towards the outside from the radially outer end of the turbine blade airfoil and axially between the leading edge and the upstream end of the platform and/or between the trailing edge and the downstream end of the platform.Type: ApplicationFiled: July 23, 2019Publication date: August 26, 2021Applicant: SAFRAN AIRCRAFT ENGINESInventors: Renaud James Martet, Thomas Langevin, Cyril Verbrugge
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Patent number: 11098607Abstract: An air-fire seal designed to be attached to a first tubular member of a turbomachine, such as a bleed duct, and to rest against a second member of the turbomachine, such as an intermediate casing hub, includes an attachment base having an annular shape around a reference axis (Y); a first annular fire-stop lip extending from the attachment base over a first length (L1); and a second annular air-sealing lip extending from the attachment base over a second length (L2) lower than the first length and facing the first lip.Type: GrantFiled: February 7, 2020Date of Patent: August 24, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Bruno Alexandre Didier Jacon, Damien Clément Didier Cordier, Gonzague Marie Come Jacques André Elluin, Florian Benjamin Kévin Lacroix, Philippe Didier Edmon André Libéral Nabias, Julien Vitra
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Patent number: 11099274Abstract: Device for tracking a target, the device comprising an optical system and a quadrant photodetector, wherein the optical system is configured to project a light beam coming from the target at one spot on at least one of the quadrants, and the photodetector is configured to estimate a current position of the spot by weighting of light energies received by the quadrants. The optical system comprises an optical device configured, when the spot is entirely contained in only one of the quadrants, to enlarge the spot. The invention also relates to a tracking method likely to be implemented by this tracking device.Type: GrantFiled: September 19, 2018Date of Patent: August 24, 2021Assignee: SAFRAN ELECTRONICS & DEFENSEInventors: Arnaud Davenel, Romain Ferquel
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Patent number: 11097846Abstract: A passenger seat with a recliner sofa system includes a passenger seatback with a seatback frame and a seatback cushion. The seatback cushion is rotatable relative to the seatback frame between a stowed configuration and a deployed configuration. In some examples, in the deployed configuration, the seatback cushion extends through the seatback frame. In various examples, in the deployed configuration, the seatback cushion of a forward passenger seat abuts a seat base of an aft passenger seat. In certain examples, a method of reclining a passenger seat with a recliner sofa system includes rotating a seatback cushion of a seatback of a passenger seat relative to a seatback frame of the seatback of the passenger seat, and positioning the seatback cushion relative to the seatback frame such that a portion of the seatback cushion extends through the seatback frame.Type: GrantFiled: April 2, 2018Date of Patent: August 24, 2021Assignee: Safran Seats USA LLCInventors: Jose Madrigal, Dafne Diaz, Teresa Antillon, Mario Herrera, Raul Daniel Flores Aguirre
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Patent number: 11099372Abstract: A telescope including a fastener plate, a primary mirror carried by a front face of the plate, and a secondary mirror held facing the primary mirror by a support. The primary mirror is connected to the plate by fastener elements each having a bearing receiving a pin as a sliding fit, the pin being adhesively bonded in the bearing by means of a structural adhesive; and in that the pin is provided with a central channel having a first end opening out into a portion of the pin that is accessible when the pin is in position in the holes in order to receive one end of a cannula for injecting adhesive, and a second end opening out at least into a transverse channel having at least one end opening out into the bearing.Type: GrantFiled: August 21, 2018Date of Patent: August 24, 2021Assignee: Safran Electronics & DefenseInventors: Charlotte Hoeltzel, Cédric Tacconi, Christophe Furui, Franck Seillier, Guillaume Anna
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Patent number: 11098590Abstract: A turbine engine rotor blade including a plurality of blade cross sections stacked along an axis Z between a blade root and a blade tip defining therebetween the height of the blade, each blade cross section including a leading edge (16) and a trailing edge (17) and a chord defined by the length of the segment which extends from the leading edge to the trailing edge and ensuring that: the ratio of the chord at mid-height and of the chord at the blade root is comprised between 140% and 160%; the ratio of the chord at the blade tip and of the chord at the blade root is comprised between 115% and 135%; the chord is locally constant in a blade root zone and in a blade mid-height zone.Type: GrantFiled: December 11, 2019Date of Patent: August 24, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Mickael Cavarec, Sadim Dieudonne, Nicolas Pierre Alain Edme De Cacqueray-Valmenier, Guillaume Pascal Jean-Charles Gondre
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Patent number: 11098613Abstract: A retention device for at least one cooling tube of a cooling system of a turbomachine casing, the casing extending around an axial direction of the turbomachine, the retention device includes a fixing plate suited to being made integral with the casing and a retention element for the cooling tube. The retention device includes an adjustment system configured to adjust the relative position of the retention element with respect to the fixing plate and to absorb a relative movement between the retention element and the fixing plate.Type: GrantFiled: October 25, 2018Date of Patent: August 24, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Didier Noël Durand, Nicolas Delaporte, Anthony Pierre Beguin
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Patent number: 11097345Abstract: A method includes fabricating a part out of composite material including fiber reinforcement densified by a metal matrix.Type: GrantFiled: August 2, 2016Date of Patent: August 24, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventor: Guillaume Fribourg
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Patent number: 11098648Abstract: An inlet body for a fluid injector for a turbomachine. The inlet body includes a casing defined by an internal surface and a seal valve housed inside the casing. The valve includes a sealing member including an intake duct, and internal duct into which the intake duct opens, and a seat for the sealing member. The seat defines an opening over a fluid path towards the internal duct. The internal surface includes a recess which defines at least partially a chamber communicating with the opening and with the intake duct.Type: GrantFiled: May 29, 2017Date of Patent: August 24, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventor: Christophe Chabaille
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Patent number: 11098983Abstract: A panel assembly that includes inside and outside core layers, an armor layer sandwiched between the inside and outside core layers, and an armor member that includes at least an outside portion and a transverse portion. The outside core layer includes a cut out portion defined therein. The armor layer has opposing first and second major surfaces. The outside portion of the armor member is positioned in the cut out portion of the outside core layer and the outer surface of the transverse portion is generally perpendicular to the first and second major surfaces of the armor layer.Type: GrantFiled: January 29, 2019Date of Patent: August 24, 2021Assignee: SAFRAN CABIN INC.Inventor: Panade Sattayatam
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Publication number: 20210253274Abstract: The invention relates to the field of aeronautical propulsion, and more specifically to an emptying and monitoring device and method for emptying and monitoring a fluid drained from an aircraft engine. The emptying and monitoring device comprises at least one first intake passage for receiving, directly from the aircraft, fluid drained from the engine, and a first quality sensor assembly for detecting at least one quality parameter of the fluid drained from the engine, having been admitted through the first intake passage.Type: ApplicationFiled: June 7, 2019Publication date: August 19, 2021Applicant: SAFRAN AIRCRAFT ENGINESInventors: Alméric Pierre Louis GARNIER, Josselin Xavier COUPARD
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Publication number: 20210253227Abstract: A landing gear system includes an axle having an internal cavity and a wheel rotatably coupled to the axle. A drive shaft is mounted within the cavity to be rotatable about an axis. The landing gear system further includes a rod slidably mounted within the drive shaft and a clutch. The clutch has a first portion that is coupled to the rod and rotates with the drive shaft. A second portion of the clutch is fixedly coupled to the wheel. The rod selectively reciprocates along the axis between a first position and a second position to engage and disengage the clutch.Type: ApplicationFiled: February 18, 2020Publication date: August 19, 2021Applicant: SAFRAN LANDING SYSTEMS CANADA INC.Inventors: Robert Kyle Schmidt, Steve Amberg, Jason Brown
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Publication number: 20210254702Abstract: A method of mounting a gearbox is described. The gearbox includes an outer sun gear and planet gears meshing with an inner sun gear and with the outer sun gear and each mounted for free rotation around a pivot of a planet carrier. The outer sun gear includes a first crown having a first toothing and a second crown having a second toothing each meshing with first and second toothings of the planet gears. The method consists in applying simultaneously and independently a first torque to the first crown centered on the axis of the first crown and a second torque is applied to the second crown centered on the axis of the second crown, the first torque and the second torque having identical values.Type: ApplicationFiled: June 5, 2019Publication date: August 19, 2021Applicant: SAFRAN TRANSMISSION SYSTEMSInventors: Jean-Charles Michel Pierre Di Giovanni, Florian Rappaport
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Publication number: 20210255012Abstract: A device for measuring the mass flow rate, including a flow pipe; a first set of actuators which are arranged in a first plane including a first transverse cross section of the pipe and perpendicular to the fluid flow path, these being configured to move selectively in the first plane; a control circuit configured to control a movement of the first and second actuators so that the cross-sectional area for flow through the pipe in the first plane remains constant; a measurement sensor measuring a force or a stress in a direction perpendicular to the flow path, in the vicinity of the actuators of the first set along the flow path; a computation device configured to calculate the mass flow rate passing through the flow pipe as a function of the force or stress measured by the sensor.Type: ApplicationFiled: September 3, 2019Publication date: August 19, 2021Applicants: COMMISSARIAT A L'ENERGIE ATOMIQUE ET AUX ENERGIES ALTERNATIVES, SAFRANInventors: Agustin PALACIOS LALOY, Jean- Christophe RIOU
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Publication number: 20210254481Abstract: The present disclosure relates to a holding system for the dismantling of a blade wheel, the blade wheel comprising: a disc, a plurality of blades configured to be mounted circumferentially around the disc, the plurality of blades defining a plurality of inter-blade spaces, each of the inter-blade spaces being defined circumferentially between two adjacent blades of the plurality of blades, the holding system comprising a plurality of inserts, each of the inserts being configured to be inserted into each of the inter-blade spaces in a holding position so as to hold the relative position of the blades when the plurality of blades is dismantled from the disc.Type: ApplicationFiled: June 6, 2019Publication date: August 19, 2021Applicant: SAFRAN AIRCRAFT ENGINESInventors: Nicolas Daniel DELAPORTE, Alain Dominique GENDRAUD, Emmanuel Bernard Marie CHARRIER
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Publication number: 20210255043Abstract: An infra-red imaging device comprising: a cryostat (4), an infra-red detector (6) arranged inside the cryostat (4) to receive an optical signal coming from outside the imaging device, a linear polarizer configured to polarize the optical signal along a variable direction of polarization, before the optical signal reaches the infra-red detector (6), the linear polarizer comprising: a first polarizing element (22) arranged outside the cryostat (4) and movable in rotation with respect to the cryostat (4), and a second polarizing element (24) arranged inside the cryostat (4) between the first polarizing element (22) and the infra-red detector (6)and fixed with respect to the cryostat (4).Type: ApplicationFiled: June 26, 2019Publication date: August 19, 2021Applicant: SAFRAN ELECTRONICS & DEFENSEInventors: Arnaud DAVENEL, Bernard RUOCCO-ANGARI
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Publication number: 20210258384Abstract: A system for exchanging data in an aircraft between at least two on-board devices which are interconnected by a communication link clocked at a predetermined link frequency, a first device being configured so as to: acquire measuring signals at frequencies native to the measuring signals; create frames on the basis of the measuring signals according to the native frequencies; and transmit the frames at the predetermined link frequency to a second device via the communication link.Type: ApplicationFiled: June 25, 2019Publication date: August 19, 2021Applicant: SAFRAN AIRCRAFT ENGINESInventor: Guillaume BONNET
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Publication number: 20210252794Abstract: A ceiling of a cavity is provided with contiguous portions, including a central portion defined entirely by edges, and peripheral portions defined by edges and by a portion of a frontier of the ceiling. For the central portion, a capital is defined by facets that bear against the central portion edges and converge towards an apex, and a slender support column is centered on the apex and extends from the capital to a floor of the cavity. For each peripheral portion, a capital is defined by facets that bear against the peripheral portion edges and converge towards a terminal edge extending in a plane normal to a wall of the cavity, and a support rib extends in the normal plane between the terminal edge of the capital and a wall of the cavity. The method includes manufactured the part while making the above-defined supports and capitals by additive manufacturing.Type: ApplicationFiled: June 14, 2019Publication date: August 19, 2021Applicant: SAFRAN LANDING SYSTEMSInventors: Yves COURTOIS DE LOURMEL, Sébastien MESSE, Gérard BALDUCCI, Thierry CAULE
