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Safran Aircraft Engines patents


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

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


 new patent  Method for high temperature forging of a preformed metal part, and shaping equipment suitable for forging

A forging method serving to use shaping tooling suitable for high temperature forging of a preformed metal part having angular twist undercuts (49) in its final shape, the method comprising placing the preformed metal part on a movable central insert (44) of the tooling and blocking it in the tooling... Safran Aircraft Engines

 new patent  Pitch-change system equipped with means for adjusting blade pitch and corresponding turbine engine

A system changes the pitch of blades of at least one turbine engine propeller provided with a plurality of blades. The system includes a link mechanism connected to the propeller blades at a first interface, and a control means acting on the link mechanism and having a body movable in... Safran Aircraft Engines

 new patent  Pitch change module for turbine engine and corresponding turbine engine

The invention relates to turbine engine module (1) including a case (9) rotating around a longitudinal axis (X) and carrying a propeller having a plurality of blades, a stationary case (15) comprising a cylindrical wall (16) extending between an inner wall (17) and an outer wall (18) of the rotating... Safran Aircraft Engines

 new patent  Pitch change system equipped with means for supplying fluid to a control means and corresponding turbine engine

A system is configured to change the pitch of blades of at least one turbine engine propeller provided with multiple blades. The system includes a control means acting on a connecting mechanism connected to the blades of the propeller. The control means includes a stationary body and a movable body... Safran Aircraft Engines

Method for manufacturing a turbomachine blade made of composite material

A method of fabricating a turbine engine blade out of composite material including fiber reinforcement densified by a matrix, the method including using multilayer weaving to make a first fiber that has a first portion forming a blade root preform and extended by a second portion, the second portion forming... Safran Aircraft Engines

Turbine engine air guide assembly with improved aerodynamic performance

A turbine engine assembly including an air flow guide assembly, including at least one guide vane and at least one structural arm, the vane and arm extending radially about an axis. The arm includes an upstream end portion having a guide vane profile and including a leading edge aligned with... Safran Aircraft Engines

System for assisting with the production or repair of a turbomachine

The invention relates to a method for assisting with the production or repair of a turbomachine. The method comprises a step (91) of displaying first production or repair information about the turbomachine on a portable display device. The method comprises a step (92) of blocking the display of second production... Safran Aircraft Engines

Guide assembly with optimised aerodynamic performance

The invention relates to a turbine engine air flow guide assembly including: a structural arm (30); and a guide vane (21) on the lower surface of the structural arm, comprising a leading edge (22), a trailing edge (23), and a camber line (24), said vane and arm extending radially about... Safran Aircraft Engines

Device for the individual adjustment of a plurality of variable-pitch radial stator vanes in a turbomachine

A device for adjusting the pitch of at least one annular row of stator vanes for a turbine engine module. The device includes a first control ring mounted to rotate freely about an axis of the turbine engine. The device also includes connecting rods for connecting the first control ring... Safran Aircraft Engines

Aircraft comprising a turbojet engine integrated into the rear fuselage comprising a fairing allowing the ejection of blades

The invention relates to an aircraft comprising a fuselage, flight control surfaces and a turbojet engine (20) integrated into the rear of said fuselage in the extension thereof, the turbojet engine (12) comprising two gas generators (22) that supply, via a common central duct (30), a power turbine (32) comprising... Safran Aircraft Engines

Flame-holder device

A flame-holder device for a reheat channel of a turbojet, the device including an arm in the form of a trough defining a cavity and a heat shield fastened in the cavity of the arm. The flame-holder device further includes a fastener plate including a first leg integrally formed with... Safran Aircraft Engines

Method of inspecting the thickness of a part of hollow shape

A thickness inspection method inspects the thickness of a part having a hollow shape by using tooling enabling a counter-shape to be molded that matches said hollow shape. The method includes putting the part into place on a support secured to the tooling, locking the part in place, and filling... Safran Aircraft Engines

Hall effect thruster and a space vehicle including such a thruster

A Hall effect thruster arranged inside a wall and including a magnetic circuit and an electric circuit including an anode, a first cathode, and a voltage source. The magnetic circuit and the electric circuit are arranged in such a manner as to generate magnetic and electric fields around the wall.... Safran Aircraft Engines

Corrosion protection plug for filling an attachment opening, and system including said plug

A plug for preventing corrosion of an attachment opening, includes a bottom surface including an opening for receiving a head of a tightening device; a top surface; and a substantially cylindrical side wall extending between the bottom surface and the top surface. The side wall includes a first side area,... Safran Aircraft Engines

Intermediate case for an aircraft turbomachine made from a single casting with a lubricant duct

The invention relates to an intermediate case (25) for a twin spool turbomachine for an aircraft, comprising a hub (26), an outer shell (23) and outlet guide vanes (24) installed at their ends on the hub and on the outer shell, and each of at least some of the outlet... Safran Aircraft Engines

Turbine engine with epicyclic reduction gear train

wherein the stator of the electrical apparatus is fixed to the stator housing by means of an annular member for apparatus support, the annular member comprising legs of an elongated shape that axially traverse the reduction gear, the annular member comprising at longitudinal extremities of the legs a first annular... Safran Aircraft Engines

Optimized aerodynamic profile for a turbine blade, in particular for a rotary wheel of the fourth stage of a turbine

When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first... Safran Aircraft Engines

Optimized aerodynamic profile for a turbine vane, in particular for a nozzle of the first stage of a turbine

When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first... Safran Aircraft Engines

Optimized aerodynamic profile for a turbine vane, in particular for a nozzle of the sixth stage of a turbine

When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first... Safran Aircraft Engines

Optimized aerodynamic profile for a turbine vane, in particular for a nozzle of the second stage of a turbine

When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first... Safran Aircraft Engines

Optimized aerodynamic profile for a turbine blade, in particular for a rotary wheel of the seventh stage of a turbine

When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first... Safran Aircraft Engines

Optimized aerodynamic profile for a turbine blade, in particular for a rotary wheel of the second stage of a turbine

When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first... Safran Aircraft Engines

Optimized aerodynamic profile for a turbine blade, in particular for a rotary wheel of the fifth stage of a turbine

When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first... Safran Aircraft Engines

Optimized aerodynamic profile for a turbine blade, in particular for a rotary wheel of the sixth stage of a turbine

When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first... Safran Aircraft Engines

Optimized aerodynamic profile for a turbine blade, in particular for a rotary wheel of the first stage of a turbine

When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first... Safran Aircraft Engines

Optimized aerodynamic profile for a turbine blade, in particular for a rotary wheel of the third stage of a turbine

When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first... Safran Aircraft Engines

Optimized aerodynamic profile for a turbine vane, in particular for a nozzle of the fourth stage of a turbine

When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first... Safran Aircraft Engines

Optimized aerodynamic profile for an arm of a structural casing of a turbine, and structural casing having such an arm

When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first... Safran Aircraft Engines

Nut for axially locking a bearing ring in a turbomachine

A nut for a turbine engine, in particular for axially locking a bearing race. The nut comprises a thread for screwing onto a part of the turbine engine, and a lock for ensuring the nut cannot rotate relative to the engine part. The nut further comprises at least one dynamic... Safran Aircraft Engines

Assembly for controlling variable pitch vanes in a turbine engine

An assembly, in particular for controlling variable pitch vanes in a turbine engine, comprising an actuating ring surrounding a casing of the turbine engine and connected by rods to variable pitch vanes, in addition to a driving means for rotating the actuating ring around the casing. The assembly includes a... Safran Aircraft Engines

Optimized aerodynamic profile for an arm of a structural casing of a turbine, and structural casing having such an arm

When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first... Safran Aircraft Engines

Method, system and computer program for learning phase of an acoustic or vibratory analysis of a machine

A method of analysis of the state of operation of a machine including a learning step supplementing a reference database with one or more thresholds for one or more indicators calculated on the basis of signals delivered by a sensor associated with the machine, the learning step including the following... Safran Aircraft Engines

Turboprop

A turboprop including a propeller including a blade extending in a direction, which also includes a root, a leading edge, a trailing edge, and a wing tip, and an inner air stream channel, wherein the inner air stream channel includes an inlet located at the root of the blade and... Safran Aircraft Engines

Fitted platform for a turbine engine fan, and a fabricating it

The invention provides a fitted platform (1) for positioning between two adjacent blades of an aviation turbine engine fan, said platform comprising a flow passage wall (10) made of composite material having a central portion (16) and first and second margins (18) each extending in a longitudinal direction of said... Safran Aircraft Engines

01/11/18 / #20180010478

System for controlling variable pitch blades for a turbine engine

The invention relates to a system for controlling variable pitch blades for a turbine engine, comprising an annular row of variable pitch blades extending about an axis (A) and each comprising a blade connected at the radially outer end thereof to a pivot (20) that defines a substantially radial axis... Safran Aircraft Engines

01/11/18 / #20180010613

Fan blade

A blade including at least one web and a vane having a leading edge and a trailing edge, wherein, for at least one aerofoil of the vane in the vicinity of the web, a maximum sweep angle associated with a position along a chord of the aerofoil extending from the... Safran Aircraft Engines

01/11/18 / #20180010799

Fuel injection system for aircraft turbomachine, comprising a variable section air through duct

An assembly includes an injection system and an injector for an aircraft turbomachine combustion chamber. The system includes an aerodynamic bowl including a first end widening toward the downstream end and centred on a central axis of the injection system, this also including a central body along which a film... Safran Aircraft Engines

01/04/18 / #20180001383

Method for producing a turbomachine part by means of a laser process

the trajectory of the nozzle is modified on the basis of a deviation threshold between said distances.... Safran Aircraft Engines

01/04/18 / #20180003193

Variable pitch vane control ring bush retention foil and turbojet containing same

A flexible metal foil can be fixed on the inside part of a variable pitch vane control ring of a turbojet compressor, so as to close all through holes in which lever pins and their surrounding bushes are housed. As a result, the foil can retain the shank of the... Safran Aircraft Engines

01/04/18 / #20180003385

Sealing device between an injection system and a fuel injection nozzle of an aircraft turbine engine

An arrangement for an aircraft turbine engine combustion chamber including an injection system and a fuel injector is provided. The injection system includes an injector nozzle guide, the inner surface of which delimits an opening for centering the nozzle, which includes an outer casing. The arrangement further includes a sealing... Safran Aircraft Engines

01/04/18 / #20180003616

Peeling test device

A device and a method for peeling tests, in order to test the peeling resistance of coupons each formed of a support and an adhesive. The device comprises: (i) a frame comprising rollers with parallel axes designed to maintain the coupon supported while guiding movement of the latter, (ii) a... Safran Aircraft Engines

12/28/17 / #20170369153

Turbomachine with multi-diameter propeller

A turbomachine including at least two unducted propellers, one of which is an upstream propeller and one a downstream propeller, the upstream propeller including a plurality of blades, at least one first blade of which has a different length from that of a second blade.... Safran Aircraft Engines

12/28/17 / #20170369382

Method of fabricating a fiber preform filled with refractory ceramic particles

A method of fabricating a fiber preform filled with refractory ceramic particles, includes placing a fiber texture including refractory ceramic fibers in a mold cavity; injecting a slip including a powder of refractory ceramic particles present in a liquid medium, the slip being injected into the pores of the fiber... Safran Aircraft Engines

12/28/17 / #20170370325

Deployable grille with fins for aircraft turbine engine thrust-reversal system

A deployable grille with fins for a thrust-reversal system for an aircraft turbine engine. The grille can adopt a rest position and a deployed, active position wherein the fins are axially spaced further apart than in the rest position. At least between two fins, the grille includes resilient return device... Safran Aircraft Engines

12/28/17 / #20170370859

Phantom intended for use in quality control of tomographic images

A phantom for use in quality control of tomographic images, the phantom including a cylindrical plate made of a uniform material having a density d1, with two cylinders being inserted in the plate, the cylinders being made out of uniform materials having different densities d2, d3, the density of one... Safran Aircraft Engines

12/28/17 / #20170371327

State controller for a system driven by a command

A state monitor for monitoring the state of a system and including a calculator and a memory; the system being controlled by a command defining a plurality of modes of operation of the system, each mode of operation corresponding to applying a command of constant value; the memory containing a... Safran Aircraft Engines

12/21/17 / #20170362946

Aerodynamic link in part of a turbine engine

The invention relates to part of a turbine engine comprising two arms passing through a stream of the turbine engine, wherein each arm comprises an outer surface and an aerodynamic linking device. The aerodynamic linking device comprises fairings extending between the two arms, compressible interface means interposed between the fairings... Safran Aircraft Engines

12/21/17 / #20170362950

Turbomachine blade fitted with an elastomer gasket

A turbomachine blade (10) comprising a body (11) and an elastomer gasket (12) fastened to said body (11).... Safran Aircraft Engines

12/21/17 / #20170363290

Air intake ring for a turbomachine combustion chamber injection system and atomizing fuel in an injection system comprising said air intake ring

A system for improving fuel-air mixing inside an injection system of a turbomachine combustion chamber. An air intake ring has an annular deflection wall, or venturi, having an internal profile provided with a discontinuity inducing an increase in the radius (φ) of the internal profile downstream of the discontinuity. A... Safran Aircraft Engines

12/14/17 / #20170355117

Device and a fabricating a part by injection molding

An injection molding device for fabricating a part, the device including an injection mold, the mold being formed of a support and a countermold that are distinct and that define between them a mold cavity presenting a first shape; and at least one injection device for injecting a fluid material... Safran Aircraft Engines

12/14/17 / #20170356306

Device for recovering lubrication oil ejected by centrifugal effect in a turbine engine

A device for recovering oil injected by centrifugal effect in a turbine engine, comprising a substantially circular ring around an axis, the ring comprising a first part forming a basin surrounding the axis and having an opening turned radially inward, so as to recover the oil injected radially across from... Safran Aircraft Engines

12/07/17 / #20170348808

Method for repairing a fan casing

A method for repairing a fan casing in which the inner surface is damaged, includes attaching a reinforcement element to the fan casing, the reinforcement element being attached to the outer surface of the fan casing opposite the damage.... Safran Aircraft Engines

12/07/17 / #20170350845

Assembly for capacitive measurement of the amount of gas in a fluid flow

an insulating sheath (6), an upstream ground (2), a measurement electrode (3), a guard electrode (7), and a downstream ground (4) arranged in succession in said insulating sheath (6) and each presenting an identical internal section defining an internal flow duct for a two-phase flow from the upstream ground (2)... Safran Aircraft Engines

12/07/17 / #20170352205

Validation tool for an aircraft engine monitoring system

A tool for validation of a system for monitoring at least one piece of equipment in an aircraft engine, also comprising a computer configured to: collect observation data related to the equipment, calculate a current value of at least one quality indicator on a current quantity of observation data, estimate... Safran Aircraft Engines

11/30/17 / #20170341263

Method for manufacturing a refractory part made of composite material

A method of fabricating a part out of composite material, includes forming a fiber texture from refractory fibers; placing the texture in a mold having an impregnation chamber including in its bottom portion a part made of porous material, the impregnation chamber being closed in its top portion by a... Safran Aircraft Engines

11/30/17 / #20170341732

An assembly of two parts, one of which is made of composite material, the parts being assembled together by a mechanical anchor element

An assembly of two parts, one of the parts being made of composite material with fiber reinforcement obtained from a fiber preform made by three-dimensional weaving and densified with a matrix, the assembly including a mechanical anchor element secured to one of the parts and inserted inside the other part.... Safran Aircraft Engines

11/30/17 / #20170342524

A titanium-based intermetallic alloy

A titanium-based intermetallic alloy includes, in atomic percent, 16% to 26% Al, 18% to 28% Nb, 0% to 3% of a metal M selected from Mo, W, Hf, and V, 0.1% to 2% of Si, 0% to 2% of Ta, 1% to 4% of Zr, with the condition Fe+Ni≦400 ppm,... Safran Aircraft Engines

11/30/17 / #20170343033

System for repairing a fastener equipping a reactor wall

An attachment system intended to equip a wall (17), the system including a nut intended to receive a screw (31) of which the orientation is normal to the wall (17), the screw (31) passing through an element such as an outer panel (32) in order to attach the element to... Safran Aircraft Engines

11/23/17 / #20170334152

Mold assembly for resin transfer molding

A mold assembly includes an injection mold configured to receive a woven preform. The preform has a principal direction with at least one edge extending substantially along the principal direction. The mold assembly is configured to allow the impregnation of the preform with a resin injected into the mold. The... Safran Aircraft Engines

11/23/17 / #20170334791

Method for manufacturing part made of composite material

A method of fabricating a part out of composite material, includes forming a fiber texture from refractory fibers; impregnating the fiber texture for a first time with a first slip containing first refractory particles; eliminating the liquid phase from the first slip so as to leave within the texture only... Safran Aircraft Engines

11/23/17 / #20170335435

A turbine engine part including a titanium-based alloy

The present invention relates to a turbine engine part including a titanium-based alloy presenting a high level of work hardening, a high breaking load, and good ductility.... Safran Aircraft Engines

11/23/17 / #20170335696

Method for manufacturing a part coated with a protective coating

A method for manufacturing a part coated with a protective coating includes: forming a protective coating across all or part of the surface of a part, wherein the part includes a refractory alloy including a niobium matrix containing metal silicide inclusions, wherein the protective coating is formed by a pack... Safran Aircraft Engines

11/23/17 / #20170335709

Rotor vane with active clearance control, rotary assembly and operating method thereof

The invention relates to a motor vane for a turbine engine, comprising a body (170) locally defining a blade provided at the radially outer end with a root (33), characterised in that it also comprises at least one sealing element (39) extending beyond the radially outer end of the root... Safran Aircraft Engines

11/23/17 / #20170335766

Arrangements for drawing in air and trapping foreign bodies in an aircraft propulsion assembly

The invention relates to an arrangement, in a pod of an aircraft propulsion assembly, for drawing in air and trapping foreign bodies. Said arrangement includes a main air inlet duct (11) separating into, on one hand, a channel (13) for leading air to a compressor and, on the other hand,... Safran Aircraft Engines

Patent Packs
11/23/17 / #20170335769

Cooling device for a turbomachine supplied by a discharge circuit

wherein the nozzle is connected to said bleed system.... Safran Aircraft Engines

11/16/17 / #20170326757

Composite blade comprising a platform equipped with a stiffener

A fiber preform for a turbine engine blade and also a single-piece blade suitable for being formed using such a preform, a rotor wheel, and a turbine engine including such a blade, the fiber preform being obtained by three-dimensional weaving and comprising a first longitudinal segment suitable for forming a... Safran Aircraft Engines

11/16/17 / #20170328222

Method for manufacturing a turbine engine blade including a tip provided with a complex well

A method for manufacturing a turbine engine blade (25) comprising a pressure side and a suction side separated from one another by an inner space for the circulation of cooling air, the blade (25) comprising a tip (S) with a closing wall (29) joining the pressure side and suction side... Safran Aircraft Engines

11/16/17 / #20170328225

Method for friction-welding a blade to a turbomachine vane, including a surfacing process

According to the invention, a blade is friction-welded to a rotor disk of a turbomachine, the disk comprising a projecting block having an outer surface to which the blade is to be welded. To this end: a surfacing process is carried out on at least a part of the periphery... Safran Aircraft Engines

11/16/17 / #20170328227

Turbine assembly of an aircraft turbine engine

The present invention relates to a turbine assembly (10) of a turbine engine (1), comprising at least: a first bladed rotor (12), a bladed stator (13) and a second bladed rotor (14) arranged in series, the rotors (12, 14) being mounted on a shaft (2); a sealing plate (20) extending... Safran Aircraft Engines

11/16/17 / #20170328229

Turbine blade having an end cap

The invention relates to a turbine blade (1) of a turbine engine including an upper surface (11), a lower surface (12), a leading edge (13), a trailing edge (14), and a squealer tip (2) at the top thereof, wherein said squealer tip (2) is defined by a rim (2a) and... Safran Aircraft Engines

11/16/17 / #20170328379

Vane for turbomachinery, such as an aircraft turbojet or turbofan engine or an aircraft turboprop engine

A vane for turbomachinery, such as, for example, an aircraft turbojet or turbofan engine, or an aircraft turboprop engine. The vane includes: (i) a first deicing fluid flow circuit inside the vane; (ii) a second deicing fluid flow circuit inside the vane; and (iii) a selector for directing the majority... Safran Aircraft Engines

11/16/17 / #20170328393

A holder device for being present at the surface of a part made of composite material

A holder device for being present at the surface of a first part made of composite material in order to enable a second part to be held to the first part, the holder device including a body made of composite material including a fiber structure and a matrix present in... Safran Aircraft Engines

11/16/17 / #20170328404

Plain self-centering bearing

The present disclosure relates to a mechanical assembly of two mechanical parts rotatable relative to each other and enabling a self-centering fluid bearing to be obtained; it comprises a first part provided with a cylindrical cavity, a second part (34) having at least one cylindrical portion engaged in the cylindrical... Safran Aircraft Engines

11/16/17 / #20170329317

Method of manufacturing parts based on analysis of statistical indicators in a situation of diminished control

The invention pertains to a method of manufacturing a population of parts produced with a manufacturing device, based on the analysis of at least one statistical indicator representative of a characteristic dimension of the parts, according to which: a) a sample comprising a number n of parts is collected from... Safran Aircraft Engines

11/16/17 / #20170329744

Method for producing mechanical devices comprising several assembled identical parts

The invention relates to a method for producing a plurality of mechanical devices, in which each mechanical device comprises a defined number N of identical parts to be assembled, the parts to be assembled having been produced according to a set of specifications including at least one compliance specification, the... Safran Aircraft Engines

11/09/17 / #20170320174

Method for producing a turbine engine part

The production method comprises the steps for producing a preform by selective melting, the preform comprising an assembly surface to be brazed to the part to be repaired and containing a brazing material, and then assembling the preform to the turbine engine part by diffusion brazing. The thermal amplitude of... Safran Aircraft Engines

11/09/17 / #20170321303

A fabricating three-dimensional parts out of an alloy of aluminum and titanium

A method of fabricating a sintered three-dimensional part, the method including: preparing an injection composition including a binder and a powder of a titanium-based alloy including aluminum and/or chromium; injecting the composition into a cavity of a mold to obtain a blank; eliminating the binder present in the blank; a... Safran Aircraft Engines

11/09/17 / #20170321604

Device for de-icing a splitter nose of an aviation turbine engine

A device for de-icing a splitter nose of an aviation turbine engine, the device including a splitter nose having an outer annular wall defining the inside of the bypass stream flow channel and an inner annular wall defining an inlet of the core stream flow channel, and an inner shroud... Safran Aircraft Engines

11/02/17 / #20170312868

Method for repairing an upstream rail of a turbine engine turbine casing

A method for repairing an upstream rail of a turbine engine turbine casing, the casing including a casing body extending along a longitudinal axis, the upstream rail including: a base including a radial surface, extending substantially radially from the casing body; a plate including an upper surface, extending substantially along... Safran Aircraft Engines

Patent Packs
11/02/17 / #20170312998

Method for checking the position of a preform in a mould

The invention relates to a method for manufacturing a turbine engine blade from a preform (10) of composite material polymerised in a mould comprising a lower part (16) and an upper part, comprising at least one closure step, during which the upper part of said mould is placed on the... Safran Aircraft Engines

11/02/17 / #20170313403

Propeller ring comprising radial housings with an ovoid cross-section

The invention relates to a propeller ring (10) of a turbomachine (1), with variable-pitch blades (P), the propeller ring (10) comprising a substantially coaxial annular body (11) with a main axis (A) and a plurality of radial housings (12) uniformly distributed around the main axis (A), each radial housing (12)... Safran Aircraft Engines

11/02/17 / #20170313431

Aircraft propulsion assembly with a filtered cradle

The invention provides an aircraft propulsion assembly comprising a gas generator coupled by a coupling mechanism to a thrust generator having a structural torque transmission gearbox, and a rigid cradle rigidly supporting firstly the thrust generator in a first suspension plane and secondly the gas generator in distinct second and... Safran Aircraft Engines

11/02/17 / #20170314465

Air circulation device for a turbomachine comprising a hot air bypass system to a heat exchanger

The main purpose of the invention is an air circulation device (1) for a turbomachine (10), comprising an air conveyance circuit (2, 4b, 9, 4a, 3) adapted to bring hot bleed air (A1) from the turbomachine (10) to a part to be heated (38), comprising a first segment fixed in... Safran Aircraft Engines

11/02/17 / #20170314473

Regulation of the oil flow in a cooling circuit of a turbomachine

A turbomachine including a turbine shaft supported by at least one bearing, at least one enclosure, housing the bearing of the turbine shaft, an oil cooling circuit of the enclosure including at least one jet configured to inject oil from the cooling circuit into the enclosure, and a regulator configured... Safran Aircraft Engines

11/02/17 / #20170315021

Method and device for monitoring an aircraft engine vane wheel via balance position measurement

A method for monitoring an aircraft engine vane wheel (22), which includes: acquiring at least one time signal relative to moments when the vane wheel blades (23) pass in front of a sensor (21); determining a common flight phase of the aircraft; for each flight in a series of flights... Safran Aircraft Engines

10/26/17 / #20170306773

Simplified pitch actuation system for a turbine engine propeller

Pitch actuation system for a turbine engine propeller, comprising an actuator, a movable part of which is designed to be connected to blades of the propeller so as to rotate said blades relative to blade pitch-setting axes, characterised in that the actuator is an electromechanical actuator and comprises first electrical... Safran Aircraft Engines

10/26/17 / #20170307511

Peeling test coupon

A coupon suitable for peeling tests, derived from a vane and comprising: (i) a portion of blade that comprises a frontside surface, a backside surface and a leading edge and/or trailing edge and (ii) a vane reinforcement that covers and is glued to at least a part of the frontside... Safran Aircraft Engines

10/19/17 / #20170297241

Method for demoulding a composite material with an organic matrix

An injection tooling is configured to inject a polymer resin into a fiber preform for fabricating a part in the form of a body of revolution out of composite material, the part having an internal cavity with back-draft. In order to enable the part to be unmolded after the polymer... Safran Aircraft Engines

10/19/17 / #20170298741

Stator of an aircraft turbine engine

A stator of an aircraft turbine engine, comprising an annular row of fixed vanes and an annular row of arms, wherein the trailing edges of the fixed vanes are positioned substantially in a first transverse plane that is positioned downstream of a second transverse plane that passes substantially through the... Safran Aircraft Engines

10/19/17 / #20170298746

Turbine engine guide vane

The present invention relates to a turbine engine guide (23) vane (25), with a height (H) extending between a vane root (26) and a vane tip (27) along a radial direction (Z), said vane (25) comprising a succession of five bulge portions along a tangential direction (Y) perpendicular to the... Safran Aircraft Engines

10/19/17 / #20170298749

Machining process for multi-vane nozzle

The present invention relates to a method for machine finishing the shape of a blank casting for a multi-vane, in particular bi-vane, nozzle of a turbine engine, comprising a first vane and a second vane extending substantially in a radial direction between two walls that are radially inner and radially... Safran Aircraft Engines

10/19/17 / #20170298750

Vane with spoiler

Relates to a vane for a turbomachine. The vane (12′) has a blade (13′) and a root (18′) to be engaged in an axial groove in a disc of the turbomachine. The upstream end (450′) of the root is connected to a radially internal end (430′) of the leading edge... Safran Aircraft Engines

10/19/17 / #20170298775

Assembly of two parts comprising a removable centring seat for an aircraft turbine engine

A turbine engine for an aircraft which includes, in general, at least one assembly made up of a first part wherein a second part is attached with an attachment device including a milled head applied to the first part and a body engaging with the second part in order to... Safran Aircraft Engines

10/19/17 / #20170299192

Turbomachine combustion chamber

The invention relates to a combustion chamber for a turbomachine, such as an aircraft turbojet engine or turboprop engine, comprising an internal annular shroud and an external annular shroud which at their upstream ends are connected by an annular chamber end wall (48), said chamber comprising deflectors (50) mounted upstream... Safran Aircraft Engines

10/19/17 / #20170300612

Method for modeling a blade of a non-ducted propeller

(EN) The present invention relates to a method for modeling at least one portion of a blade (2) of a non-ducted propeller (1), wherein the blade portion (2) is offset (3). The method is characterized in that it comprises the implementation of the steps of: (a) Parametrizing an at least... Safran Aircraft Engines

10/12/17 / #20170291713

Turbine engline, such as for example an aircraft turbojet engine or a turboprop engine

The invention relates to a turbine engine provided with an element (3), comprising a wall (11) and at least one load-bearing member (17) extending substantially perpendicularly relative to the wall (11), with said member (17) being intended to be attached onto a mounting (18) used for the attachment thereof onto... Safran Aircraft Engines

10/12/17 / #20170292526

Sealing system and turbopump comprising such a system

A sealing system for at least one floatingly mounted ring in a support for a rotary shaft rotatable about an axis directed along a longitudinal direction provides dynamic sealing between the shaft and the support. The system includes a coupling part interposed between the ring and the support, whereby the... Safran Aircraft Engines

10/12/17 / #20170292795

Panel for heat exchange and improved noise reduction for a turbomachine

A heat exchange and noise reduction panel the panel for an aircraft comprising: an external surface intended to be swept by an airflow and from which fins extend along a first and a second main predetermined direction; cavities forming Helmholtz resonators, linked to the first ends of channels for the... Safran Aircraft Engines

10/05/17 / #20170282311

Optimized for crimping attachment of an abradable piece support to a radially inner wall of a vane sector of a turbomachine

A method for attaching an abradable piece support by crimping to the radially inner wall of a vane sector of a turbomachine, comprises deforming opposite rims of the radially inner wall on opposite free axial ends of the abradable piece support respectively, jointly, by means of two pressure blocks (40A,... Safran Aircraft Engines

10/05/17 / #20170283032

Aircraft including a wing with improved acoustic treatment

An aircraft having a wing and an aeroengine having a longitudinal main axis M and including a ducted nacelle with at least one fan, the wing including an acoustic treatment surface on a bottom portion of its outer shell on either side of the main longitudinal axis M and over... Safran Aircraft Engines

10/05/17 / #20170283036

Propeller pitch control system

By means of the variable speed drive (70), the speed of rotation of the outlet member of the transmission is a predetermined function of the speeds of rotation not only of the propeller shaft, but also of the control member.... Safran Aircraft Engines

10/05/17 / #20170284205

Variable pitch bladed disc

A variable-pitch bladed disc including a plurality of blades, each at a variable pitch in relation to a rotation axis of the blade and each having a root, the plurality of blades including at least one first blade and at least one second blade, a plurality of rotor connecting shafts,... Safran Aircraft Engines

10/05/17 / #20170284306

Aircraft turbine engine comprising a discharge device

Aircraft turbine engine (10), comprising at least one first compressor, an annular combustion chamber (70) and at least one first turbine (46), which define a first flow duct (22) for a primary flow, characterised in that it comprises, between said combustion chamber (70) and said first turbine (46), a device... Safran Aircraft Engines

10/05/17 / #20170284408

Supply of air to an air-conditioning circuit of an aircraft cabin

Aircraft turboprop engine (110), comprising at least one low-pressure body (12) and one high-pressure body (14), the low-pressure body driving a thrust propeller by means of a gearbox (16), the turboprop engine further comprising means for supplying air to an air-conditioning circuit (36) of an aircraft cabin, said supply means... Safran Aircraft Engines

10/05/17 / #20170284417

Output director vane for an aircraft turbine engine, with an improved lubricant cooling function using a heat conduction matrix housed in an inner duct of the vane

A guide vane for a dual flow aircraft turbine engine, the aerodynamic part of the vane including an inner duct for lubricant cooling extending in a main direction and being partly bounded by a pressure side wall and a suction side wall of the vane. A heat conduction matrix is... Safran Aircraft Engines

10/05/17 / #20170284889

Method for inspecting a connection seal between two parts

A method for checking a connection seal between two elements of a part, includes dipping the part to be checked in a penetrant having a compound suitable for reacting to light excitation; cutting the part at the connection to be checked; and checking for the presence of penetrant under a... Safran Aircraft Engines








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