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Safran patents


Recent patent applications related to Safran. Safran is listed as an Agent/Assignee. Note: Safran may have other listings under different names/spellings. We're not affiliated with Safran, we're just tracking patents.

ARCHIVE: New 2018 2017 2016 2015 2014 2013 2012 2011 2010 2009 | Company Directory "S" | Safran-related inventors


 new patent  Inertial measurement system for an aircraft

. . An inertial measurement system for aircraft, the system comprising at least one processor unit connected to at least two inertial units, namely at least one inertial unit of a first type having at least three angular sensors and three linear sensors aligned on three substantially distinct sensing axes, and an inertial unit of a second type comprising at least four angular sensors and four linear sensors aligned on four substantially distinct sensing axes. The system is arranged to calculate one piece of inertial data from the six sensors of the inertial unit of the first type and four pieces of inertial data from four distinct combinations of three angular sensors and three linear sensors selected from the sensors of the inertial unit of the second type, and the processor unit is arranged to compare the four pieces of inertial data from the measurements of the inertial unit of the second type with one another so as to determine whether the inertial unit of the second type has failed.. ... Safran

 new patent  Inertial measurement device with dual suspension

An inertial measurement device comprising a housing, a plate connected to the housing via a first stage of suspension, an inertial measurement unit comprising vibrating sensors having predetermined first resonant modes of vibration and mounted on the plate via a second stage of suspension; the first stage has a resonant frequency lower than a bandwidth of the inertial measurement unit, and the second stage has a resonant frequency higher than a resonant frequency of the first stage and lower than the first resonant modes of the vibrating sensors, the first stage having four resilient suspension elements and a center of stiffness corresponding substantially to the center of gravity of the assembly formed by the plate, the second stage, and the inertial measurement unit; the second stage having one to three resilient suspension elements.. . ... Safran

 new patent  Motor-driven aiming device and method

A method of controlling a motor-driven aiming device, the method including the steps of servo-controlling the motor as a function of a difference between a nominal speed setpoint and a measurement of the angular speed sensor, and in the event of saturation, determining a correction value for correcting the nominal speed setpoint as a function of a difference between a reference inertial position prior to the saturation and a current inertial position, and applying the correction value to the nominal speed setpoint. An aiming device for implementing the method.. ... Safran

 new patent  Bleed flow duct for a turbomachine comprising a passively actuated variable section vbv grating

The invention relates to a hub (2) of an intermediate casing (1) for a bypass turbomachine comprising: —a bleed stream duct (18), —a bleed valve, comprising a mobile door at the inlet orifice to the bleed stream duct (18), —a set of bleed vanes (22) which are mounted with the ability to rotate about a pivot (26) in the bleed stream duct (18) between an open configuration in which a flow of air coming from the inlet orifice (4) passes between the bleed vanes (22) and a closed configuration, the pivot (26) for each bleed vane (22) being closer to its leading edge (ba) than to its trailing edge (bf).. . ... Safran

 new patent  Turbine engine exhaust casing with improved lifetime

The invention relates to an exhaust casing for a turbine engine of an aircraft, including: a collar (4), a hub (5), hollow arms (63) connecting said collar (4) to said hub (5), and an opening piece (3) which is located on the collar (4) and is suitable for being connected to an outlet tube (30) of a transient-operation valve of the turbine engine. In said exhaust casing, said opening piece (3) is attached onto the collar (4) and forms an extension of a hollow arm (63) such that an air flow (7) leaving the outlet tube (30) of the transient-operation valve penetrates the hollow arm (63) and flows into the hub (5).. ... Safran

 new patent  Assembly for turbine

An assembly for a turbine of a turbine engine, including a casing and an annular duct surrounding the casing, which can be connected to a device for supplying cooling air, and having a radially inner annular wall provided with openings arranged opposite the casing in order to cool same by the impact of cooling-air jets. The casing has a plurality of axial grooves including first grooves and second grooves arranged in alternation, and the openings are distributed in a plurality of annular rows in which any pair of consecutive annular rows is such that the openings of one of the annular rows of the pair are centered relative to the first grooves while the openings of the other annular row of the pair are centered relative to the second grooves.. ... Safran

 new patent  A method of treating silicon carbide fibers

A method of treating at least one silicon carbide fiber, the method including a) putting at least one silicon carbide fiber presenting an oxygen content that is less than or equal to 1% in atomic percentage into contact with an oxidizing medium in order to transform the surface of the fiber chemically and form a surface layer of silica; b) eliminating the resulting silica layer by putting the fiber obtained after performing step a) into contact with an acid liquid medium comprising at least hydrofluoric acid; and c) depositing an interphase layer on the surface of the fiber obtained after performing step b).. . ... Safran

 new patent  Manual cutting tool

The invention relates to a manual cutting tool (110), comprising two arms (112) hinged about an axis (x), each arm comprising a first portion (114) to enable said tool to be grasped by a user and a second cutting portion (116), said first and second portions being separated from one another by said axis, the second portions of the arms comprising cutting edges (118) that define a cross-sectional area (a) of an element to be cut, the tool being configured such that a hinge on the arms about said axis brings the cutting edges of the arms together and cuts said element. The invention is characterized in that it further comprises a member (130) for protecting the user, which is made of a transparent material, said member extending substantially in parallel with said cross-sectional area and covering same completely, and being flexible in a plane substantially perpendicular to said cross-sectional area.. ... Safran

 new patent  Method for manufacturing a blade comprising a bathtub tip integrating a small wall

The invention relates to a method for manufacturing a turbine engine blade (16) including an active-surface wall (17) and a passive-surface wall (18) separated from one another, this blade (16) including a tip that has a closing wall grouping together the active-surface (17) and passive-surface (18) walls in the region of this tip to define the bottom (23) of a bathtub tip shape located at the tip of the blade, the method comprising a moulding step implementing a core defining the bathtub tip shape. According to the invention, there is a step of adding metal to the bottom (23) of the bathtub tip by means of a direct laser additive manufacturing (clad) method, to deposit material onto the bottom of the bathtub tip to form therein an inner partition (28) supported by the bottom thereof (23).. ... Safran

 new patent  Installation for manufacturing a part by implementing a bridgman method

An installation for manufacturing a part by implementation of a bridgman method includes in particular a mold intended to receive a melted material and a thermal screen movable with respect to the mold intended to be positioned in front of the solidification front during the directional solidification.. . ... Safran

Hydraulic valve for dampening pressure spikes, and associated systems and methods

Hydraulic valves for dampening pressure spikes and associated methods are disclosed herein. In one embodiment, a hydraulic valve for dampening pressure spikes includes a valve body, a poppet at least partially inside the valve body, and a pilot piston at least partially inside the valve body and away from the poppet. ... Safran

Supply device for an electric actuator system

The present disclosure relates to a nacelle for an aircraft turbofan engine and an aircraft that includes a nacelle that includes a supply device for supplying electric power to an electric actuator system allowing movement of a mobile member for deflecting a stream between a first position parallel or substantially parallel to the flow of the stream and a second position allowing the flow of the stream to be deflected so as to modify the path of the stream in one direction and/or the speed of the stream.. . ... Safran

Assistance device for a free-turbine engine of an aircraft having at least two free-turbine engines

An assistance device for a free-turbine engine of an aircraft having at least two free-turbine engines, the device including an electrical starter machine for providing prolonged assistance to the gas generator of a first engine using energy produced by an electric generator machine driven by the second engine, the device further including at least one electricity storage member electrically connected to the electrical starter machine for providing a burst of assistance to the gas generator, wherein the electrical starter machine is powered by a first power converter enabling it to exchange energy with the storage member for providing the burst of assistance, and that transmits thereto the energy supplied by a second power converter for the prolonged assistance.. . ... Safran

Turbine blade comprising an improved trailing-edge

A turbomachine blade including a hollow body defining a cavity, and including a downstream trailing edge. The blade further includes at least one hole which communicates with the cavity and which opens downstream onto the trailing edge. ... Safran

07/05/18 / #20180186446

Landing gear with threadless cardan joint

A retractable landing gear includes a main strut having an upper end that is configured to connect to aircraft primary structure and a lower end configured to connect to an axle or bogie truck. An articulated stay has a distal end configured to connect to the aircraft structure and a proximal end pivotally connected to a cardan pin member. ... Safran

07/05/18 / #20180185905

Casting tree and method of assembly

A field of lost pattern casting, and more particularly to a casting tree for lost pattern casting, and also to its method of assembly is provided. The casting tree includes at least one part support, at least one pattern, and at least one first male-female connection connecting the pattern to the part support. ... Safran

06/28/18 / #20180183404

Microelectronic structure comprising means of control of viscous damping

Microelectronic structure comprising a mobile mass mechanically linked to a first and to a second mechanical element by first and second mechanical linking device respectively, a polarisation source for the second mechanical linking device. The second mechanical linking means comprises two linking elements and a thermal reservoir placed between the linking elements, where at least one of the linking elements is made of piezoresistive material, where at least one of the first and second linking elements exhibit thermoelasticity properties. ... Safran

06/28/18 / #20180180734

Observation device having an eye-controlled laser rangefinder

The invention pertains to a hand-held observation device (1) for observing distant targets, comprising at least a first optical observation channel (20) defining a first observation optical axis (40) by receiving and imaging optical light rays onto an image plane for observations of a user, a first eyepiece being arranged at the first optical observation channel (20), and a laser range finder for determining, along an axis (3a) of the laser range finder, a distance between the observation device (1) and a target, the laser range finder being adapted to emit a laser beam through a laser emission channel (31) and receive a reflection of the laser beam through a laser receiver channel (30), characterized by at least one light source (27a, 27b) that is adapted to emit light, particularly infrared light, to illuminate a user's eye at the first eyepiece, an image sensor (25) that is adapted to capture images of the eye, and comprises an electronic image processing unit (24) for determining, in real-time, eye parameters that indicate a gazing direction of the user, and at least one opto-mechanical alignment unit (23a, 23b) that is adapted to deflect the laser beam in the laser emission channel (31) and the beam reflection in the laser receiver channel (30), the at least one opto-mechanical alignment unit comprising at least one mirror, at least one actuator that is adapted to move the at least one mirror, and alignment circuitry for controlling the at least one actuator to move the at least one mirror depending on the eye parameters to emit the laser beam onto a target in the gazing direction of the user.. . ... Safran

06/28/18 / #20180179898

Nozzle sector for a turbine engine with differentially cooled blades

A nozzle sector for a turbine engine. The nozzle sector includes a radially outer platform, a radially inner platform, a first end blade, a second end blade and at least one first central blade between the end blades in a circumferential direction of the platforms. ... Safran

06/28/18 / #20180178905

Braking system architecture for aircraft

A braking system architecture for aircraft, the architecture comprising: a brake including friction members and electromechanical actuators for exerting a braking torque on the wheel; a computer situated in the fuselage of the aircraft and arranged to produce first control signals; and a junction box situated on the undercarriage, the junction box being connected to the computer and to the electromechanical actuators, the junction box being configured to receive the first control signals and to use the first control signals to produce second control signals for application to the electromechanical actuators in order to control the electromechanical actuators.. . ... Safran

06/28/18 / #20180178904

Aircraft landing gear fitted with a braked wheel

An aircraft landing gear comprising at least an axle carried in the bottom portion of the landing gear, a wheel provided with a rim mounted on the axle of the landing gear via bearings in order to rotate about an axis of rotation, a brake threaded on the axle and including a torque tube extending around the axle, friction members mounted around the torque tube and extending between the torque tube and the rim of the wheel, and at least one brake actuator designed for selectively exerting a braking force on the friction members, the brake actuator being carried by an actuator carrier to which the torque tube is secured, and a rotary drive for driving the wheel in rotation comprising firstly an actuator for driving the wheel in rotation and secondly a transmission member for selectively transmitting movement in rotation from the rotation actuator to the rim of the wheel and extending between the axle and the torque tube. The actuator carrier is centered directly by the axle and the transmission member is carried by the brake and guided in rotation thereon by bearings.. ... Safran

06/28/18 / #20180178280

Knockout method and machine for a cluster of lost-pattern castings

A knockout method for knocking out a cluster (30) of lost-pattern metal castings (32), the cluster of castings being formed in a shell (1), wherein at least one knife is moved by means of a machine without making contact with the cluster in such a manner that the knife engages the shell, breaks it into a plurality of fragments, and detaches at least a portion of the shell from the cluster; a machine for performing the method.. . ... Safran

06/28/18 / #20180178274

Shell mold for a sector of a 360º-set of guide vanes

A shell mold (100) for a guide vane sector comprising a first platform and a second platform that are mutually coaxial and between which there extends at least one airfoil, the shell mold having a first platform molding portion (112) suitable for forming the first platform, a second platform molding portion (114) suitable for forming the second platform, an airfoil molding portion (116) suitable for forming the airfoil, a fastener molding portion (118) suitable for forming a fastener projecting from the first platform towards a first edge of the first platform, a main casting duct (120), a distribution duct (122) connecting the main casting duct (120) to the fastener molding portion (118), and an auxiliary duct (124) connecting the main casting duct (120) to the first platform molding portion (112) beside said edge.. . ... Safran

06/28/18 / #20180178243

Device for coating a turbomachine annular casing

A device applies a coating to a surface of an turbomachine annular casing, wherein the casing has an abradable layer obtained by polymerising a resin. The device includes first support means and, optionally second automated means movable relative to the first support means. ... Safran

06/21/18 / #20180172539

Device for detecting mechanical decoupling pressure

. . A pressure detection device including a mount whereon a pressure sensor is attached which comprises a membrane which has a surface intended to be subjected to a pressurized fluid and which is so arranged as to elastically deform according to pressure, and means for determining the deformation of the membrane along an axis normal to a mid-plane of the membrane in the rest state. The membrane is supported by a frame connected to the mount by a mechanical decoupling structure in order to isolate the membrane from stress resulting from a differential thermal expansion between the frame and the mount, with the membrane and the frame being made of the same material.. ... Safran

06/21/18 / #20180172534

Pressure detecting device

A pressure measuring device comprising a bracket supporting a pressure sensor which defines a first sealed enclosure with a first face of the bracket, with the pressure measuring device comprising a substrate having opposite faces, opposite which a first deformable membrane and a second deformable membrane respectively extend, with the first membrane and the second membrane respectively defining with the substrate a second sealed enclosure and a third sealed membrane, with the pressure sensor comprising a cover in order to define a fourth sealed enclosure connected through a second channel to the first enclosure, with the pressure sensor comprising means for measuring the deformation of the first and the second deformable membranes.. . ... Safran

06/21/18 / #20180172111

Tool for balancing a turbine engine module

The invention relates to tooling for balancing a turbine engine module (10) in a balancing machine, said module having at least one stator housing (14) and a rotor (16) having a shaft (18) with a longitudinal axis a and at least one blade stage (20) surrounded by said stator housing (14), said tooling having at least a balancing frame (14), having rotor (16) guide bearings, first and second means (30, 32) designed to be attached to said stator housing (14), third and fourth means (34, 36) provided on said frame (24), to attach said first and second means (30, 32) to said frame, fifth means for transporting the frame (24), and sixth means (84, 94) for supporting the frame, provided on said frame (24) and cooperating equally well with the balancing machine and with the fifth means for transporting the frame (24).. . ... Safran

06/21/18 / #20180172035

Centre seeking actuator

A centre seeking actuator having an outer cylinder, a slave cylinder slidably disposed within the outer cylinder, and a rod assembly having a piston slidably disposed within the slave cylinder and a rod extending from the piston to a point outside the outer cylinder. One or more first dynamic seals are arranged to act on a side wall of the rod to inhibit working fluid leaking from the outer cylinder, and one or more second dynamic seals are arranged to act on a sidewall of the slave cylinder to inhibit working fluid leaking from the outer cylinder.. ... Safran

06/21/18 / #20180171932

Assembly comprising an exhaust case and a downstream rotationally symmetrical part

The invention relates to an assembly comprising: a turbomachine exhaust case (110) that includes an external sleeve and an internal sleeve inside the former, both sleeves extending concentrically about a turbomachine axis, and also includes a plurality of arms extending radially between the sleeves; and an annular part (130) that is centered about the axis, is mounted on one sleeve of the exhaust case, and is located downstream of the exhaust case in the direction in which the air flows inside the turbo-machine; the assembly is characterized in that the annular part and the sleeve of the exhaust case on which the annular part is mounted each have a circumferential thread (131, 115), said threads cooperating with each other in order to allow the annular part to be screwed onto the sleeve of the exhaust case.. . ... Safran

06/21/18 / #20180171874

Turbine engine rapid reactivation method and system

The system for rapidly reactivating a turbine engine of an aircraft includes an electrical machine that is dc powered from an on-board electrical power supply network. The system also includes a switch interposed between the on-board network and the electrical machine, an additional set including a plurality n electrical energy storage elements, and a control unit for controlling a device for discharging the storage elements and adapted to enable a series circuit including at least some of the n electrical energy storage elements to be connected in parallel with the on-board network so that when the rapid reactivation system is in operation the electrical machine is powered by a voltage level higher than the voltage level of its nominal characteristics.. ... Safran

06/21/18 / #20180171803

Method for manufacturing a turbomachine fan having a reduced noise level at multiple rotational frequencies of said turbomachine

The invention relates to a method (100) for manufacturing a turbomachine fan comprising a plurality of blades mounted on a disc extending along a longitudinal axis, said method comprising the following steps of: —measuring (102) at least one structural parameter of each of the blades in the cold state, and, for each of the blades, estimating (103) at least one structural parameter in operation relating to a blade from the structural parameter(s) measured on said blade in the cold state, —determining (104) an optimal sequence of the blades around the disc from the structural parameters estimated in operation for each of the blades, and —mounting (105) the blades on the disc in the optimal sequence thus determined.. . ... Safran

06/21/18 / #20180170580

Method for monitoring an aircraft engine operating in a given environment

The present invention relates to method for monitoring an engine (1) of an aircraft (2) operating in a given environment. The invention is characterized in that it comprises the implementation, via means for data processing (31), of the steps of: (a) receiving a sequence of n-tuples (x1-exec . ... Safran

06/21/18 / #20180170531

Aircraft assembly including deflection sensor

An aircraft assembly having a first region, a second region spaced from the first region by a flexible region, and a deflection sensor. The first region has greater positional stability than the second region such that the second region deflects further from its default position than the first region during in-use loads. ... Safran

06/21/18 / #20180170529

Aircraft assembly and method

An aircraft assembly having landing gear with a known deployment value, apparatus for permitting landing gear deployment, down-lock sensing apparatus, a navigation system, a landing gear control system, a flight control system, and a deployment controller. The deployment controller is configured to: calculate a touch down value using the aircraft position and speed information provided by the aircraft navigation system; command the landing gear control system to provide the deploy signal when the touch down value reaches a deployment threshold value which is greater than the landing gear deployment value; and command the flight control system to execute a landing abort sequence if the controller does not receive the down-lock signal from the landing gear sensing apparatus within a deployment value window which is greater than or equal to the known deployment value for the landing gear but less than the touch down value.. ... Safran

06/21/18 / #20180170528

Aircraft landing gear

The invention relates to an aircraft landing gear (2) comprising:—a leg (6) having a first leg portion (8) that can be pivotably connected to a load-bearing structure of the aircraft (1) in order for the landing gear (2) to be deployed and retracted, and a second leg portion (9) that is rotatable in relation to the first leg portion (8);—a wheel (13, 14) that is rotatable in relation to the second leg portion (9), and an electric motor (15, 16) that can rotate the wheel (13, 14) in relation to the second leg portion (9);—a transmission mechanism (17) designed to selectively transmit torque generated by the electric motor (15, 16) to the wheel (13, 14) in order to rotate the wheel in relation to the second leg portion (9) or to the second leg portion (9) in order to rotate the second leg portion (9) in relation to the first leg portion (8).. . ... Safran

06/21/18 / #20180170527

Aircraft landing gear

The invention relates to an aircraft landing gear (2) comprising: a leg (6) that can be pivotably connected to a load-bearing structure of the aircraft (1) in order for the landing gear (2) to be deployed and retracted; a wheel (13, 14) that is rotatable in relation to the leg (6), and an electric motor (15, 16) that can rotate the wheel (13, 14) in relation to the leg (6); a transmission mechanism (17) designed to selectively transmit torque generated by the electric motor (15, 16) to the wheel (13, 14) in order to rotate the wheel in relation to the leg (6) or to the leg (6) in order to rotate the leg (6) in relation to the load-bearing structure of the aircraft (1) in order to deploy or retract the landing gear (2).. . ... Safran

06/21/18 / #20180170522

System for electromechanical pitch actuation for a turbine engine propeller

A pitch actuation system for a turbine engine propeller includes an actuator with movable part configured to rotate the blades of the propeller relative to the blade pitch axes. The actuator includes a transmission screw that is rotatable and movable in translation along a longitudinal axis, and a nut that engages the screw to move in translation along the longitudinal axis to adjust the pitch of the propeller blades. ... Safran

06/21/18 / #20180169972

Method and tooling for shaping a fan casing

A method of shaping the profile of a fan casing having an inside surface, the method including placing the casing around a surface of revolution of a drum of shaping tooling; interposing at least one bladder that is inflatable under the action of a fluid under pressure between a portion of the inside surface of the casing and the drum, the bladder extending over all or part of the surface of revolution of the drum; stoving the assembly including the casing, the tooling, and the at least one bladder at a predetermined temperature; and during the stoving, applying isostatic pressure via the at least one bladder so as to impart a cylindrical profile to the portion of the inside surface of the casing facing the at least one bladder.. . ... Safran

06/14/18 / #20180166058

Acoustic attenuation panel made of an oxide ceramic composite material with a core made of an electrochemically-converted metal material

. . The present disclosure relates to a method for producing an acoustic attenuation panel having two outer skins made from a composite material with a ceramic matrix containing a fibrous reinforcement. The skins are assembled on each side of a central honeycomb core having walls forming acoustic cavities produced by at least partial electrochemical conversion of aluminum into aluminum oxide. ... Safran

06/14/18 / #20180164339

Out-of-plane-accelerometer

Accelerometer including a seismic mass in a plane and a first capacitor plate and a second capacitor plate arranged parallel to the plane. The seismic mass is arranged in between the first capacitor plate and the second capacitor plate. ... Safran

06/14/18 / #20180164150

Method and device for determining the vibration of rotor blades

A method for determining the vibration of turbomachine rotor blades, including steps of measuring, via one or more sensors, the variation in the minimum distance between each sensor and the top of each blade along a radial axis of the rotor, between successive rotations of each blade in front of each sensor, a minimum distance value being obtained on each passage of each blade in front of each sensor, in order to deduce therefrom a variation in the lengths of the blades along the radial axis; and, using directly, as such, the variation in the length of the blades along the radial axis in a model of the deformation of the blades, in order to deduce therefrom characteristics of one or more vibrational modes of the rotating blades. A turbomachine can be equipped with a device implementing this method.. ... Safran

06/14/18 / #20180164102

Navigational aid method, computer program product and inertial navigation system therefor

The invention relates to a navigational aid method for an inertial navigation system including at least one inertial sensor (4) having a sensitive axis (x-x), each inertial sensor (4) comprising an asg gyroscope (8) able to deliver an asg signal representative of a rotation about the corresponding sensitive axis (x-x), and a mems gyroscope (10) able to deliver a mems signal representative of a rotation about the corresponding sensitive axis (x-x), the method including the steps of: between a first date and a subsequent third date, calculating a path from the mems signals; from the third date, calculating the path from the asg signals; estimating a bias vector introduced by the mems gyroscopes (10), from the mems signals and asg signals; at a fourth date subsequent to the third date, resetting the path.. . ... Safran

06/14/18 / #20180164075

Aiming system comprising a screen covered with a tactile interface and corresponding aiming method

The invention provides an aiming system comprising a display control unit connected to a screen having a surface that is covered at least in part by a touch interface, the display control unit being arranged to inlay an aiming frame in the images displayed on the screen. According to the invention, the display control unit is arranged to: inlay a control zone in a portion of the touch interface; and to move the aiming frame on the screen as a function of a contact exerted on the touch interface in the control zone. ... Safran

06/14/18 / #20180163850

Reduction gear having an epicyclic gear train for a turbine engine

A reduction gear having an epicyclic gear train for a turbine engine, in particular of an aircraft, comprising: a planetary shaft having an axis of rotation a; a ring gear having an axis a extending around said planetary shaft; planet gears distributed around said axis a, which mesh with said ring gear and the planetary shaft; and a planet carrier including members for supporting bearings of the planet gears, having axes of rotation b, which are evenly distributed around the axis a, as well as a part holding each supporting member substantially by the middle thereof along the axis b thereof, wherein said supporting members are made as a single part having means for supplying lubricating oil to said bearings. A method for assembling said reduction gear is also provided.. ... Safran

06/14/18 / #20180163556

Assembly of turbine engine parts comprising a fan blade having an integrated platform, and corresponding turbine engine

The invention relates to an assembly of turbine engine (50) parts having a longitudinal axis (x), the assembly comprising at least two adjacent fan blades made of a 3d woven composite material, each blade (1) comprising a root (3), a vane (2) extending from the root (3), and an integrated platform (4) inserted between the root (3) and the vane (2), the platform (4) extending on either side of the vane (2) and forming a pressure face platform portion (4i) and a suction face platform portion (4e), the pressure face and suction face platform portions of adjacent blades being connected by a fin (14) extending at least radially at the outer side of the pressure face and suction face platform portions (4i, 4e), relative to the longitudinal axis (x), having a substantially triangular transverse cross section and extending axially and so as to upper overlap the longitudinal edges (11a, 11b) of the pressure face and suction face platform portions (4i, 4e) of the adjacent blades.. . ... Safran

06/07/18 / #20180156654

Oil level sensor

The oil level sensor is associated with a tank containing oil and comprises a float movable along guide means and which can float on the oil of the tank, so as to move with the oil level, a permanent magnet movable with the float, and an electronic card provided with magnetic switches sensitive to said magnet. The guide means of the spherical float are positioned about the float and the contacts thereof with said float are limited to three substantially linear zones.. ... Safran

06/07/18 / #20180156239

Turbine engine part with non-axisymmetric surface

A turbine engine part or set of parts including at least first and second obstacles each having a leading edge and a trailing edge, and a platform from which the obstacles extend; wherein the platform has, between the pressure side of the first obstacle and the suction side of the second obstacle a non-axisymmetric surface defining at least one fin with a substantially triangular cross-section, each fin being associated with a leading position and a trailing position on the surface between which the fin extends, such that the leading position is upstream of each of the leading edges; the trailing position is downstream of each of the leading edges.. . ... Safran

06/07/18 / #20180156237

Turbine engine flow guide vane with removable attachment

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). It further comprises a first attachment heel (43) and a second attachment heel (45) positioned in the continuation of the longitudinal body (41) at the first end (42) and the second end (44) respectively, the first (43) and second (45) attachment heels being planar elements arranged parallel with respect to one another, each attachment heel (43; 45) being arranged at a distance from the leading edge (41a) and from the trailing edge (41b).. ... Safran

06/07/18 / #20180156232

Composite blade, comprising a leading-edge reinforcement made of another material

The invention relates to a blade made of composite material, provided with a reinforcement (17) made of a stronger material with regard to a leading edge (5) likely to be struck by solid objects, which comprises, under the aerodynamic portion of the blade, extensions (18, 19) attached to the blade root. According to the invention, the extensions (18, 19) are dissymmetric, the extension (18) located on the suction side being generally further back from the leading edge (5) than the extension (19) on the pressure side.. ... Safran

06/07/18 / #20180156139

Hydromechanical cutoff device with hysteresis for a turbomachine lubrification system

The invention relates to a lubrication system for turbomachine. The hydromechanical cutoff device is configured to close when a rotation speed of a turbomachine shaft reduces and becomes lower than a first threshold, and wherein the hydromechanical cutoff device is configured to open when the rotation speed of the shaft increases and becomes higher than a second threshold higher than the first threshold.. ... Safran

06/07/18 / #20180156070

Turbine for turbine engine

A turbine for a turbine engine is disclosed, comprising a casing and a rotor comprising blades, the radially external periphery of which comprises at least one first wiper extending radially outwards, sealing means extending radially around the blades and comprising a ring made from abradable material, the radially external ends of the first wipers being engaged in a groove in said ring made from abradable material so as to form a labyrinth-type seal, wherein said ring is formed by a plurality of contiguous annular sectors, each sector comprising at least one fixing member cooperating with at least one complementary attachment flange of the casing so as to provide mounting of each sector on the casing by axial movement of said sector with respect to the casing, the casing being configured so as to allow the mounting of the sectors in the casing solely by axial movement of said sectors.. . ... Safran

06/07/18 / #20180156069

Turbine ring assembly with axial retention

A turbine ring assembly includes both a plurality of ring sectors made of ceramic matrix composite material forming a turbine ring and also a ring support structure having two annular flanges, each ring sector having two tabs held respectively between the two annular flanges of the ring support structure. The two annular flanges of the ring support structure exert stress on the tabs of the ring sectors. ... Safran

06/07/18 / #20180156068

A turbine ring assembly

A turbine ring assembly includes both a plurality of ring sectors made of ceramic matrix composite material forming a turbine ring, and also a ring support structure. Each ring sector includes a portion forming an annular base with an inner face defining the inside space of the turbine ring and an outer face from which an attachment portion of the ring sector extends for attaching it to the ring support structure. ... Safran

06/07/18 / #20180156066

Oil tank comprising an oil level control device

An oil tank for a turbine engine comprising a closed enclosure having the shape of an arc of circle adapted to receive oil, with the enclosure having a lower portion and an upper portion at a distance from each other, and an oil level control device in the enclosure, wherein the oil level control device comprises a first sensor positioned in the lower portion of the enclosure so as to control the oil level, and a second sensor separate from the first sensor and positioned in the upper portion of the enclosure so as to control the oil level.. . ... Safran

06/07/18 / #20180155041

Turbine engine suspension device

A suspension device for suspending, for example, a turbine engine to a pylon, the device comprising a first unit interposed between a first lug and a second lug of a second unit, the first unit having a bore for passing an axle running through first and second bushings mounted respectively in said first and second lugs; and a clamping unit interacting with the axle. The device further comprising a third bushing mounted in the second lug and having radial centering means which interact with the complementary centering means of a head section of the axle; and a fourth axially slidably mounted bushing, biased axially by the clamping unit, and comprising radial centering means which interact with complementary centering means of the first bushing.. ... Safran

06/07/18 / #20180154427

Method for producing a pattern for lost pattern casting

A fabrication method for fabricating a pattern for lost pattern casting, comprising at least one insert (10), providing at least two pattern portions (12, 14), said at least two portions being made of a material that can be eliminated, and assembling said at least two pattern portions together around at least a portion of said at least one insert in sealed manner so as to make said pattern (16).. . ... Safran

05/31/18 / #20180149621

Method of non-destructive inspection of a weld bead

. . A non-destructive method for inspecting a weld bead (18) connecting together two parts (14, 16), a longitudinal direction (x) of the weld bead (18) extending along the interface between the two parts (14, 16), the method comprising providing an emitter (10) and a receiver (12) and taking at least one measurement of a signal emitted by the emitter (10) and received by the receiver (12) after passing through the weld bead (18), wherein the emitter (10) and the receiver (12) are positioned relative to the weld bead (18) in such a manner that the plane containing the axis (a1) of the emitter and the axis (a2) of the receiver is substantially parallel to the longitudinal direction (x).. . ... Safran

05/31/18 / #20180149544

Modular calibration rotor for a horizontal balancer

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. ... Safran

05/31/18 / #20180149365

Turbine engine cvc combustion chamber module comprising a pre-combustion chamber

A turbine engine combustion chamber module including at least one constant-volume combustion chamber. The module includes, upstream of the at least one constant-volume combustion chamber, a precombustion chamber capable of producing hot combustion gases that supply the at least one constant-volume combustion chamber so as to allow the ignition thereof.. ... Safran

05/31/18 / #20180149258

Method for generating a tooth profile of a wheel engaging with a roller pinion

Method for generating a tooth space profile (5) between two teeth (4) of a wheel (1) engaging with a roller (3) pinion (2) in a reference plane perpendicular to a central axis (x1) whose intersection with the reference plane defines a centre (c), comprising the step of defining a nominal tooth space with symmetrical first and second profiles so that the space is suitable for receiving a roller which comes into contact, without clearance, with the facing active portions of the first and second profiles at the level of a primitive diameter. The method of the invention comprises the steps of deforming the bottom portion (12) of the first profile so that the bottom point is brought nearer to the centre by an amount equal to a given radial clearance, and moving the first profile angularly through a given angular half-clearance around the centre to shift it away from the radial axis.. ... Safran

05/31/18 / #20180149034

Turbine ring assembly supported by flanges

A turbine ring assembly includes both a plurality of ring sectors made of ceramic matrix composite material forming a turbine ring and also a ring support structure having first and second annular flanges, each ring sector having first and second tabs, the tabs of each ring sector being held between the two annular flanges of the ring support structure. Each of the first and second tabs of the ring sectors has an annular groove. ... Safran

05/31/18 / #20180149033

Turbomachine case comprising an acoustic structure and an abradable element

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.. . ... Safran

05/31/18 / #20180148381

Porous ceramic material obtained by weaving and acoustic panel including such a material

The present disclosure concerns a porous body made of a ceramic-matrix composite material for an acoustic attenuation panel and a method of manufacturing the porous body. The porous body includes a plurality of interwoven ceramic fibers, a metal oxide matrix, and a plurality of channels interwoven with the ceramic fibers and interconnected together. ... Safran

05/31/18 / #20180148187

Acoustic attenuation structure with a plurality of attenuation degrees for a propulsion assembly of an aircraft

The present disclosure particularly relates to an acoustic attenuation structure for a propulsion assembly of an aircraft. The acoustic attenuation structure includes an acoustically reflective wall and a sandwich panel. ... Safran

05/31/18 / #20180147885

Aircraft wheel with a removable rim flange

An aircraft wheel rim includes a main portion and a removable portion. The main portion includes a hub and a disk extending between the hub and an annular outer portion that receives a tire and is shaped to form a rim one of its sides of the annular outer portion. ... Safran

05/24/18 / #20180142626

Butterfly valve for bleeding a compressor for an aircraft turbine engine

. . The invention relates to a butterfly valve (24) for bleeding a compressor for an aircraft turbine engine, the valve including a valve body (32), a butterfly (36), and a device (42) for controlling the angular position of the butterfly, the device (42) including a mobile actuation member (64) connected to the butterfly by a link (70), the member (64) being subjected: to a first adjustable pressure force (f1) applied by air from the compressor, the first force (f1) returning the butterfly (36) to a closed position; and to a second mechanical force (f2) returning the butterfly (36) to an open position, and coming from an aerodynamic torque (c) applied by the air to the butterfly (36), of which the axis of rotation (38) is off-centre relative to the butterfly.. . ... Safran

05/24/18 / #20180142572

A turbine ring assembly held by jaw coupling

A turbine ring assembly includes a plurality of ring sectors of ceramic matrix composite material forming a turbine ring and a ring support structure secured to a turbine casing and having two annular flanges, each ring sector having two tabs held between the two annular flanges. The ring support structure includes an annular retention band mounted on the turbine casing, the annular retention band including an annular web forming one of the flanges. ... Safran

05/24/18 / #20180142563

Annular wall of a combustion chamber with optimised cooling

An annular turbine engine combustion chamber wall including air admission orifices to create zones of steep temperature gradient, and cooling orifices to enable the air flowing on the cold side to penetrate to the hot side in order to form a film of cooling air along the annular wall, the annular wall being further includes, in the zones of steep temperature gradient, multi-perforation holes having respective bends of an angle α greater than 90°, the angle α being measured between an inlet axis ae and an outlet axis as of the multi-perforation hole, the outlet axis of the multi-perforation hole being inclined at an angle θ3 relative to the normal n to the annular wall through which the multi-perforation holes with bends are formed, in a “gyration” direction that is at most perpendicular to the axial flow direction d of the combustion gas.. . ... Safran

05/24/18 / #20180142562

Turbine engine comprising a lobed mixer having scoops

The invention relates to a lobed mixer (8) for arranging on the downstream end of a hood (4) separating the two co-axial streams, respectively inner and outer, the mixer (8) being shaped so as to have a least one peripheral succession of lobes (20, 21) which are generally radially oriented in relation to a longitudinal axis (ll′) of the mixer, each lobe (20, 21) forming a channel extending mainly along the longitudinal axis and comprising at least one peripheral succession of baffles (26) from the first stream to the second stream and/or from the second stream to the first stream, arranged on said lobes (20, 21).. . ... Safran

05/24/18 / #20180141666

Turbine engine having a three-phase transformer for powering electrical deicer elements

In an aeroengine comprising a gas turbine engine driving a propeller via a reduction gearbox, the propeller comprising a plurality of blades, each provided with one or more electrical deicer elements and being set into rotation by a propeller-carrying shaft passing through the gearbox, the propeller-carrying shaft having a fastener flange for fastening to the propeller, provision is made, in order to deliver the electrical power needed for powering said electrical deicer elements, for the aeroengine to include a rotary three-phase transformer set into rotation by the propeller-carrying shaft and comprising firstly a rotor mounted inside the propeller-carrying shaft and angularly secured thereto, and secondly a stator secured to a stationary portion of the aeroengine, the rotary three-phase transformer being arranged behind the propeller fastener flange.. . ... Safran

05/24/18 / #20180141440

System and method for dissipating electric energy regenerated by actuators

A system for dissipating regenerated electric energy produced by an electric actuator of an aircraft, the dissipating system including: a resistor; two switching arms, each switching arm being connected in series with the resistor, the two switching arms being connected together in parallel, each switching arm including two switches connected to one another in series, each switch including two terminals and a control grid, each switch being capable of being controlled by controlling the potential applied to the control grid thereof; and a measurement system capable of measuring the voltage at the terminals of each switch.. . ... Safran

05/17/18 / #20180138800

Dc-dc converter for controlling an aircraft fan inverter, and associated control method and fan

. . The invention relates to an electric dc-dc converter suitable for being supplied with power by a primary voltage source and for supplying control electronics of a three-phase inverter with power, said three-phase inverter being configured to control a fan of a ventilation system of an aircraft. The dc-dc converter is characterised in that it comprises a transformer (16), a primary circuit (12) comprising two loops forming a symmetrical assembly, at least one secondary circuit (14) comprising a secondary winding (ls), suitable for supplying, firstly, the inverter with an output voltage equal to twice the peak voltage at the terminals of the secondary winding (ls) and, secondly, a branch of the circuit suitable for supplying the inverter with an output voltage equal to the opposite of the peak voltage at the terminals of the secondary winding (ls), and in that the controllable transistors (m1, m2) are suitable for each being switched at zero voltage.. ... Safran

05/17/18 / #20180137325

Fingerprint or palmprint sensor

The invention relates to a skin print sensor (140) comprising, on a supporting substrate, a plurality of elementary acquisition cells (141), each of which includes: a reading node (sn); a first photoelectric or pyroelectric conversion element (pyr) having a first electrode that is connected to the reading node (sn) as well as a second electrode that is connected to a control node (cmd) of the cell; and a third electrode (el) that is connected to the reading node (sn), is coated with a dielectric layer and is designed to form a capacitance along with the skin of a user; in each cell of said sensor, the control node (cmd) is designed to receive a control signal that initiates reading of a value on the reading node (sn), said value representing the capacitance formed between the third electrode (el) and the user's skin.. . ... Safran

05/17/18 / #20180136059

Deformation measuring torque meter

A torque meter includes a casing and a part is configured to move in the casing in translation in a longitudinal direction under the effect of an axial thrust representative of the torque to be measured. The torque meter further includes a bearing surface connected to the casing via at least one of the ends thereof. ... Safran

05/17/18 / #20180135561

Testing method

The invention relates to the field of technical testing, and more particularly to a method of testing a machine, the method comprising: at least one step (s101) of determining a plurality of operating points for said machine, each operating point being defined by a duration and a specific value of at least one operating parameter of the machine; a step of calculating a set of distances between pairs of operating points; a step (s106) of selecting an optimum sequence of operating points by applying an algorithm for solving the traveling salesman problem to said set of distances between pairs of operating points; and a step (s107) of controlling the operation of said machine according to said optimum sequence of operating points.. . ... Safran

05/17/18 / #20180135462

Device for uncoupling first and second parts of a turbine engine

Device for uncoupling first and second parts of a turbine engine, the parts extending around an axis a, wherein the first part comprises an annular row of axial through-openings that extend around the axis a, and in that the second part comprises an annular row of axial fusible lugs that pass axially through the openings and include threaded portions onto which a nut having the axis a and intended for axially clamping the parts is screwed.. . ... Safran

05/17/18 / #20180135436

Blade having platforms including inserts

A fiber preform for a turbine engine blade and a single-piece blade suitable for being made by means of such a preform, a bladed wheel, and a turbine engine including such a blade; the fiber preform obtained by three-dimensional weaving comprises a first longitudinal segment (41) suitable for forming a blade root, a second longitudinal segment (42) extending the first longitudinal segment (41) upwards and suitable for forming an airfoil portion, a first transverse segment (51) extending transversely from the junction between the first and second longitudinal segments (41, 42), and suitable for forming a first platform; the first transverse segment (51) includes at least one non-interlinked portion comprising a top strip (51b) and a bottom strip (51a), and at least one insert (61) is arranged between the top and bottom strips (51b, 51a) of the non-interlinked portion of the first transverse segment (51).. . ... Safran

05/17/18 / #20180135433

Turbine for a turbine engine

A turbine for a turbine engine, the turbine comprising a rotor including blades the radially external periphery of which includes at least one first wiper radially extending outwards, sealing means radially extending about the blades and including a ring made of abradable material, with the radially external ends of the wipers cooperating with said ring made of abradable material so as to form a labyrinth-type seal, wherein said ring includes at least one first portion axially extending upstream of the first wiper and a second portion, different from the first portion, axially extending downstream of the first wiper, with the first portion and/or the second portion including a groove, wherein the first wiper has been inserted, with said groove being defined by the first portion and by the second portion.. . ... Safran

05/17/18 / #20180134402

Bipartite cradle with slide for turbomachine

A cradle for supporting an aircraft turbine engine, said cradle comprising an attachment interface for attaching a gas generator of the turbine engine. The cradle is produced in at least two portions comprising: an upper half-cradle, which is designed to be attached to a wing of the aircraft, a lower half-cradle, which is movable between a position in which it is connected to the upper half-cradle and a position in which it is disconnected from the upper half-cradle, and which comprises at least a portion of the attachment interface for attaching the gas generator, a guide configured for slidably guiding the lower half-cradle between the connected and disconnected positions thereof, and at least one lock for locking the lower half-cradle in the connected position thereof.. ... Safran

05/17/18 / #20180134377

Method of controlling an electrical taxiing system

A control method for controlling an electrical taxiing system adapted to moving an aircraft while it is taxiing, the method comprising the steps of: generating a ground speed setpoint for the aircraft; transforming the ground speed setpoint into an optimized speed setpoint presenting a curve as a function of time that has a predefined function comprising a plurality of linear portions, each having a slope that is a function of the ground speed setpoint; implementing a regulator loop having the optimized speed setpoint as its setpoint; and generating a command for the electrical taxiing system from an output of the regulator loop.. . ... Safran

05/17/18 / #20180133791

Method for knocking out a foundry core, and method for manufacturing by moulding including such a method

A method for knocking out a foundry core confined in an internal cavity in a part at the end of a casting operation, in particular a lost-wax casting operation, includes at least a primary chemical knocking-out step. During the primary chemical knowing-out step, the part is subjected to a chemical solution to dissolve the core, in a sealed enclosure. ... Safran

05/10/18 / #20180128289

Hydraulic circuit with controlled recirculation circuit

The invention relates to a hydraulic circuit (10) for an aircraft turboprop comprising a hydraulic fluid tank (16), a pump (14), a component (12) that is supplied with fluid pressurised by the pump (14) and that is selectively put into operation, and a fluid recirculation circuit (20) between the pump discharge (14) and the tank (16) characterised in that it comprises a valve (22) located in the recirculation circuit (20), that is capable of closing the recirculation circuit (20) when the component (12) is not in operation and is capable of opening the recirculation circuit (20) when the component is in operation.. . ... Safran

05/10/18 / #20180128183

Turbine engine with a pair of contrarotating propellers placed upstream of the gas generator

Engine comprising a propeller unit with a pair of contrarotating propellers (31, 32), a gas generator (5) supplying a power turbine (53), the pair of propellers being rotationally driven by the shaft (53a) of the power turbine via a speed reduction gearbox, the axis of rotation (xx) of the pair of propellers not being coaxial with that (yy) of the power turbine, the speed reduction gearbox comprising a differential gearset (7) and a first stage (6) comprising a simple gearset connecting the turbine shaft (53a) and the differential gearset (7), the engine air intake comprising an air intake duct (11), the air intake duct (11) being in the shape of a lobe adjacent to the assembly formed by the simple gearset and the differential gearset (7).. . ... Safran

05/10/18 / #20180128180

Support providing a complete connection between a turbine shaft and a degassing pipe of a turbojet

The invention relates to a support providing a complete connection between a degassing pipe (3) and a turbine shaft (2), said support including a plurality of outer contact spans (41a) intended to bear on the inner walls of the turbine shaft to secure the degassing pipe with respect thereto, characterized in that the different spans are each bordered by at least one elastomer insert (41g) which contributes to the protection of the turbine shaft during insertion of the support therein.. . ... Safran

05/10/18 / #20180128173

Turbine engine fan module including a turbine engine inlet cone de-icing system, and a de-icing method

The invention relates to an aviation turbine engine fan module including a de-icing system (10) for de-icing an inlet cone (1) and comprising a sheath (30) placed inside an inside space defined upstream by the inlet cone, said sheath comprising a first duct (38) having at least one hot air admission orifice (42), said first duct being configured to convey hot air from a bearing enclosure (22) of the engine towards a wall of the inlet cone in order to heat it from the inside, the sheath further comprising a second duct (40) having at least one outlet situated downstream from the admission orifice of the first duct, said second duct being configured to discharge air from the first duct towards the downstream end of the engine. The invention also provides a method of de-icing a turbine engine inlet cone.. ... Safran

05/10/18 / #20180128120

Connecting assembly for cooling the turbine of a turbine engine

A connecting assembly comprising an air distribution housing, between an air inlet passage and at least one duct connected with the housing by at least one bush mounted on an orifice of a wall of the housing. The wall of the housing and an inner wall of the bush are connected by a fillet having a radius which is maximum over an angular sector.. ... Safran

05/10/18 / #20180127084

Unducted-fan aircraft engine including a propeller comprising vanes with roots outside the nacelle and covered by detachable covers

The invention relates to an unducted-fan aircraft engine comprising a generally cylindrical nacelle through which a primary jet flows, the nacelle bearing a fan rotor comprising variable-pitch vanes (33) located radially outside the nacelle in order to be traversed by a secondary jet (31) flowing longitudinally around the nacelle. The rotor comprises a hub bearing variable-pitch vane supports each carrying one vane (33), each vane (33) comprising a blade extending from a root that is used to removably attach same to a base of the associated support (34). ... Safran

05/10/18 / #20180126591

A method of impregnating a fiber texture of hollow shape

A method of impregnating a fiber texture of hollow shape, the method including introducing a first suspension containing a first powder of solid particles of ceramic or carbon material into an inside volume defined by an inside face of a fiber texture of hollow shape placed in a mold, an outer face of the fiber texture being presented facing a wall of the mold; and using the action of centrifugal force to impregnate the fiber texture with the first suspension by causing the mold to rotate and varying the speed of rotation of the mold during the impregnation of the texture with the first suspension.. . ... Safran

05/10/18 / #20180126468

Method for machining an attachment flange of an aircraft turbomachine case

A method of machining an attachment flange of an aircraft turbomachine case, the method also including a system to machine the two opposite surfaces of the flange, and including a shape follower machining module, this module being designed to follow the shape of the flange and including a first structure equipped with a first machining tool, and a second structure equipped with a second machining tool, the flange fitting between the structures such that its two opposite surfaces are machined by tools, the module also including shape follower elements carried by the structures; and a device to drive movement of the machining module along a circumferential direction of the flange.. . ... Safran

05/03/18 / #20180119682

Device and method for regulating flow rate

A flow rate regulator device is provided, including an upstream chamber, a downstream chamber, a plurality of electrically conductive capillary ducts providing parallel fluid flow connections between the upstream chamber and the downstream chamber, first and second electrical terminals configured to be connected to an electric current source, and at least one electric switch configured to connect one or more of the capillary ducts selectively between the electrical terminals. A system for feeding propellant gas to a space electric thruster is also provided, including at least one such flow rate regulator device to regulate a propellant gas flow rate. ... Safran

05/03/18 / #20180119620

Flow limiter

The invention relates to a flow limiter which comprises a body (1) comprising a fluid intake (2) and a fluid outlet (3), in which body a pipe (5) for circulating the fluid is provided, comprising a series of chambers having different cross-sections, connected to the fluid intake as well as to the fluid outlet, the pipe being generally tubular, and the pipe having a bottom which has a regular curve so that the pipe does not have one or more areas that retain the fluid circulating in the pipe.. . ... Safran

05/03/18 / #20180119575

Turbine engine unit for lubricating a bearing holder

Provided, including an inter-turbine housing that includes a hub including a bearing bolder, a ferrule extending around and at a distance from the hub, at least one arm extending radially between the hub and the ferrule, and at least one lead-through for lubricating the bearing holder. The lead-through includes a first pipe having an end portion that can be screwed onto the hub so as to place the first pipe in fluid communication with the bearing holder, an intermediate portion secured to the end portion placed inside the arm when the end portion is screwed onto the hub, and a clamping portion secured to the end portion and rotatable by a clamping tool. ... Safran

05/03/18 / #20180119571

Turboshaft engine mountable in a reduction gearbox

A turboshaft engine for a helicopter, comprising a case inside which a gas generator and a turbine are accommodated, the turbine being mounted on a power shaft that extends along a longitudinal direction. The turboshaft engine further comprises means for removably mounting the power shaft into a reduction gearbox inside which at least one gear of a first reduction stage is accommodated. ... Safran

05/03/18 / #20180119551

Reinforcement for the leading edge of a turbine engine blade

A turbine engine blade comprising an aerodynamic surface that extends in a first direction between a leading edge and a trailing edge, and in a second direction substantially perpendicular to the first direction between a root and a tip of the blade, and a leading-edge reinforcement comprising a fin partly covering the aerodynamic surface of the blade, characterised in that the fin has a radially outer edge arranged in the vicinity of the tip of the blade and extending between the leading edge and the trailing edge, this radially outer edge comprising an upstream point fitting flush with the tip of the blade at the leading edge and a so-called downstream point separated from the tip of the blade.. . ... Safran

05/03/18 / #20180119550

Blade comprising lands with a stiffener

A preform for a turbine engine blade, the preform comprising a main fiber preform obtained by three-dimensional weaving and comprising a first longitudinal segment suitable for forming a blade root (21), a second longitudinal segment extending the first longitudinal segment upwards, and suitable for forming an airfoil portion (22), and a first transverse segment extending transversely from the junction between the first and second longitudinal segments, and suitable for forming a first platform (23), wherein the preform also includes at least one stiffener (40) fitted on the main fiber preform along at least a portion of the distal edge of the first transverse segment.. . ... Safran

05/03/18 / #20180118358

Assembly between an aircraft pylon and a turbine engine

An assembly between an aircraft structural pylon and an aircraft turbine engine is disclosed, with the assembly comprising a beam intended to be attached to the turbine engine and wherein a knuckle intended for the installation of a pad integral with the pylon is mounted, with the beam comprising suspension lugs each including a bore for the passage of a shaft intended to further go through a bore formed in the pylon to connect the beam with the pylon.. . ... Safran

05/03/18 / #20180117807

Method of fabricating a blade platform out of composite material with integrated gaskets for a turbine engine fan

There is provided a method of fabricating a blade platform out of composite material with integrated gaskets for a turbine engine fan, the platform including a base and a stiffener, the method including using three-dimensional weaving to make a single-piece fiber blank with a plurality of longitudinal yarn layers extending in a direction corresponding to a longitudinal direction of the base of the platform; shaping the fiber blank to form a fiber preform having a first portion forming a base preform and a second portion forming a stiffener preform; positioning platform gaskets at side margins of the first portion of the fiber preform forming a base preform; placing the fiber preform with the gaskets in an injection mold; injecting resin into the injection mold; compacting the assembly; heating the injection mold to solidify the resin; and unmolding the resulting platform.. . ... Safran

04/19/18 / #20180110149

Backplane electronic board and associated electronic control unit

The present invention concerns a backplane electronic board (20) having on inner face (142) suitable for bein g connected to electronic board connectors (12) and an outer face (143) suitable for being connected lo an outer connector (15), the backplane board (20) being characterised in that it has blind holes opening on ihe inner face (142) of some, and holes opening on the outer face (143) of same, the holes being suitable for receiving press-fit connection elements and forming therewith an electrical connection point.. . ... Safran

04/19/18 / #20180106823

Method for linking the shaft of a tachometer and an aircraft wheel

The invention relates to a method for linking an end (9) of a shaft (8) of a tachometer (7) positioned in a landing gear hub (1) and a wheel (2) mounted to rotate on said hub, the method comprising the step of equipping the wheel with a housing (14) suitable for receiving the end of the shaft of a tachometer and driving the shaft in rotation with the wheel, the housing comprising a bearing member (17) protruding inside the housing to be pushed back by the end of the shaft against an elastic member (18) to take up any play between the end of the shaft and the housing. The invention also relates to a bush ensuring application.. ... Safran

04/19/18 / #20180106603

System and method for contactless measurement of circular geometrical parameters of turbine engine components

A system for contactless measurement of circular geometrical parameters of a turbine engine component, comprising a contactless measurement module comprising a support, having a fixed position, for supporting said turbine engine component; an optical measurement device for transmitting a plurality of light beams onto at least said internal surface of said internal side wall, and for acquiring a plurality of reflections coming from said plurality of light beams, mechanically coupled to said support and comprising: an electronic conversion unit for converting a plurality of signals of said first optical sensor into a plurality of values of said plurality of circular geometrical parameters.. . ... Safran

04/19/18 / #20180105278

Turbine engine having horizontally offset axes

The invention relates to an aircraft propulsion assembly comprising a cradle receiving a turbine engine comprising at least one propeller having a longitudinal axis of rotation, a gas turbine engine having a longitudinal axis of rotation offset from the axis, and a reduction gear by means of which said propeller receives drive power from said engine, wherein the propeller and the gas turbine engine are designed such that axes and are offset from one another within said cradle at least by a given value in a transverse direction, the axis of the gas turbine engine being transversely closer to a proximal lateral side of the cradle than to an opposite distal lateral side of the cradle in order to create a lateral space between said engine and said distal lateral side of the cradle, thereby forming at least one region for installing equipments, components or accessories of said turbine engine.. . ... Safran

04/12/18 / #20180101825

System for pooling data relating to aircraft engines

A system for pooling observation data relating to aircraft engines includes a receiver adapted for recovering the observation data from distinct entities, a processor adapted for describing the observation data in a metric space by transforming them into measurable observation states, and a database adapted for storing therein the observation states.. . ... Safran

04/12/18 / #20180101635

System and method for product data management and 3d model visualization of electrical wiring design and specifications

A method for generating a three-dimensional (3d) computer model of an assembly that includes wiring routing, which includes creating a part data structure that defines a part in a virtual product management system. The part data structure includes a plurality of nodes that define at least 3d part design data, 3d wiring routing design data and wiring routing annotation data of the part. ... Safran

04/12/18 / #20180100562

Speed reducer comprising two intermediate transmission lines

The invention relates to a speed reducer having two intermediate transmission lines (4, 5) in particular for a turbine engine, comprising an input line (2) and an output line (3) driven by the input line by means of said intermediate lines, said intermediate lines being substantially in parallel with an axis (b) of rotation of the input line (2), said reducer further comprising means for distributing loads between the intermediate lines (4, 5), characterised in that said distribution means comprise a pinion (7) which is rigidly connected to a shaft (6) of the input line, the input line being movable in translation along said axis (b) and comprising two rings having helical external teeth (7a, 7b), the helices of which are oriented in opposite directions, each cooperating respectively with a pinion (12, 13) of an intermediate line (4, 5). The invention also relates to a turbine engine comprising such a speed reducer and to a method for distributing the loads in such a reducer.. ... Safran

04/12/18 / #20180100516

Vane comprising an assembled platform and blade

A blade portion of a vane is assembled to a platform portion by insertion into a cavity in the latter, in a lateral direction from an opening in the cavity, where the cavity possesses a back wall over at least a portion of its surface area. The bonding surface area between the portions of the vane is increased. ... Safran

04/12/18 / #20180100400

Blade equipped with platforms comprising a retaining leg

A preform for a turbine engine blade, the preform being obtained by three-dimensional weaving and comprising a first longitudinal segment (31) suitable for forming at least a portion of a blade root, a second longitudinal segment (32) extending the first longitudinal segment (31) upwards, and suitable for forming at least a portion of a stilt portion, a third longitudinal segment (33) extending the second longitudinal segment (32) upwards, and suitable for forming an airfoil portion, a first transverse segment (34) extending transversely from the junction between the second and third longitudinal segments (32, 33), and suitable for forming a first platform, and a first oblique segment (36) extending from the junction between the first and second longitudinal segments (31, 32) to the first transverse segment (34), and suitable for forming a retaining leg (26) for the first platform.. . ... Safran

04/05/18 / #20180096248

Methods for secure learning of parameters of a convolution neural network, and for secure input data classification

. . A method for secure learning of parameters of a convolution neural network, cnn, for data classification includes the implementation, by data processing of a first server, including receiving from a second server a base of already classified learning data, the learning data being homomorphically encrypted; learning in the encrypted domain, from the learning database, the parameters of a reference cnn including a non-linear layer (polynomial) operating an at least two-degree polynomial function approximating an activation function; a batch normalization layer before each non-linear layer (polynomial); and transmitting the learnt parameters to the second server, for decryption and use for classification.. . ... Safran

04/05/18 / #20180095158

Method for communication in an ad hoc network

A communication method in an ad hoc network, including a coordinating mobile communication device, referred to as the coordinator device, and a plurality of subordinate mobile communication devices, referred to as subordinate devices, each communication device including a wireless communication module and a positioning module using a transmission of first pulses modulated in accordance with a first ultra-wide band modulation in order to determine information representing a position of said communication device. The method includes, when it is implemented by a communication device: obtaining data to be transmitted; checking a transmission capability of the wireless communication module; when the wireless communication module does not allow to transmit the data, using the positioning module to transmit said data in the form of second pulses orthogonal to the first pulses.. ... Safran

04/05/18 / #20180094745

Fluid valve

A fluid valve includes a valve member located between a first cavity and a second cavity, and an actuator that includes a pilot. The valve member is moved by the balance between the pressure prevailing in the first cavity and the pressure prevailing in the second cavity. ... Safran

04/05/18 / #20180094698

Gearbox comprising an improved reduction gear

A gearbox for an aircraft turbine engine includes a drive shaft, a secondary drive shaft coupled to the drive shaft with a reduction mechanism, and output shafts, each of which is coupled to the drive shaft or to the secondary drive shaft with a set of ring and pinion gears, wherein the reduction mechanism includes an intermediate shaft, a first end coupled to the drive shaft with a first stage of gears and the second end coupled to the secondary drive shaft with a second stage of gears, and wherein the intermediate shaft is rotatably mounted in the gearbox about the main axis thereof which is oriented substantially perpendicular to the main axis of the drive shaft.. . ... Safran

04/05/18 / #20180094584

Cooling of the oil circuit of a turbine engine

The invention relates to a turbine engine, such as a turbojet engine or a turboprop engine of an aeroplane, including at least one oil circuit (8) and cooling means (16) for cooling the oil of said circuit (8), the cooling means (16) including a refrigerant circuit (17) provided with a first heat exchanger (18) capable of exchanging heat between the refrigerant and the air and forming a condenser, a second heat exchanger (19) capable of exchanging heat between the refrigerant and the oil of the oil circuit and forming an evaporator, a pressure reducer (20), a compressor (21) and first regulator means (31) capable of regulating the pressure of the refrigerant entering the first exchanger (18).. . ... Safran

04/05/18 / #20180094535

Gyratory-effect flow deflector of a discharge valve system, discharge valve system and turbine engine comprising such a discharge valve system

A discharge valve system of a bypass turbine engine compressor includes a flow deflector. The flow deflector has a wall provided with a plurality of ejection channels configured to discharge a discharge airflow from the compressor in a duct of the turbine engine in which an airflow circulates. ... Safran

04/05/18 / #20180094526

Rotor disk comprising a variable thickness web

A disk of a rotor including an annular radial web, a radially central hub located at the inner radial end of the web and a rim located at the outer radial end of the web, the web including an upstream face and a downstream face, and a plurality of orifices through which bolts pass for the attachment of at least one annular flange forming part of another adjacent rotor disk on either the upstream face or the downstream face of the web, or on both faces. The upstream face and/or the downstream face of the web includes a globally annular shaped indentation, with a bottom set back along the axial direction inwards into the web, and that extends radially outwards from the hub of the disk towards the rim, and that surrounds a radially inner part of each of the orifices of the web, at a distance.. ... Safran

04/05/18 / #20180093779

Translatable scoop for auxiliary power units air intake

An air intake assembly for an aircraft includes an auxiliary power unit intake that is defined by a skin of the aircraft. The auxiliary power unit intake is in fluid communication with an auxiliary power unit. ... Safran

03/29/18 / #20180087405

Turbine ring assembly that can be set while cold

. . . . A turbine ring assembly comprises a plurality of ring sectors made of ceramic matrix composite material forming a turbine ring and a ring support structure including first and second annular flanges. In section, each ring sector presents a k-shape having an annular base-forming portion with an inside face defining the inside face of the turbine ring and an outside face with first and second s-shaped tabs projecting therefrom. ... Safran

03/29/18 / #20180087401

Turbine ring assembly comprising a cooling air distribution element

A turbine ring assembly includes a plurality of ring segments and a ring support structure, the ring assembly further including, for each ring segment, a cooling distribution element fixed to the ring support structure and positioned in a first cavity delimited between the turbine ring and the ring support structure.. . ... Safran

03/29/18 / #20180087400

Turbine ring assembly comprising a cooling air distribution element

A turbine ring assembly includes a plurality of ring segments and a ring support structure, the ring assembly further including, for each ring segment, a cooling distribution element fixed to the ring support structure and positioned in a first cavity delimited between the turbine ring and the ring support structure.. . ... Safran

03/29/18 / #20180087399

Turbine ring assembly comprising a cooling air distribution element

A turbine ring assembly includes a plurality of ring segments and a ring support structure, the ring assembly further including, for each ring segment, a cooling distribution element fixed to the ring support structure and positioned in a first cavity delimited between the turbine ring and the ring support structure.. . ... Safran

03/29/18 / #20180087392

Turbomachine provided with a vane sector and a cooling circuit

A turbomachine including at least one stator vane sector (10) and a fluid distribution circuit (22), the stator vane sector comprising at least one vane (12), a fluid inlet (25a), a fluid outlet (25b), and a channel (24a) providing fluid flow connection between the fluid inlet and the fluid outlet while extending at least in part in the vane (12), the vane and the channel being adapted, to enable heat to be exchanged between a hot fluid passing through the channel and a stream of cold air passing through the vane sector, the fluid distribution circuit (22) presenting a feed pipe (22a) and a recovery pipe (22b), the fluid inlet (25a) being in fluid flow connection with a branch tapping (23a) of the feed pipe (22a) while the fluid outlet (25b) is in fluid flow connection with a branch tapping (23b) of the recovery pipe (22b).. . ... Safran

03/29/18 / #20180087389

Blisk comprising a hub having a recessed face on which a filling member is mounted

A fan blisk for a turbomachine, the blisk comprising a hub delimited by an upstream face and a downstream face in addition to an outer peripheral face and a revolving inner peripheral face delimiting an inner opening, the hub carrying blades each having a leading edge and a trailing edge, the hub and the blades forming a one-piece assembly. The upstream face and/or the downstream face is offset, being located along the axis of rotation (ax) between the leading edges and the trailing edges of the blades, the blisk (bladed disk) comprising a filling member mounted on the offset face, the filling member comprising an inner centring ferrule engaging in the inner face of the hub, a radial portion resting against the offset face and an outer ferrule extending the outer peripheral face of the hub.. ... Safran

03/29/18 / #20180087386

Fan blisk for aircraft turbomachine

The invention relates to a fan blink (28) for an aircraft turbomachine, comprising a hub, an annular platform (42) and fan blades (44) arranged projecting from the annual platform. It also comprises a mechanical discharge slit (52) from a trailing edge (49) of the fan blade, associated with at least one of the fan blades (44), for the case of ingestion of a bird, the slit being made on the annular platform (42) going around the trailing edge (49).. ... Safran

03/29/18 / #20180086440

Aircraft undercarriage fitted with a shimmy-attenuator device

An aircraft undercarriage having a sliding rod slidably mounted in a strut-leg, and a scissors linkage (4) having one branch (4a) hinged to the strut-leg or to a turning element of a control for steering the sliding rod mounted to turn in the strut-leg, and one branch (4b) hinged to the sliding rod, the branches being hinged to each other by a pivot pin (12), the undercarriage being fitted with a shimmy-attenuator device (10a, 10b) placed on the pivot pin of the shimmy-attenuator, the attenuator device including threshold resilient return means generating a force returning the branches towards a rest position, and at least damping means generating a damping force when the branches move axially along the pivot pin. The attenuator device comprises two modules (10a, 10b) placed on either side of the scissors linkage in order to co-operate with the pivot pin, each of the modules performing at least one of the damping function and the threshold resilient return function.. ... Safran

03/29/18 / #20180085856

Device for fabricating annular pieces by selectively melting powder, the device including a powder wiper

A device (10) for fabricating annular pieces by selectively melting powder, the device comprising an inner annular wall (12) and an outer annular wall (14) that are concentric and that define an annular powder deposition zone (a), and a powder dispenser (16) movable in rotation about the axis (x) of the inner and outer annular walls (12, 14), the powder dispenser (16) including a wiper (18) extending between the inner annular wall (12) and the outer annular wall (14) and forming an angle (α) with the radial direction (r) of the inner and outer annular walls (12, 14).. . ... Safran

03/22/18 / #20180080409

Thrust reverser for a nacelle of an aircraft turbojet engine

. . A thrust reverser for a nacelle of an aircraft turbojet engine is provided that includes a thrust reverser cowl movable along a direction parallel to a longitudinal axis of the nacelle and a variable section outlet nozzle extending from the thrust reverser cowl. The thrust reverser further includes an actuator, a first locking device to lock the thrust reverser cowl, a second locking device to lock the variable section outlet nozzle, and a reset lever. ... Safran

03/22/18 / #20180080408

Device with gratings for ejecting microjets in order to reduce the jet noise of a turbine engine

A device for reducing the jet noise of a turbine engine includes an outer cover having an inside wall defining the outside of an annular passage for passing a bypass stream from the engine, the wall of the outer cover including a plurality of microjet circuits, each including intakes for taking a gas stream from the bypass stream flow passage and leading to a single feed duct, which in turn opens out into the trailing edge of the outer cover via at least one ejection grating suitable for splitting the intake gas stream into a plurality of gas streams of right sections of dimensions less than a right section of the feed duct.. . ... Safran

03/22/18 / #20180080385

Assembly for passing an electrical harness into a turbine engine

The invention relates to an assembly for passing an electrical harness through a wall (28), comprising a tubular metal end piece (34) passing right through the wall (28) and housing the electrical harness, and a sleeve (38, 64, 66) made from heat-shrinkable material extending around an end part (40, 50) of the tubular end piece (34) and of the electrical harness. The assembly comprises means (42, 44, 46, 76) for extracting heat from the tubular end piece that are arranged on the side of the end piece (34) surrounded by the heat-shrinkable sleeve (38, 64, 66).. ... Safran

03/22/18 / #20180080345

Reinforced exhaust casing and manufacturing method

The invention relates to an exhaust casing (10) of a turbine engine for an aircraft which extends along an axis and which comprises a central hub (20), an annular outer shroud (30) and arms (40) which connect the central hub (20) to the outer shroud (30), at least one yoke (50) for attaching the exhaust casing (10) to the turbine engine being located on the outer shroud (30) and forming at least one lug (51) extending in a plane perpendicular to the axis and protruding toward the exterior of said outer shroud (30), characterized in that the outer shroud (30) comprises ribs (60) which form a constant excess of said outer shroud (30), which are located on either side of said at least one lug (51) of said at least one yoke (50), and which are aligned with said at least one lug (51).. . ... Safran

03/22/18 / #20180080344

A turbine ring assembly comprising a plurality of ring sectors made of ceramic matrix composite material

A turbine ring assembly includes a ring support structure and a plurality of ring sectors made of ceramic matrix composite material, each ring sector having a portion forming an annular base with an inside face defining the inside face of the turbine ring, and an outside face from which there extends a wall defining an internal housing in which a holder member made of metal material is present, the holder member being connected to the ring support structure and including a body from which elastically deformable holder elements extend inside the internal housing on either side of the body, the holder elements bearing against the wall.. . ... Safran

03/22/18 / #20180080343

A turbine ring assembly comprising a plurality of ring sectors made of ceramic matrix composite material

A turbine ring assembly includes a plurality of ring sectors made of ceramic matrix composite material, together with a ring support structure, each ring sector having a portion forming an annular base with an inner face defining the inner face of the turbine ring and an outer face from which there project at least two tab-forming portions, the ring support structure having at least two attachment tabs extending radially, the tabs of each ring sector gripping the attachment tabs of the ring support structure at least at the radially-inner ends of the attachment tabs.. . ... Safran

03/22/18 / #20180080337

Discharge flow duct of a turbine engine comprising a vbv grating with variable setting

A hub of an intermediate casing for a dual-flow turbine engine includes a discharge flow duct extending between an inner shroud and an outer shroud of the hub, the discharge flow duct leading into the secondary flow space through an outlet opening formed in the outer shroud, the outlet opening included in a discharge plane substantially tangential to the outer shroud; and discharge fins including an upstream fin and a downstream fin. An upstream acute angle between the discharge plane and the skeleton line of the upstream fin is smaller than a downstream acute angle between the discharge plane and the skeleton line of the downstream fin.. ... Safran

03/22/18 / #20180080332

Intermediate casing guide vane wheel

An ogv wheel comprising guide vanes made of polymer matrix composite material reinforced by fibers, each having a vane root and a vane tip, the vane roots being fastened on a hub of the wheel by first connection means and the vane tip being fastened on an outer shroud of the wheel by second connection means, the first connection means including a bearing plane secured to the hub and a first backing plate for securing to the hub, the vane roots being sandwiched between the bearing plane and the first backing plate, and the second connection means including a second backing plate for securing to the shroud, the vane tip being sandwiched between the shroud and the second backing plate.. . ... Safran

03/22/18 / #20180079517

Locking device for pivoting cowls of a thrust reverser

The present disclosure provides a device for locking a first cowling and a second cowling of a thrust reverser of an aircraft propulsion assembly. The cowlings are mounted such that each cowl pivots around a longitudinal axis between a closed flight position and an open maintenance position. ... Safran

03/15/18 / #20180077607

Method for authorising transmission requests

A method for maximising a quantity of enabled transmission requests from a set of transmission requests in a mobile wireless network comprising a plurality of mobile nodes. Said method is implemented by a master node and activated on reception by the master node of an event belonging to a predefined set of events comprising a first type of event involving a modification to the topology of the network. ... Safran

03/15/18 / #20180073398

Turbine ring assembly made from ceramic matrix composite material

A turbine ring assembly includes ring sectors made as a single piece of ceramic matrix composite material and being for mounting on a metal ring support structure, the ring support structure having two tabs extending radially towards a gas flow passage, each ring sector having a first portion forming an annular base with a radially inside face defining the inside face of the turbine ring and an outside face from which there extend two tab-forming portions, the ring sectors having a section that is substantially r shaped. The tabs of each ring sector fit axially over the tabs of the ring support structure with contact between the tabs of the ring support structure and the tabs of each ring sector when cold. ... Safran

03/15/18 / #20180073384

Aircraft turbine engine with planetary or epicyclic gear train

Aircraft turbine engine comprising a low-pressure spool that comprises a low-pressure shaft (24), means (44) for taking off power from said low-pressure shaft, and a fan (28) that is driven by said low-pressure shaft by means of a reduction gear (32), said reduction gear comprising at least one first element (50) that is connected to said low-pressure shaft for conjoint rotation, at least one second element (56) that is connected to said fan for conjoint rotation, and at least one third element (52) that is connected to a stator casing of the turbine engine, characterised in that said at least one third element is connected to said stator casing by disengageable connection means (60), and comprising at least one member that can move from a first position in which said at least one third element is fixedly connected to said stator casing into a second position in which said at least one third element is separated from said stator casing and is free to rotate about said longitudinal axis.. . ... Safran

03/15/18 / #20180073373

Ceramic core for a multl-cavity turbine blade

A ceramic core used for fabricating a hollow turbine blade for a turbine engine by using the lost-wax casting technique and shaped to constitute the cavities of the blade as a single element, includes, in order to feed the insides of these cavities jointly with cooling air, core portions that are to form first and second lateral cavities and that are connected to a core portion that is to form at least one central cavity, firstly in the core root via at least two ceramic junctions, and secondly at various heights up the core via a plurality of other ceramic junctions of positioning that defines the thickness of the internal partitions of the blade, while also ensuring additional cooling air for predetermined critical zones of the first and second lateral cavities.. . ... Safran

03/08/18 / #20180068172

Method of surveillance using a multi-sensor system

. . A method for the surveillance of a place using a network of image sensors connected to a biometric recognition device so arranged as to retrieve biometric features of persons from images supplied by the sensors and to compare the biometric features retrieved from images provided by distinct sensors in order to detect therefrom the presence of the same person according to a score of proximity between the biometric features, with the method comprising the steps of determining positional information and temporal information representing a split time between the two images and checking consistency between the newly determined positional and temporal information and the previously stored positional and temporal information.. . ... Safran

03/08/18 / #20180066608

Composite panel and aircraft turbojet engine nacelle comprising such a panel

The present disclosure relates to a composite panel having a sandwich structure formed by a central core having a primary cellular structure, for example, of the honeycomb type, sandwiched between two skins. The primary cellular structure includes an array of main cells. ... Safran

03/08/18 / #20180066581

Assembly for an aircraft turbine engine comprising a fan casing equipped with an acoustic liner incorporating a fan casing stiffener

The present invention relates to an assembly (20) for an aircraft turbine engine comprising a fan casing (14) having an inner surface (14b), at least one acoustic panel (26) fastened using fastening elements (48, 54) to the inner surface of the fan casing, and at least one circumferential stiffener (40) of the fan casing (14). According to the invention, the fastening elements (48, 54) connect the fan casing (14) to the stiffener (40) incorporated with the acoustic panel (26).. ... Safran

03/08/18 / #20180066545

Turbomachine test bench with active noise control

A test bench for turbomachine comprising: an installation zone for turbomachine; an active system for attenuating the noise emissions produced by the turbomachine. The active system includes an attenuation zone with emitters such as loudspeakers; a first microphone placed downstream of the turbomachine; and a second microphone placed downstream of the attenuation zone. ... Safran

03/08/18 / #20180066540

Intermediate casing for a turbomachine turbine

A turbine comprising an intermediate casing axially inserted between an upstream high pressure turbine casing and a downstream low pressure turbine casing and comprising an outer annular shroud from which an annular flange radially extends, characterized in that the downstream end of the high pressure turbine casing and the upstream end of the low pressure turbine casing are attached on the radial annular flange of the intermediate casing.. . ... Safran

03/08/18 / #20180066536

Compressor stage

The invention relates to the field of compressors, and specifically a compressor stage (100) comprising at least a casing (101) delimiting an air passage (2), a stator (102) comprising a plurality of guide vanes (103) arranged radially around a central axis (x) in the air passage (2), and a rotor (104) suitable for rotating about the central axis (x) relative to the stator (102) and comprising a plurality of blades (105) arranged radially around the central axis (x) in the air passage (2) downstream from the guide vanes (103). Each blade (105) of the rotor (104) extends from a blade root (105a) to a blade tip (105b) further away from the central axis (x) than the blade root (105a) and presents radial clearance (j) between the blade tip (105b) and the casing (101). ... Safran

03/08/18 / #20180066528

Turbine rotor with air separation ferrules for cooling of blade and disk coupling portions, for a turbomachine

A turbine rotor is fitted to a turbomachine and includes disks each containing a coupling portion with recesses each holding a root of a blade, and coupled to one another by a first annular ferrule attached to one of them close to the recesses, and second rotationally coupled ferrules, which are respectively coupled radially to the disks, which each consists of at least two semi-annular sectors, and which form with the associated disk a space which communicates with the recesses of the coupling portion of this latter disk. In addition, each first ferrule includes through-holes enabling air to enter this space, and then the recesses, intended to cool the coupling portion which couples its disk and the blade roots.. ... Safran

03/08/18 / #20180065730

A radial shaft device for controlling the pitch of fan blades of a turbine engine having an un-ducted fan

A device for controlling pitch of fan blades of a turbine engine including an un-ducted fan, the device including: at least one set of fan blades of adjustable pitch, the set being constrained to rotate with a rotary ring centered on a longitudinal axis and mechanically connected to a turbine rotor, each blade of the set being mounted on a blade root support that is pivotally mounted on the rotary ring; and at least one radial control shaft adjusting pitch of at least two adjacent blades of the set, the control shaft being constrained to rotate with the rotary ring and being configured to pivot about an axis of the shaft, being coupled to the blade root supports of the at least two blades of the set to adjust their pitch via a transmission system including eccentrics connected together by at least one connecting rod.. . ... Safran

03/08/18 / #20180065727

Aircraft propulsion unit comprising an unducted-fan turbine engine and an attachment pylon

A propulsion assembly for aircraft, the assembly including a turbojet having at least one unducted propulsion propeller; and an attachment pylon for attaching the turbojet to a structural element of the aircraft, the pylon being positioned on the turbojet upstream from the propeller and having an airfoil extending transversely between a leading edge and a trailing edge, the trailing edge of the airfoil of the pylon includes a cutout extending longitudinally over a fraction of the trailing edge facing at least a portion of the propeller, the cutout being configured to increase locally the distance between the trailing edge and the propeller, the cutout presenting an outline having a curved shape presenting at least two points of inflection.. . ... Safran

03/01/18 / #20180059037

Method of fabricating a reference blade for calibrating tomographic inspection, and a resulting reference blade

. . A method of fabricating a reference blade for calibrating non-destructive inspection by tomography of real blades of similar shapes and dimensions, including making a three-dimensional blank out of resin, creating housings in the thickness of the blank at predetermined locations, and introducing in each of the housings a cylinder including an artificial defect or a real defect in order to obtain the reference blade.. . ... Safran

03/01/18 / #20180058973

Method for detecting a fluid leak in a turbomachine and fluid distribution system

A method for detecting a high temperature fluid leak in a turbomachine. The turbomachine includes a source of high temperature pressurized fluid, at least one fluid distribution line suitable for distributing said high temperature fluid, and a turbomachine compartment wherein the distribution line is at least partially housed. ... Safran

03/01/18 / #20180058510

Method for connecting the rotor of an electric motor to an element that is to be driven

The invention relates to a method for connecting in rotation an output member (5) of an electric motor (1) and an element (2) that is to be driven in rotation, comprising the use of at least one fusible pin (11) that links the output member and the element that is to be driven, and that has at least one section that is prone to fail in shear when a torque transmitted by the fusible pin exceeds a predetermined threshold. The method comprises the step of interposing, between the pin and either the output member or the element that is to be driven, at least one elastic member (20) comprising a first travel with a first stiffness followed by a second travel with a second stiffness greater than the first stiffness.. ... Safran

03/01/18 / #20180058471

Inner shroud and orientable vane of an axial turbomachine compressor

An assembly for the compressor stator of a turbomachine. The assembly comprises: a shroud, in various instances an inner shroud, that is axially divided into two parts; a pocket formed in the shroud; a bearing located in the pocket; and an orientable vane pivotably mounted in the bearing about a pivot axis. ... Safran

03/01/18 / #20180058260

Turbine engine with an oil guiding device and method for disassembling the turbine engine

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. ... Safran








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