| SNECMA Patent applications |
| Patent application number | Title | Published |
|---|
| 20160140155 | METHODS OF CREATING A DATABASE AND OF FORMULATING A MAP OF OPERATING STATES OF AIRCRAFT AND A METHOD OF MONITORING THE OPERATION OF AN ASSOCIATED AIRCRAFT - A method of creating a database of operating states of an aircraft fleet, in which a computer executes the steps of acquiring parameters wherein a state of operation of an aircraft of the aircraft fleet; acquiring at least one item of degradation information indicative of a level of degradation of at least one aircraft from among the fleet of aircraft; storing series of parameters in said database, each series of parameters including parameters wherein a state of operation of one of the aircraft and if the item of degradation information has been acquired, at least one item of degradation information indicative of a level of degradation of the aircraft. | 05-19-2016 |
| 20160138476 | IMPROVED INTERMEDIATE CASING FOR TURBOMACHINE AND ACCESSORY GEARBOX DRIVE ASSEMBLY - A turbomachine intermediate casing including an internal hub designed to accept a turbomachine compressor shaft, an outer shell ring, and a plurality of radial arms connecting the hub and the shell ring, one of the arms including an internal housing of radial shaft for driving auxiliary machines, the casing further includes a bevel gearbox for the radial shaft arranged in the outer shell ring, the gearbox being formed as one with the outer shell ring, and the bevel gearbox includes a housing for gears between a radial shaft and an accessories gearbox, said the housing including an opening opening to the periphery of the outer shell ring. | 05-19-2016 |
| 20160138472 | VENTILATION OF A TURBOMACHINE NACELLE - The invention relates to a jet pump type ejector for a turbomachine, including a duct through which a secondary ventilation air flow passes, and a first end of which forms an air intake and a second end of which forms an air outlet, the two nozzles for spraying a primary air flow being mounted in the duct which defines a mixer and a diffuser downstream from the nozzle, said two nozzles being parallel and adjacent to one another, the mixer including two substantially planar longitudinal walls, bottom and top respectively, connected to one another by two side walls having a semicircular cross-section, in which the radius of curvature R | 05-19-2016 |
| 20160138414 | ACCESSORY DRIVE CASE FOR A TURBOPROP - A turbomachine including an accessory drive case, connected to the engine shaft via a radial shaft, wherein the accessory drive case also includes: a primary shaft which is driven by the radial shaft via a bevel gearbox, and assemblies for mechanically driving accessories, driven by the primary shaft and configured such that the related accessories lie at the upper portion and on at least one of the side edges of the engine case. | 05-19-2016 |
| 20160136855 | Coating of a Turbine Engine Part by Overinjection - The invention relates to equipment ( | 05-19-2016 |
| 20160129497 | TURBINE ENGINE BLADE PREFORM - The invention relates to a blade preform ( | 05-12-2016 |
| 20160125518 | PROCESS, SYSTEM AND COMPUTER PROGRAM PRODUCT FOR ASSET MAINTENANCE - A process, system and computer program product for asset maintenance, performed by an asset management system which evaluates an expected operational life until maintenance on the asset is no longer economical, and determines a frequency and a scope of maintenance work for each asset over the expected remaining life of each asset, determines a cost of maintenance over the expected remaining life of each asset based on the frequency and scope of the maintenance work and operational factors, establishes a first maintenance agreement between an asset maintenance company and an asset owner, and a second maintenance agreement between the asset maintenance company and operator such that the maintenance agreements include the frequency, scope, and costs of maintenance work. | 05-05-2016 |
| 20160123185 | METHOD AND A CIRCUIT FOR VENTILATING EQUIPMENT OF A TURBOJET BY THERMOELECTRICITY - The invention provides a method of ventilating equipment of a turbojet, the turbojet ( | 05-05-2016 |
| 20160123167 | HOLLOW VANE, AND ASSOCIATED PRODUCTION METHOD - A hollow vane, includes a main portion, of which the cavity is closed by a cover, that is produced by expanding the main portion relative to the cover, for example by means of differential thermal expansion, then by placing the cover at the bottom of the opening of the cavity, before allowing the main portion to close again, closing a nesting between a protrusion at the bottom of the cover and a widening at the bottom of the opening. The disadvantages linked to the use of welding, glue or even assembly parts are as such avoided. | 05-05-2016 |
| 20160123162 | PROPELLER RING MADE OF COMPOSITE MATERIAL FOR A TURBOMACHINE - A propeller ring of a turbomachine including an annular body substantially coaxial to a principal axis and a plurality of radial housings uniformly distributed about the principal axis, each radial housing being configured to receive a root of a blade, the annular body being made of composite material including a fibrous reinforcement densified by a polymer matrix and further including a plurality of metallic inserts configured to each receive the root of a blade, said metallic inserts being anchored in the composite material of the annular body. | 05-05-2016 |
| 20160123157 | TURBINE WHEEL FOR A TURBINE ENGINE - A turbine wheel for a turbine engine comprising a disc carrying blades. Each blade comprises an upstream radial wall and a downstream radial wall which extend inwards from the platform of the blade. Inter-blade cavities each accommodate one sealing and vibration damping member. According to the invention, each member comprises at least a transverse partition wall axially arranged at a distance from a downstream (or upstream, respectively) portion of the member and axially opposite two upstream (or downstream, respectively) so as to obstruct a flow of incoming air into the cavity between the two radial (or downstream, respectively) upstream walls. | 05-05-2016 |
| 20160123153 | TURBINE WHEEL FOR A TURBINE ENGINE - A turbine wheel for a turbine engine, comprising a disk carrying blades each having a platform, carrying an impeller connected by a stilt to a root. Each blade comprises an upstream radial wall and a downstream radial wall extending inwards from the platform of the blade. The roots of the blades are engaged into slots on the periphery of the disk, so that the radial walls of the blades and the platforms of the blades are circumferentially arranged end-to-end, and define inter-blade cavities radially inside the platforms, each accommodating an inter-blade sealing and vibration damping member. At least one member comprises an elastically deformable element configured so as to be elastically prestressed against the walls of a cavity in the member mounting position. | 05-05-2016 |
| 20160122028 | AIRCRAFT TURBOPROPELLER - An aircraft turbopropeller includes two coaxial contra-rotating unducted propellers, upstream and downstream respectively, each propeller including an annular row of blades. The blades of the downstream propeller have a reverse sweep in relation to that of the blades of the upstream propeller. The leading edges of the blades of the downstream propeller extend radially outwards from downstream to upstream, at least over a radially outer portion of the blades. | 05-05-2016 |
| 20160121999 | AN AIR PROPELLER BLADE PIVOT IN THE SHAPE OF A SPHERICAL CAP - A pivot for an air propeller blade, the pivot including a rotary support for mounting radially on a propeller hub while being suitable for pivoting about a pivot axis; and a blade support including a housing for receiving a blade root and at least one arm extending laterally relative to the pivot axis and carrying a flyweight forming a counterweight; the arm and its flyweight presenting the general geometrical shape of a spherical cap. | 05-05-2016 |
| 20160116387 | TEST BENCH COMBINING HIGH-FREQUENCY TRIBOLOGICAL STRESS AND OLIGOCYCLIC FATIGUE - Test rig combining high-frequency tribological stress and low-cycle fatigue, comprising a first test piece which is fixed to a frame and defines at least one bearing surface, a second test piece which is connected to traction means for loading the second test piece so that it bears against the or each bearing surface of the first test piece, means for heating the test pieces and means for loading the test pieces in a vibratory manner so as to carry out a fretting fatigue and low-cycle and high-cycle fatigue test, one of the test pieces comprising a portion which is in the shape of a turbine engine rotor blade root and which is inserted in a groove, the shape of which groove is substantially complementary to the other test piece so as to reproduce a turbine engine blade-disc attachment. | 04-28-2016 |
| 20160115875 | SYSTEM FOR CONTROLLING VARIABLE-PITCH VANES FOR A TURBINE ENGINE - A system for controlling variable-pitch vanes for a turbine engine, including a control ring having an axis of revolution and, about the axis of revolution, an annular row of connecting rods for connecting the ring to the vanes, each connecting rod including a first end designed so as to be connected to one of the vanes, and a second end which is connected to an elongate shaft which is connected to said the ring. The shaft connected to each connecting rod has an axis of elongation which is inclined relative to a plane extending substantially through the axis of revolution and the connecting rod. | 04-28-2016 |
| 20160115798 | ROTOR BLADE WITH REDUCED ACOUSTIC RESPONSE - A turbine engine rotor blade having a trailing edge ( | 04-28-2016 |
| 20160109344 | OPTIMISATION OF A CYCLE FATIGUE OR CYCLE AND HIGH-CYCLE FATIGUE TEST RIG - A method for optimising a cycle and optionally high-cycle fatigue test rig, said test being intended to reproduce a support for turbomachine parts, wherein it comprises the steps consisting of determining variable geometric parameters of the support member and/or of the workpiece of the rig, in addition to ranges of variation of these parameters, determining at least one aim to be achieved, a variation in the values of at least a part of the abovementioned parameters having an influence on this aim, modifying one or a plurality of the values of the abovementioned parameters, in the respective ranges of same, and determining those that make it possible to achieve the aim, and producing or modifying a support member and/or a workpiece on the basis of the optimised parameters. | 04-21-2016 |
| 20160109283 | IMPROVED METHOD FOR INSPECTION BY THE TRANSMISSION OF ULTRASOUNDS - The invention relates to a method for inspecting an object by means of ultrasound transmission, comprising the steps consisting in: sweeping an ultrasound beam over a reference part that has the same geometry as the object to be inspected, and measuring the amplitude ( | 04-21-2016 |
| 20160108744 | ROTOR DISK BLADE WITH FRICTION-HELD ROOT, ROTOR DISK, TURBOMACHINE AND ASSOCIATED ASSEMBLY METHOD - A rotor disk blade for a turbine engine, the blade being made of composite material including fiber reinforcement obtained by multilayer weaving of yarns and densified by a matrix. The blade has a portion constituting an airfoil and a blade root forming a single piece, the blade root having two substantially plane opposite lateral flanks that are formed respectively extending the pressure side surface and the suction side surface of the airfoil. The blade root is clamped between two metal plates fastened against the lateral flanks of the blade root by a bolt and a nut passing through the plates and the blade root. The bolt has a head bearing against one of the two plates. The nut has a head bearing against the other plate. | 04-21-2016 |
| 20160103168 | EMC TEST BENCH COMPRISING AN ITEM OF EQUIPMENT UNDER TEST WHICH IS INTENDED TO BE LOADED ON BOARD AN AIRCRAFT - An EMC test bench, includes an item of equipment under test to be loaded on board an aircraft, the item of equipment being subjected to EMC tests and delivering ARINC electrical interfaces as inputs and as output; an electrical interfaces device representative of an item of anti-lightning equipment and including an ARINC signals acquisition and/or generation card connected to the ARINC inputs and outputs of the item of equipment under test; a command and control rack for analyzing control signals originating from the electrical interfaces device including the ARINC signals acquisition and/or generation card, and a signals conversion system for protecting the command and control rack connected between the command and control rack and the electrical interfaces device | 04-14-2016 |
| 20160103038 | METHOD AND SYSTEM FOR THE VIBRATION ANALYSIS OF AN ENGINE - A method and a system for the vibration analysis of an engine, including acquiring vibration signals relating to the engine and in order to form at least one spectrogram that represents an operating state of the engine, selecting at least one zone of interest in at least one spectrogram, comparing each zone of interest with a set of corresponding comparison zones belonging to annotated spectrograms recorded in a reference database, and determining a subset of comparison zones that have vibration behaviours similar to those of the zone of interest, and displaying the subset of comparison zones and annotations associated with the subset of comparison zones. | 04-14-2016 |
| 20160101575 | METHOD FOR IMMOBILISING A PREFORM IN A MOULD - A method for manufacturing a turbine-engine blade from a preform made from polymerized composite material in a mold comprising a bottom part and a top part, comprising at least one closure step during which the top part of said mold is attached to the bottom part of the mold containing the preform, wherein it comprises, prior to said closure step, at least one insertion substep during which a first end of an immobilization element is inserted in a bottom part of the preform in a substantially transverse direction, and a positioning substep during which a second, opposite end of said element is disposed in a complementary reception cavity emerging in the bottom part of the mold. | 04-14-2016 |
| 20160096634 | MONITORING OF AN AIRCRAFT PROPULSION SYSTEM - Monitoring the propulsion system of an aircraft includes selecting elements representative of operation of the propulsion system, modeling the propulsion system by a model including the selected elements, a set of exogenic parameters of the propulsion system and interdependence relations between the elements, operation of a given element being modelled by at least one endogenic parameter dependent on at least one of the exogenic parameters and/or on at least one parameter of another element, and analyzing elements, the analysis of the given element including the expression of the at least one endogenic parameter of the given element as a function only of exogenic parameters of the propulsion system and being made by layers of different levels, a layer of a given level being capable of taking account of at least one parameter that is the result of a layer of a different analysis level of another element. | 04-07-2016 |
| 20160096633 | METHOD FOR DETERMINING AT LEAST ONE FAULTY PIECE OF EQUIPMENT OF AN AIRCRAFT, AND CORRESPONDING SYSTEM - A method is provided for determining at least one faulty piece of equipment from amongst a plurality of pieces of equipment of an aircraft. A system is also provided that implements the method. The method comprises the steps of reading a plurality of predetermined parameters for monitoring said equipment; defining a list of symptoms associated with said parameters read, using a predetermined correspondence table; attributing a value associated with each symptom according to the parameters read, which value is selected from amongst a predetermined list of values; evaluating for each piece of equipment an occurrence of one or more fault modes for said piece of equipment on the basis of at least one predetermined truth table which associates a fault mode with each combination of symptom values; and determining at least one faulty piece of equipment from amongst one or more pieces of equipment, of which at least one fault mode is currently occurring, referred to as potentially faulty equipment. | 04-07-2016 |
| 20160090855 | TURBINE WHEEL FOR A TURBINE ENGINE - A rotating assembly for a turbine engine, comprising a disc having an outer periphery having alternating slots and teeth, blades radially extending from the disc and roots of which are axially engaged in the slots, with spaces called slot cavities being provided between the roots of the blades and the slots, platforms laterally extending from the blades and circumferentially arranged end-to-end, so as to form spaces called inter-blade cavities, and a downstream annular shroud, comprising an outer annular sealing lip opposite the downstream ends of the platforms. The downstream shroud further comprises an intermediate annular sealing lip opposite the downstream faces of the teeth of the disc, radially between the slot cavities and the inter-blade cavities. | 03-31-2016 |
| 20160084501 | ANNULAR COMBUSTION CHAMBER - A turbine engine having an annular combustion chamber formed by two coaxial annular shrouds, an inner shroud and an outer shroud relative to the axis of the turbine engine, which shrouds are arranged one inside the other and are connected together at their upstream ends by an annular chamber end wall that is fastened to an outer casing surrounding the outer annular shroud, the downstream ends of the inner and outer annular shrouds being connected to flanges fastened to an inner casing and to the outer casing, respectively. The upstream end of at least one of the inner and outer shrouds is centered by bearing radially against the annular chamber end wall and co-operates therewith in leaktight axial sliding. | 03-24-2016 |
| 20160083106 | DEVICE FOR CUTTING-OFF POWER TO THE ALTERNATORS OF A TURBINE ENGINE DURING ACCELERATION - A DC electrical generation system for an aircraft propelled by a turbine engine, such as a turbojet, includes at least one electrical energy storage capacity, at least one generator driven mechanically by a rotation shaft of the turbine engine and electrical connections between the electrical energy storage capacity, the generator and the aircraft equipment for powering the above-mentioned equipment with DC current, also including at least one alternative for supplying DC current to the equipment, which are autonomous in relation to any mechanical driving by a rotation shaft of the turbine engine, and a device that can cut-off power to the generator(s) and simultaneously activate the alternative current supply. The power cut-off device for triggering power cut-off and activating the alternative current supply is controlled by a control or operating parameter of the turbine engine. The alternative current supply is preferably formed by one or more supercapacitors. | 03-24-2016 |
| 20160077019 | MACHINE FOR WEAVING OR WINDING A FIBER TEXTURE AND ENABLING ANOMALIES TO BE INSPECTED BY IMAGE ANALYSIS - A machine for weaving or winding a fiber preform on a mandrel having an axis of rotation that is substantially horizontal and that serves to receive the preform, the machine having a plurality of cameras pointing towards the underside of the fiber preform in order to scan the hidden face of the fiber preform and acquire images of the hidden face; an image analysis module for processing these images of the hidden face of the fiber preform in a plurality of adjacent scan windows, and for extracting weaving patterns therefrom and comparing them with reference weaving patterns previously stored in the module; a motor for driving the mandrel in rotation about its axis of rotation; and a control unit for stopping rotation of the mandrel if the result of the comparison reveals a difference of appearance between the two weaving patterns. | 03-17-2016 |
| 20160076401 | BALL JOINT DEVICE FOR SUSPENDING A TURBINE ENGINE ON A PYLON OR SUSPENDING EQUIPMENT ON THE BODY OF THE TURBINE ENGINE - Ball joint device for suspending a turbine engine from a pylon or suspending equipment on the body of the turbine engine, comprising a connecting rod, one end of which bears a ball and which is inserted between the two lugs of a clevis, the ball having a boring for the passage of a spindle having an axial boring for mounting a screw for clamping and axial locking the ball, the ball being axially locked by clamping between a bushing and a ring which carries removable means for axially retaining the ring with respect to the clevis during an operation of dismantling the device. | 03-17-2016 |
| 20160069276 | A METHOD AND A DEVICE FOR GENERATING A COMMAND FOR THE FLOW RATE OF FUEL THAT IS TO BE INJECTED INTO A COMBUSTION CHAMBER OF A TURBINE ENGINE - During a stage (E | 03-10-2016 |
| 20160069275 | TURBOMACHINE COMPRISING A PLURALITY OF FIXED RADIAL BLADES MOUNTED UPSTREAM OF THE FAN - Bypass turbine engine, in particular for an aircraft, in which air flows circulate from upstream to downstream, the turbine engine extending axially and comprising:
| 03-10-2016 |
| 20160069207 | FAN DISK FOR A JET ENGINE AND JET ENGINE - A fan disk is for a jet engine in which there flows a gas stream in a flow direction, pin-shaped radial section of the fan disk includes a first branch, designed to be fixed to a drive shaft of the jet engine, a second branch, extending opposite the first branch and designed to support a plurality of fan blades, and a curved junction wall that extends between the first branch and the second branch. | 03-10-2016 |
| 20160069205 | TURBOMACHINE COMPRISING A PLURALITY OF FIXED RADIAL BLADES MOUNTED UPSTREAM OF THE FAN - Bypass turbine engine, in particular for an aircraft, in which air flows circulate from upstream to downstream, the turbine engine extending axially and comprising:
| 03-10-2016 |
| 20160068950 | PROCESS FOR DEPOSITING A COATING FOR PROTECTION AGAINST OXIDATION AND AGAINST HOT CORROSION ON A SUPERALLOY SUBSTRATE, AND COATING OBTAINED - To protect a superalloy substrate from oxidation and hot corrosion, disclosed herein is coating made by a process that deposits successive layers on the substrate, a first layer of aluminium and of at least one element capable of being alloyed with sulphur, and a second layer of a material that isolates the at least one element capable of being alloyed with sulphur. | 03-10-2016 |
| 20160061699 | METHOD FOR ANALYSING A FRACTURE FACE OF A PART OF A TURBINE ENGINE - Process for analysing a fracture or crack surface of a TiAl turbomachine part, comprising at least one of the steps consisting in: a) marking on the surface the position and the orientation of cleavage facets, so as to identify a region of fracture or crack initiation and to determine the direction of propagation of this fracture or crack, b) examining the surface and detecting the regions with the presence of equiaxed grains and/or lamellar grains, so as to evaluate the temperature at which the fracture or crack has taken place, and c) comparing the heat tintings of the surface with those of samples from a heat tinting colour chart so as to evaluate the speed of propagation of the fracture or crack. | 03-03-2016 |
| 20160061675 | SYSTEM FOR REPRODUCING A DRY FRICTION TORQUE - A system for reproducing a dry friction torque applied to an actuator on a valve of a hydraulic line including a disc coupled to a power transmission shaft; a disc brake including a caliper mounted on a frame and plates adapted to be put into contact with the disc; and an electric actuator configured to control the force of application of the plates onto the disc so as to apply a controlled resistive torque to the power transmission shaft, is provided. | 03-03-2016 |
| 20160059315 | METHOD FOR MANUFACTURING AN ASYMMETRIC COMPONENT USING ADDITIVE MANUFACTURING - A method of fabricating a part by additive fabrication, in particular by melting or sintering particles of powder by means of a high energy beam. The method includes supplying a digital model of a part to be fabricated; orienting the model relative to a construction direction for constructing the part; modifying the model by adding a sacrificial balancing fraction configured so as to balance the residual stresses that appear in the part while it is being fabricated; making a rough part layer by layer using an additive fabrication technique on the basis of the model as modified in this way, the layers being stacked in the construction direction; and using a material-removal method to eliminate the sacrificial portion from the rough part as results from the sacrificial balancing fraction of the model, thereby obtaining the part that is to be fabricated. | 03-03-2016 |
| 20160054233 | SYSTEM FOR DETECTING DEFECTS ON AN OBJECT - A system and method for detecting defects on an object including forming an image representing the object from signals relating to the object, constructing subdivisions of the image according to auto-adaptive resolutions, and calculating differentials between various subdivisions in order to detect an abnormal subdivision indicating incipient failure. | 02-25-2016 |
| 20160052046 | MONOCRYSTALLINE CASTING MOLD - The invention relates to the field of monocrystalline casting, and in particular to a mold ( | 02-25-2016 |
| 20160047510 | METHOD AND DEVICE FOR THERMALLY INSULATING A PIECE OF EQUIPMENT - A device for thermally insulating a piece of equipment, the device including a block of thermal insulation having at least a first hole; a deformable cover made of a gastight material and surrounding the block of insulation so that the wall of the first hole is covered by the gastight cover while leaving open the ends of first hole, the cover defining, at the second end, a first opening that communicates with the first hole and a second opening that communicates with the space situated between the insulating block and the cover; and the first and second openings of the cover being closed in gastight manner with the inside of the cover under a partial vacuum. | 02-18-2016 |
| 20160041550 | METHOD OF MONITORING SHORT CIRCUITS IN TORQUE MOTORS - A method of monitoring an actuator system comprising a control device, a torque motor having a voltage Umc across its terminals and actuating a servo-valve, and an actuator controlled by the servo-valve, the control device being suitable for delivering to the torque motor a control current Icmd as a function of a current setpoint I_c and of a measured current Imes, the monitoring method comprising the following steps:
| 02-11-2016 |
| 20160040711 | BEARING WITH DOUBLE PRE-LOADING - In a rotary machine bearing including an inner ring, an outer ring, and rolling elements between them, one of the inner and outer rings includes first and second half-rings suitable for being clamped in the axial direction between a thrust member and a first pre-loading system exerting a first predetermined axial force, and a second pre-loading system is provided that is inserted in the axial direction between the first and second half-rings and that exerts a second predetermined axial force less than the first predetermined axial force. | 02-11-2016 |
| 20160032964 | DISENGAGEABLE AXIAL THRUST BEARING WITH INTERNAL PRELOAD - In a disengageable axial thrust bearing for a rotary machine, an outer ring has first and second outer half-rings ( | 02-04-2016 |
| 20160032762 | DEVICE FOR DEICING A SEPARATOR NOSE OF AN AVIATION TURBINE ENGINE - A device for deicing a separator nose of an aviation turbine engine, and including a separator nose for positioning downstream from a fan of the engine to separate annular channels for passing a primary stream and a secondary stream coming from the engine, and a casing fastened to the separator nose so as to extend it downstream, the casing having an inner shroud defining the outside of the primary stream flow passage, and including at least one air duct incorporated in the inner shroud so as to be formed integrally therewith, the air duct opening out downstream to an air feed and opening out upstream into the inside of the separator nose. | 02-04-2016 |
| 20160032755 | V-SHAPED GEARBOX FOR DRIVING TURBOMACHINE EQUIPMENT - A gearbox for driving equipment of a turbomachine, including a substantially V-shaped box having two arms joined together by a joining part, the arms containing gear trains joined together at the joining part, and an attachment to the turbomachine. The attachment include a mechanism for insetting and/or for attaching the joining part and a suspension device of the arms. | 02-04-2016 |
| 20160032741 | SHOT PEENING DEFORMATION PROCESS FOR ASSEMBLING TWO PARTS OF A TURBOMACHINE - The main object of the invention is a process for deforming at least one part ( | 02-04-2016 |
| 20160032734 | FAN FOR A MULTI-FLOW TURBOSHAFT ENGINE, AND TURBOSHAFT ENGINE EQUIPPED WITH SUCH A FAN - The fan comprises a fan disk able to be rotationally driven about a longitudinal axis and provided at the periphery with radial blades each comprising a root slideably engaged in a groove of the disk and, on the outside thereof, a vane, platforms surrounding the disk being interposed between the radial blades. Advantageously, the fan additionally comprises shock-absorbing wedges which are arranged tangentially at the exterior periphery of said disk underneath the platforms and between two roots of adjacent radial blades, each wedge being in tangential contact with the two adjacent blades. | 02-04-2016 |
| 20160026256 | DEVICE FOR ASSISTED MAINTENANCE OF AN AIRCRAFT ENGINE BY RECOGNITION OF A REMOTE MOVEMENT - There is provided a device for assistance with maintenance for an aircraft engine, including computer means; display means; and a human-machine interface. The human-machine interface includes remote movement recognition means to remotely identify a movement or a position of a human operator and to provide corresponding identification data; and a control module, to provide a control command to the computer means in response to the identification data. The computer means are designed to control the display on the display means, of assistance information for maintenance of an aircraft engine, in response to the control command. The computer means are also designed to control holding the content of a display shown on the display means. A method used with such a device is also provided. | 01-28-2016 |
| 20160024967 | TOOL FOR FITTING AN INNER BEARING RACE CARRYING A BEARING CAGE AND SCREWS FOR RETAINING IN A TURBOMACHINE - The disclosure relates to a tool for fitting an inner bearing race carrying a bearing cage and rollers and screws in a turbomachine, comprising two sectored cylindrical casings which respectively cover an upstream end part of the race and the bearing cage, a cylindrical annulus which surrounds the second casing, and a locking ring which is fitted on an upstream part of the first casing and which has means for axially pressing against the annulus and for axially clamping the second casing between the annulus and the heads of the screws carried by the flange. | 01-28-2016 |
| 20160017808 | COMPACT DOSING DEVICE FOR AN INJECTOR WITH TWO FUEL CIRCUITS FOR AN AIRCRAFT TURBOMACHINE - A fuel dosing device for a fuel injector of an aircraft turbomachine, including an opening, a movable member for sealing the opening, and elastic return, with the member able to be displaced under the effect of the fuel pressure. The device includes a first outlet communicating with a primary circuit of the injector as well as a second outlet communicating with a secondary circuit. In addition, it is designed such that up to a defined level of displacement of the sealing member, the latter allows the fuel coming from the opening to reach the first outlet and, only beyond the defined level of displacement, the member allows the fuel coming from the opening to reach the second outlet. | 01-21-2016 |
| 20160003148 | METHOD AND DEVICE FOR REGULATING THE COOLING OF OIL IN A TURBOMACHINE - A method for regulating oil cooling within an oil cooling device of a turbomachine including a first heat exchanger mounted in series with a second heat exchanger, the first heat exchanger being an oil/air exchanger while the second heat exchanger is an oil/fuel exchanger, each heat exchanger having an oil inlet and an oil outlet, a bypass directly connecting the oil inlet of the first heat exchanger to the oil outlet of the first heat exchanger, and a flow regulator to regulate the flow rate of oil flowing through the bypass. Circulation of oil though the bypass is allowed by means of the flow regulator when the oil temperature is less than or equal to a predetermined temperature comprised between 70° C. and 90° C., preferably equal to about 80° C. | 01-07-2016 |
| 20160003146 | ROTATING INLET COWL FOR A TURBINE ENGINE, COMPRISING AN ECCENTRIC FORWARD END - A rotating inlet cowl for a turbine engine includes a rotation axis. The rotating inlet cowl includes a forward cone defining a forward end of the inlet cowl. The forward end is configured to be eccentric relative to the rotation axis of the inlet cowl. Furthermore, the forward cone is truncated by a truncation surface defining the forward end of the inlet cowl. | 01-07-2016 |
| 20160003095 | UNDULATING STATOR FOR REDUCING THE NOISE PRODUCED BY INTERACTION WITH A ROTOR - A stator designed to be placed radially in a flow which passes through one or more rotors which share the same axis of rotation, with a leading edge and a trailing edge. The leading edge and trailing edge are connected by a lower face and an upper face, wherein at least one of the faces of the stator has radial undulations which extend axially from the leading edge to the trailing edge. The radial undulations can have at least two bosses in the same azimuth direction, the amplitude of which is at least one centimeter on at least part of the axial length of the stator. A propulsion assembly formed by the rotor and the stator, and to a turbine engine comprising such assembly is also provided. | 01-07-2016 |
| 20160001898 | SPACE PROPULSION MODULE HAVING BOTH ELECTRIC AND SOLID FUEL CHEMICAL PROPULSION - A space propulsion module in particular for fitting to spacecraft such as satellites, probes, or indeed the upper stages of rockets. According to the invention, the space propulsion module comprises a solid propellant chemical thruster ( | 01-07-2016 |
| 20160001466 | MOLD COMPRISING SHELLS AND AT LEAST ONE SLIDE - A mold comprises a first shell and a second shell that are suitable, in the closed position, for imparting a shape to a part that is to be molded in the mold, a main axis A being perpendicular to the main plane in which the first shell and the second shell extend. The mold further comprises at least one slide that is situated between the first shell and the second shell and that is in contact with the first shell and the second shell when the mold is in the closed position, and that is to come into contact with the molded part, the or each slide presenting a first face that constitutes its interface with the first shell, the first face presenting a primary direction along which the slide is suitable for sliding along the first face when the mold is in the open position. | 01-07-2016 |
| 20150377489 | INJECTION SYSTEM FOR A TURBINE ENGINE COMBUSTION CHAMBER CONFIGURED FOR DIRECT INJECTION OF TWO COAXIAL FUEL FLOWS - In known types of injection systems for a turbine engine combustion chamber, the secondary fuel flow strikes the venturi before entering into the combustor. A new injection system is disclosed to overcome this problem, comprising a first annular deflector surrounded by the bowl of the injection system and extending in the downstream direction from the downstream transverse surface that delimits the downstream side of the swirler. This first deflector has a free downstream end offset in the upstream direction from a downstream end of the bowl, so as to guide an air film output from the first orifices formed through the bowl. The internal radius ψ of the cross section of the first annular deflector increases from the downstream transverse surface as far as the downstream end of the first annular deflector. | 12-31-2015 |
| 20150377235 | TWO STAGE PUMP, PARTICULARLY PROVIDED AS MAIN PUMP FOR SUPPLYING AN AIRCRAFT ENGINE WITH FUEL - A two stage pump ( | 12-31-2015 |
| 20150377136 | TURBOJET ENGINE SUSPENSION USING A DOUBLE REAR SUPPORT - Bypass turbojet engine comprising a fan casing ( | 12-31-2015 |
| 20150369080 | ROTATING MACHINE COMPRISING A DAMPING COLLAR - A rotary machine including a stationary portion and a rotary portion; at least one bearing provided with a stationary ring and a rotary ring, the bearing being mounted between the stationary portion and the rotary portion in order to guide the rotary portion in rotation; and a damper collar interposed between the stationary ring of the bearing and the stationary portion. The damper collar includes a flexible strip having tongues cut out therein, and the flexible strip is shaped into a ring around the stationary ring of the bearing, the shaping of the strip into a ring causing the tongues to move outwards from the collar so that the free edges of the tongues come into contact with the stationary portion. | 12-24-2015 |
| 20150369058 | TURBOMACHINE ROTOR BLADE - A turbomachine rotor blade, said blade having, at the distal end thereof, a heel comprising: a platform ( | 12-24-2015 |
| 20150361920 | OPTIMISING THE AVAILABILITY OF A THRUST REVERSER - A method of controlling a thrust reverser made up of a plurality of pieces of equipment, wherein, in the event of it being detected that one of the pieces of equipment has not activated by the end of a predetermined activation period, an error message relating to the malfunction of the thrust reverser is generated, and in spite of the error message being generated, activation of the equipment is continued, and if the equipment is finally activated before a predetermined maximum period for deployment of the thrust reverser, then deployment of the thrust reverser is continued and the error message relating to the malfunction of the thrust reverser is withdrawn. | 12-17-2015 |
| 20150361885 | AN ACOUSTICALLY OPTIMIZED AIR INLET - A nacelle structure ( | 12-17-2015 |
| 20150361817 | TURBINE ENGINE IMPELLER - The invention relates to an impeller for a turbine engine, such as a turbojet engine or a turboprop engine of an aircraft, intended for rotating about an axis of rotation in a predetermined direction of rotation (R) and for having a flow of gas passing therethrough, comprising a series of blades ( | 12-17-2015 |
| 20150361808 | TURBOMACHINE VANE INCLUDING AN ANTIVORTEX FIN - The invention relates to a turbomachine vane ( | 12-17-2015 |
| 20150360788 | SUSPENSION STRUCTURE WITH VARIABLE GEOMETRY OF A TURBOPROP ENGINE ON A STRUCTURAL ELEMENT OF AN AIRCRAFT - A variable geometry suspension structure for suspending a turboprop from a structural element of an aircraft, the structure including a rear cradle for fastening to a structural element of an aircraft and a front cradle for supporting a front portion of the turboprop, the front cradle being connected to the rear cradle, firstly via a pivot connection configured to enable the front cradle to tilt vertically relative to the rear cradle, and secondly by a return spring configured to prevent the front cradle from tilting while thrust from the turboprop is below a predetermined threshold. | 12-17-2015 |
| 20150354994 | DEVICE FOR MEASURING THE INTERNAL PROFILE OF A HOLLOW SHAFT - A sensor is placed on a plate lowered into the hollow of the shaft and guided by taut wires between a lower attachment device and an upper motorised winder. The deformations, responsible for measurement errors and caused either by static deformations, produced by the weight or poor construction of the apparatus, or by vibrations, are to a large extent eliminated. | 12-10-2015 |
| 20150354505 | PROPELLANT FEED CIRCUIT AND A COOLING METHOD - The invention relates to the aerospace field, and in particular to the field of vehicles propelled by rocket engines. In particular, the invention relates to a feed circuit ( | 12-10-2015 |
| 20150354503 | SYSTEM AND A METHOD FOR FEEDING A ROCKET ENGINE - The invention relates to the field of rocket engines, and more particularly to a system for feeding a rocket engine ( | 12-10-2015 |
| 20150352634 | METHOD FOR MANUFACTURING A COMPONENT USING THE LOST-WAX CASTING METHOD WITH DIRECTED COOLING - A method for manufacturing a metal component using the lost-wax casting method is provided. The component is made of nickel alloy, with a columnar or monocrystalline structure with at least one cavity of elongate shape. The method includes creating a wax model of the component with a ceramic core corresponding to said cavity, the ceramic core comprising a first land for holding at one longitudinal end and a second land for holding at the opposite end, creating a shell mold around the model, the mold comprising a base and the first land of the core being at the same end as the base, placing the mold in a furnace, with the base standing on the sole of the furnace, pouring the said molten alloy into the shell mold, solidifying the poured metal by gradual cooling from the sole in a direction of propagation. The core in one example is secured to the shell mold by an anchor providing anchorage between the first land of the core and the wall of the mold, the second land of the core being retained in the mold by a retainer that slides on the wall of the mold. | 12-10-2015 |
| 20150346155 | DEVICE FOR THE NONDESTRUCTIVE TEST OF A PART - Eddy current testing to detect defects at the surface or at shallow depth in a part, in particular a blade root for an airplane engine fan. The device comprises a probe ( | 12-03-2015 |
| 20150343556 | AUXILIARY DEVICE FOR WELDING SPINDLE DISKS, HAVING A DAMPING BELT, AND FRICTION WELDING METHOD - A belt including notches alternating with bushings on its inside surface is arranged around a disk, so as to encase it and to squeeze its periphery, the bushings penetrating into slot necks designed to house blade roots, so as to apply an elastic tightening force on the teeth and prevent fatigue cracks from forming during inertial friction welding of the disk with other parts of the rotor, these cracks possibly appearing at fillet connections of the teeth to the central part of the disk. The belt is made from elastic polymer with good internal viscosity, and damping properties. | 12-03-2015 |
| 20150338103 | TURBINE ENGINE WALL HAVING AT LEAST SOME COOLING ORIFICES THAT ARE PLUGGED - A turbine engine wall having a cold side and a hot side and including a plurality of cooling orifices for enabling air flowing on the cold side of the wall to penetrate to the hot side at least some of the cooling orifices being plugged by a plugging material so as to define a minimum level of porosity for the wall corresponding to putting the turbine engine into service, and the plugged cooling orifices being suitable for being unplugged progressively throughout the lifetime of the turbine engine in order to define a maximum level of porosity for the wall corresponding to an end of lifetime for the turbine engine, the plugging being performed by alternating at least one of the following rows or lines: circumferential rows, axial rows, diagonal lines, so as to lie in the range one-third to one-half of the maximum porosity. | 11-26-2015 |
| 20150337763 | A PROPELLANT FEED CIRCUIT AND A COOLING METHOD - The invention relates to the aerospace field, and in particular to the field of vehicles propelled by rocket engines. In particular, the invention relates to a feed circuit ( | 11-26-2015 |
| 20150337736 | TURBOMACHINE FUEL CIRCUIT - A fuel circuit of a turbomachine, this circuit including a fuel return valve connected to the main fuel circuit and to a tank, the valve being able to take a first and a second open position, separate from one another, and a closed position, two primary hydraulic lines connecting the valve to the main circuit and including, respectively, first and second filters through which the fuel passes when the valve is in its first open position, two secondary hydraulic lines which connect the valve to the main circuit and which are positioned in relation to the first and second filters in such a way that the circulation of fuel in these secondary lines contributes, respectively, to the cleaning of the first and second filters, the fuel circulating in the secondary lines when the valve is in its second open position. | 11-26-2015 |
| 20150337679 | METHOD FOR DETECTING A FLUID LEAK IN A TURBOMACHINE AND SYSTEM FOR DISTRIBUTING A FLUID - The invention relates to a method for detecting a fluid leak in a turbomachine. The turbomachine comprises a high temperature fluid source, at least one fluid distribution pipe adapted to distribute said fluid to different parts of the turbomachine and/or the aircraft which is intended to be equipped with said turbomachine, a turbomachine compartment in which the distribution pipe is at least partly accommodated, said compartment having in operation a low temperature relative to the high temperature of the fluid supplied by the fluid source. The method comprises the following steps: measuring a temperature variation in the compartment between two instants to obtain a temperature gradient; and detecting a fluid leak if the temperature gradient is greater than or equal to a threshold temperature gradient. The invention further relates to a system for distributing a high temperature fluid for a turbomachine and a turbomachine comprising such a system for distributing a fluid. | 11-26-2015 |
| 20150336181 | DEVICE AND METHOD FOR LOCALIZING A POSITION ON A PART - A device for localizing a position on a part ( | 11-26-2015 |
| 20150330949 | METHOD FOR CHARACTERISING A PART MADE OF A COMPOSITE MATERIAL - The invention consists in a method of characterizing a part made of composite material ( | 11-19-2015 |
| 20150330308 | TURBOJET WITH A DISCHARGE DUCT - The invention relates to a unit comprising an intermediate turbojet casing formed by a hub including a downstream transverse endplate having formed therein at least one first opening putting the inside of the hub into communication with a duct extending downstream from the endplate and opening out at its downstream end via a second opening formed in an outer annular shroud extending downstream from the hub for defining the inside of an annular flow space for a secondary stream. More particularly, the upstream end of said duct is fastened to the downstream endplate of the hub by releasable elastic engagement. | 11-19-2015 |
| 20150322796 | TURBINE ROTOR FOR A TURBOMACHINE - A turbine rotor for a turbomachine, including a disk containing slots for mounting vane roots, each slot being defined by two adjacent teeth of the disk, the vane roots including contact surfaces bearing on contact surfaces of the teeth of the disk. Foils are mounted on the teeth of the disk, each foil having a general U-shape including lateral bearing parts inserted between the corresponding contact surfaces of the vane roots and teeth of the disk, and a central part facing the peak of the corresponding tooth of the disk and defining a cavity between said peak and the foil. The turbine rotor also includes a device for supplying cooling air into said cavity. | 11-12-2015 |
| 20150322794 | ASSEMBLY OF A BALANCE WEIGHT WITH A ROTOR ELEMENT - The balance weight is fixed to the flange of a rotor element by a pre-fixing screw with a conical head engaged into a conical counterbore having a shape complementary to the flange, which places the weight at a very accurate position before permanently fixing it by a clamping stud. | 11-12-2015 |
| 20150316512 | METHOD AND DEVICE FOR ACOUSTICALLY DETECTING A MALFUNCTION OF A MOTOR HAVING AN ACTIVE NOISE CONTROL - The present invention relates to a method for acoustically detecting at least one malfunction (DYS) of a motor, the motor generating a primary noise Po that is treated by an active noise control system emitting, at the noise reduction targets, an acoustic signal Pc produced by at least one actuator and connected by a transfer function H to a signal Y produced by said active noise control system, said malfunction (DYS) having an acoustic signature identifiable in the primary noise Po at the noise reduction targets, characterised in that it comprises the following steps: acquisition of said signal Y produced by the active control system; identification of the appearance, if any, of a malfunction by a monitoring means that uses the knowledge of Y and H and emits an alert message if warranted. | 11-05-2015 |
| 20150315931 | DEVICE FOR CONNECTING A FIXED PORTION OF A TURBINE ENGINE AND A DISTRIBUTOR FOOT OF A TURBINE ENGINE TURBINE | 11-05-2015 |
| 20150315926 | TURBINE CASING MADE OF TWO MATERIALS - The invention proposes a casing ( | 11-05-2015 |
| 20150315923 | STATOR VANE FORMED BY A SET OF VANE PARTS - A stator vane for a turbine machine includes a set of vane parts arranged relative to each other to define air flow stream paths between vane parts, and a mechanism circulating a fluid to be cooled by the air flow. | 11-05-2015 |
| 20150315915 | PROPELLER BLADE FOR A TURBOMACHINE - The invention relates to a propeller blade ( | 11-05-2015 |
| 20150315914 | A METHOD OF BALANCING A TURBINE ENGINE ROTOR, AND A ROTOR BALANCED BY SUCH A METHOD - A method of balancing a turbine engine rotor, the method including mounting screws forming balance weights on the rotor in order to form a balance configuration, each screw possessing a predetermined weight and a screw head having a visual characteristic previously associated with its weight. A rotor balanced by such a method is also disclosed. | 11-05-2015 |
| 20150314853 | CONTROL DEVICE FOR AN ENGINE - An engine control device having a calculator for calculating a pitch setpoint for at least one propeller of the engine, the calculator taking account at least of a flight speed. | 11-05-2015 |
| 20150311542 | ELECTRICAL INSTALLATION HAVING A COOLED FUEL CELL COMPRISING AN ABSORPTION HEAT ENGINE - The invention relates to an installation ( | 10-29-2015 |
| 20150308984 | METHOD AND DEVICE FOR ULTRASOUND INSPECTION OF WELDS, PARTICULARLY WELDS OF BLADES ON THE DISK OF A BLADED DISK - Method and device for ultrasound testing of welds, particularly for welds of blades on the blisk of a bladed disk. | 10-29-2015 |
| 20150308384 | PROPULSION ASSEMBLY FOR ROCKET - A propulsion assembly for a rocket including a tank for liquid oxygen, an engine having a combustion chamber, and a “heater” heat exchanger suitable for vaporizing liquid oxygen. The assembly has a vaporized oxygen circuit suitable for directing the oxygen vaporized by the heater either to the combustion chamber or to the tank. When the vaporized oxygen is directed to the combustion chamber, the engine advantageously develops low thrust. | 10-29-2015 |
| 20150308289 | ATTACHMENT OF A DISCHARGE CONDUIT OF A TURBINE ENGINE - Discharge conduit for a turbine engine, comprising an air intake end, an air outlet end and a tubular sleeve for guiding air between said ends, said air intake end being equipped with means for attachment to an intermediate casing of the turbine engine, characterized in that said attachment means are of the resilient snap-in type. | 10-29-2015 |
| 20150308280 | ASSEMBLY FORMING A SEAL FOR A TURBOMACHINE INCLUDING A BRUSH SEAL AND AT LEAST ONE LIP - The main object of the invention is an assembly forming a seal ( | 10-29-2015 |
| 20150308279 | ROTATING ASSEMBLY FOR A TURBOMACHINE - A rotating assembly for a turbomachine, including a disc having an external periphery with alternating recesses and teeth, blades extending radially from the disc and the feet of which are axially engaged and radially retained in the recesses of the disc, platforms extending on the circumference from the blades and being arranged end to end on the circumference, with respect to each other, axial sealing device upstream and/or downstream of an annular zone extending radially from the platforms up to the disc. The sealing device radially includes an internal annular portion and an external annular portion structurally distinct from each other, and the external annular portion of which is elastically constrained radially inwards by the internal annular portion. | 10-29-2015 |
| 20150302577 | METHOD FOR THE NON-DESTRUCTIVE TESTING OF A BLADE PREFORM - An automated method for the non-destructive testing of a woven preform for the manufacture of a turbine engine part and including a plurality of first marker threads intertwined with second marker threads, the first and second threads having light-reflecting properties that are different from those of the threads of the preform and being woven with the threads of the preform so as to form a surface grid on a given area of the preform. The method includes determining, with a plurality of consecutive steps, the spatial coordinates of the intersections between the first and second marker threads. | 10-22-2015 |
| 20150300329 | PROPELLANT GAS SUPPLY FOR AN IONIC PROPULSION UNIT - A field of feeding propellant gas to ion thrusters, and in particular a method of feeding an ion thruster with propellant gas coming from a pressurized tank via a feed circuit including an on/off valve and, in succession downstream from the on/off valve, a high pressure restrictor, a buffer tank, and at least one low pressure restrictor. The method includes the steps of calculating a pressure setpoint for the buffer tank as a function of a flow rate setpoint, calculating the difference between the pressure setpoint for the buffer tank and a pressure measured in the buffer tank, calculating a setpoint for the opening time of the on/off valve as a function of the difference and of a pressure inside the pressurized tank, and opening the on/off valve in compliance with the opening time setpoint. | 10-22-2015 |
| 20150300255 | DEVICE FOR RECOVERING LUBRICATING OIL FROM AN EPICYCLIC REDUCTION GEAR - An epicyclic reduction gear, including a planetary gear movable in rotation about an axis of rotation, planet pinions driven by the planetary gear and movable in rotation about axes of planet gears carried by a planet carrier, the planet pinions rolling on a fixed ring gear and the planet carrier being axially positioned laterally relative to the ring gear, the gear formed by the planet pinions and the ring gear being formed to axially eject lubricating oil thereof after use. The planet carrier includes a radial extension positioned facing the gear and forming a mechanism for guiding the oil to a radial end thereof to be ejected from there by centrifugation. | 10-22-2015 |
| 20150300208 | TURBINE ENGINE HAVING AN ELEMENT FOR DEFLECTING FOREIGN OBJECTS - Turbine engine ( | 10-22-2015 |
| 20150300206 | AIR EXHAUST TUBE HOLDER IN A TURBOMACHINE - A support for carrying a tube for discharging oil-laden air from a turbine engine, the support including a radially inner annular portion for mounting around the tube, and fins that are inclined relative to the axial direction of the annular portion and relative to the radial plane, the radially outer periphery of each fin being for fastening to an exhaust cone of the turbine engine. | 10-22-2015 |
| 20150300198 | TURBOMACHINE COMPRISING A PLURALITY OF FIXED RADIAL BLADES MOUNTED UPSTREAM OF THE FAN - A bypass turbine engine including an inner casing, an inter-duct casing and an outer casing, wherein a primary duct is defined between the inter-duct casing and the inner casing, wherein a secondary duct is defined between the inter-duct casing and the outer casing wherein a rotary shaft includes, at the upstream end, a movable fan including radial blades of which the free ends face the outer casing of the turbine engine so as to compress an air flow at least in the secondary duct, wherein a plurality of variable-pitch radial stator vanes are mounted upstream of the movable fan, the variable-pitch vanes being configured to deflect the incident axial air, wherein the movable fan is configured to axially rectify the air deflected in the secondary duct, and the turbine engine not being provided with stator vanes in the secondary duct downstream of the movable fan. | 10-22-2015 |
| 20150300191 | ASSEMBLY FORMING A GASKET FOR A TURBOMACHINE, COMPRISING A BRUSH SEAL - An assembly forming a gasket for a turbomachine, includes a brush seal made of a plurality of sealing elastic bristles surrounding a core, a retaining ring including a recess to at least partly accommodate the brush seal, and a bearing cover, placed in contact with the brush seal to hold it in position against the retaining ring, the brush seal being located between the retaining ring and the bearing cover. | 10-22-2015 |
| 20150300182 | METHOD FOR FRICTION WELDING A BLADE ONTO A TURBINE ENGINE ROTOR DISC; CORRESPONDING INTEGRAL BLADE DISC - A method of friction welding an airfoil ( | 10-22-2015 |
| 20150292623 | LOW-COST HIGH-PERFORMANCE ANNULAR METALLIC SEAL FOR HIGH PRESSURES AND LARGE DIAMETERS - An annular metal static seal ( | 10-15-2015 |
| 20150292544 | DEVICE FOR LOCKING A NUT - The invention relates to a device for locking a nut ( | 10-15-2015 |
| 20150292439 | INJECTOR ELEMENT - The invention relates to the field of injectors, and in particular to an injector element ( | 10-15-2015 |
| 20150292412 | FUEL INJECTOR FOR A TURBINE ENGINE - A fuel injector for a turbine engine, the injector including a body including a primary fuel circuit and a secondary fuel circuit fed by a metering valve. A leakage channel extends from a zone in fluid flow connection with the primary circuit to a zone in fluid flow connection with the secondary circuit. The leakage channel is configured to be open in a closed position of the metering valve and to be closed by the metering valve moving. | 10-15-2015 |
| 20150292407 | REMOVABLE ACOUSTIC PANELS FOR TURBOJET ENGINE CASING - An acoustic panel intended to be fixed internally to a fan casing of a turbojet engine, including an exterior face and an interior face which are curved about an axis, and two axially opposed transverse faces, the exterior curved face having at least one first recess on the side of a first transverse face and at least one second recess on the side of the opposite transverse face, said recesses each an attachment, in which said recesses do not open onto the interior curved face of the panel. Also covered are the turbojet engine including these panels and the method of mounting them. | 10-15-2015 |
| 20150290744 | A METHOD OF SURFACE MARKING A MECHANICAL PART WITH A PREDEFINED GRAPHICAL REPRESENTATION VISIBLE TO THE NAKED EYE - The invention relates to a method of surface marking a mechanical part with a predefined graphical representation, the method comprising using a laser source to apply a single laser pulse to an outside surface of a part for marking, with a mask being interposed between the laser source and the outside surface of the part, the mask having a predefined graphical representation, and the laser pulse having power flux density of at least 20 MW/cm | 10-15-2015 |
| 20150287249 | SYSTEM FOR MONITORING A SET OF COMPONENTS OF A DEVICE - The invention relates to a system for monitoring a set of components of a device such as an engine, comprising:
| 10-08-2015 |
| 20150285709 | DEVICE FOR FIXING REACTOR MODULES TO A TEST BENCH - The invention relates to a suspension device of at least one reactor module to a test bench comprising at least one suspension arm, at least one upstream fixing assembly adapted to be fixed to a ceiling or wall of the test bench, at least one downstream fixing assembly adapted to be fixed to a reactor module, said suspension arm extending between two attachment ends adapted to be respectively fixed to the upstream fixing assembly and to the downstream fixing assembly, characterized in that said arm has a flexible median area whereof at least one cross-section dimension is less than the same cross-section dimension at the level of the attachment ends, the downstream casing comprising a fall-protection device. | 10-08-2015 |
| 20150285500 | AIRCRAFT TURBOMACHINE COMBUSTION CHAMBER MODULE AND METHOD FOR DESIGNING SAME - A combustion chamber module for an aircraft turbomachine, including an annular combustion chamber in which each of primary and dilution ports of an outer annular wall, which is located at least partly in a wake of a fuel injector, has a discharge coefficient higher than that of its homologous port of an inner annular wall. A method for designing such a module includes determining wakes generated by fuel injectors, and then geometrically defining air inlet ports of coaxial walls of the combustion chamber such that an air flow rate actually entering through ports of the outer wall is substantially equal to an air flow rate entering through ports of the inner wall. | 10-08-2015 |
| 20150285262 | DEVICE AND METHOD FOR CONTROLLING THE PITCH OF BLADES - The invention concerns a device ( | 10-08-2015 |
| 20150285187 | METHOD AND A DEVICE FOR FEEDING A ROCKET ENGINE - The invention relates to a feed device for feeding a thrust chamber ( | 10-08-2015 |
| 20150285159 | METHOD AND A DEVICE FOR ADJUSTING A SETPOINT VALUE OF A PARAMETER THAT INFLUENCES THRUST FROM A GAS TURBINE ENGINE - A method of adjusting a setpoint value of at least one parameter that has an influence on thrust of a gas turbine engine propelling an aircraft during a stage of flight of the aircraft, the method including: obtaining a current value of at least one operating variable of the engine; extracting from a pre-established table a decrement value for the at least one parameter associated with the current value of the at least one operating variable of the engine; and adjusting the setpoint value of the at least one parameter by applying thereto the decrement value extracted from the table. | 10-08-2015 |
| 20150285151 | METHOD FOR MOUNTING AN ACOUSTIC PANEL IN A HOUSING OF A TURBOMACHINE AND TURBOMACHINE COMPRISING AN ACOUSTIC PANEL - A method for mounting an acoustic panel on the inner surface of an annular housing of an axial turbomachine, the cylindrical acoustic panel comprising at least one longitudinal slot so as to define two opposing ends, the method comprising: bringing the two opposing ends closer together so as to reduce the cylinder radius of the acoustic panel; inserting the acoustic panel into the fan casing when said opposing ends are close together; deploying the opposing ends so as to increase the cylinder radius of the acoustic panel; securing the acoustic panel to the housing by gluing. | 10-08-2015 |
| 20150285100 | AIR EXHAUST TUBE HOLDER IN A TURBOMACHINE - A support for carrying a tube for discharging oil-laden air from a turbine engine, the support including a radially inner annular portion for mounting around the tube, and fins extending outwards in a radial plane from the annular portion, each fin forming an angle relative to the radial direction. The fins have fastener zones at their outer peripheries, the fastener zones being inclined in the axial direction of the support so as to be suitable for fastening to an exhaust cone of the turbine engine. | 10-08-2015 |
| 20150285098 | EXHAUST HOUSING HUB FOR A TURBOMACHINE - The invention relates to an exhaust ( | 10-08-2015 |
| 20150285093 | METHOD FOR MONITORING AN IGNITION SEQUENCE OF A TURBOMACHINE ENGINE - A method for monitoring an ignition sequence of an engine, in particular a turbomachine engine, including the following steps: (i) defining an ignition time of the engine for a defined starting parameter, (ii) comparing the ignition time of the engine defined in this way with a reference ignition time expected for a reference engine and for this starting parameter, (iii) deducing an indicator of the bringing into operation of the engine, (iv) repeating steps (i) to (iii) for this starting parameter, for each bringing into operation of the engine of the sequence, and (v) on the basis of the change in the indicator, generating a degradation alert for the ignition sequence of the engine. | 10-08-2015 |
| 20150285092 | METHOD FOR DIFFERENTIATING CONTROL FAILURES IN A SYSTEM FOR CONTROLLING AN ACTUATOR, IN PARTICULAR OF A STATOR OF A GAS-TURBINE ENGINE - The present invention relates to a method for differentiating control failures in a system for controlling an actuator ( | 10-08-2015 |
| 20150285084 | PART CONSISTING OF A CERAMIC MATERIAL, COMPRISING A BASE AND A WALL - A part made of a ceramic material, including a portion forming a base and a portion forming a wall, wherein the base consists of a low-porosity ceramic material and the wall is obtained by powder sintering and includes an envelope and a core, the core being within the envelope, the porosity of the core being higher than that of the base and increasing the further it is from the base. | 10-08-2015 |
| 20150284098 | TURBOMACHINE COMPRISING A DEVICE FOR THE COOLING OF A PYLON - A turbomachine ( | 10-08-2015 |
| 20150284069 | DEVICE FOR CONTROLLING BLADE ANGLE, AND PROPELLER - The invention relates to a device ( | 10-08-2015 |
| 20150276554 | BENCH TEST, FOR THE CHARACTERIZATION OF A FLOW OF A TWO-PHASE FLUID - The invention provides a test bench for characterizing a flow of a two-phase fluid, the test bench comprising a fluid tank, a first pump suitable for taking fluid from the tank and for feeding first and second lines connected in parallel, each line being provided in succession, from upstream to downstream in the flow direction of the fluid, with: injection means for injecting air into the fluid; measurement means suitable for providing information about the proportion of the vapor phase relative to the liquid phase of the fluid; and a second pump or a Venturi. | 10-01-2015 |
| 20150275680 | SELF-CLAMPING FASTENER FOR CMC TURBINE BLADE - The invention relates to a turbine blade having an airfoil ( | 10-01-2015 |
| 20150268131 | METHOD AND A DEVICE FOR NORMALIZING VALUES OF OPERATING PARAMETERS OF AN AEROENGINE - The normalization method comprises:
| 09-24-2015 |
| 20150268073 | METHOD AND SYSTEM FOR DETERMINING THE FLOW RATE OF AIR COLLECTED FROM AN AIRCRAFT ENGINE - A method and a device for determining, in real time, the flow rate of air collected from an aircraft engine by a system for collecting air from the engine, including an acquisition device for acquiring at successive times measurements of physical quantities in respect of temperature, pressure and pressure loss, specific for the air collection system, a computing device for evaluating at each current time of the successive times a first current estimation of the flow rate of air collected from the aircraft engine on the basis of said the physical quantity measurements, the acquisition device for acquiring at the current time a minimum current air flow rate data item defined on the basis of a predetermined flow rate tables, the computing device for hybridising, at the current time, the first current air flow rate estimation and said the minimum current air flow rate data item to form a second current air flow rate estimation. | 09-24-2015 |
| 20150267555 | TURBOMACHINE CASING - A turbomachine casing including a substantially cylindrical wall and an annular one-piece acoustic insulation panel mounted inside the wall, the panel including an annular surface that is radially external opposite a radially internal annular surface of the wall, wherein the wall includes on its internal angular surface first projecting members which bear axially against second projecting members belonging to the external annular surface of the panel and which are fixed to these second members in a dismountable manner. | 09-24-2015 |
| 20150267545 | BLISK WITH LOW STRESSES AT BLADE ROOT, PREFERABLY FOR AN AIRCRAFT TURBINE ENGINE FAN - The invention relates to an assembly for an aircraft turbine engine comprising an integral element ( | 09-24-2015 |
| 20150266093 | METHOD FOR INCORPORATING ABRADABLE MATERIAL INTO A HOUSING BY ISOSTATIC PRESSING - A method of fabricating a part ( | 09-24-2015 |
| 20150263440 | SYSTEM FOR ATTACHING ELECTRICAL EQUIPMENT TO A METALLIC SUPPORT - The invention relates to a system ( | 09-17-2015 |
| 20150260102 | HEAT EXCHANGER FOR A TURBO ENGINE - The invention relates to a heat exchanger of an air circulation channel of a turbomachine, the heat exchanger being configured so as to have fluid to be cooled passing through it and including a plurality of fins protruding from a support surface, the heat exchanger being characterized in that each fin includes a base and a preferably continuous leading face which extends axially from the base in the air circulation direction while tapering from upstream to downstream along an axis parallel with the support surface. | 09-17-2015 |
| 20150260045 | PROPELLER COMPRISING A MOVEABLE DYNAMIC SCOOP - The main purpose of the invention is a propeller ( | 09-17-2015 |
| 20150258597 | METHOD FOR REDUCING THE DIAMETER OF AN OPENING - A method for reducing the diameter of an opening, including peening a perimeter of the opening. A method for correcting the permeability of a part including a plurality of openings for allowing a gaseous fluid to pass therethrough. The method identifies at least one opening with a diameter which exceeds a predetermined upper limit and reduces the excessive diameter by peening a perimeter of the opening. | 09-17-2015 |
| 20150252690 | HYDRAULIC AND ELECTRICAL INTERFACE RING FOR A TURBINE ENGINE - The disclosed subject matter relates to a hydraulic and electrical interface ring for a turbine engine, characterized in that said ring comprises fluid transfer pipes which axially pass therethrough and having axial ends that form axial interlocking means, the supporting means of at least one electrical device, and at least one electrical linking connector of the device, said connector being configured to engage by axial interlocking with a complementary electrical connector of another part. | 09-10-2015 |
| 20150252687 | TURBOMACHINE DISTRIBUTOR COMPRISING A THERMAL PROTECTION SHEET WITH A RADIAL STOP, AND ASSOCIATED THERMAL PROTECTION SHEET - A distributor of a turbomachine configured to be mounted in a housing, including: a plurality of segments; a plurality of anti-rotation pins, mounted both on a segment of the distributor and on the housing; and a thermal protection sheet, including at least one axial tab configured to radially abut against an inner face of a first anti-rotation pin, and at least one radial tab configured to axially abut against an upstream face of a second anti-rotation pin. | 09-10-2015 |
| 20150251281 | METHOD FOR RESURFACING AT LEAST ONE ARM OF AN INTERMEDIATE CASING OF A TURBOMACHINE - A method for resurfacing at least one arm of an intermediate casing of a turbomachine, such as a turbojet engine or a turboprop engine of an aircraft, including striking off at least one end of the arm to be resurfaced, resurfacing the struck-off end of the arm by adding filler metal using a short-circuit transfer MIG welding method, also called CMT (Cold Metal Transfer) method, machining the resurfaced portion of the arm so as to provide it with the required geometry. | 09-10-2015 |
| 20150248375 | MULTI-SENSOR MEASURING METHOD AND SYSTEM - The measurement system having multiple sensors for sensing the same physical magnitude comprises at least one set of n redundant sensors or of models representing the same physical magnitude in order to deliver n measurement signals, a fusion unit for performing fusion that is the result of multiplexing the n measurement signals in order to deliver a single multiplexed output signal resulting from the fusion of the n measurement signals, and a reconditioned UKF receiving the multiplexed output signal to output a signal constituting the best estimate of the measurement of the physical magnitude after rejecting signals representative of a sensor failure. | 09-03-2015 |
| 20150247412 | TURBINE ENGINE BLADE MADE OF COMPOSITE MATERIAL WITH A BULB-SHAPED ROOT - A turbine engine blade made of composite material including fiber reinforcement obtained by three dimensionally weaving yarns and densified with a matrix, the blade including an airfoil and a blade root forming a single part. The blade root includes two opposite lateral flanks that are substantially plane and that are clamped between two independent pads made of composite material, which pads are fastened against the lateral flanks of the blade root to form a blade root that is bulb-shaped. | 09-03-2015 |
| 20150240714 | TURBINE ENGINE WITH A COMBUSTION CHAMBER OUTER FLANGE OF SANDWICH TYPE - A turbine engine has inner and outer annular covers containing an annular combustion chamber and an annular nozzle ( | 08-27-2015 |
| 20150240649 | COOLED VANE OF A HIGH-PRESSURE TURBINE - The invention relates to a movable vane of a turbomachine comprising a blade ( | 08-27-2015 |
| 20150239569 | PYLON FOR MOUNTING AN ENGINE ON THE STRUCTURE OF AN AIRCRAFT - A system for pylon attachment for mounting an engine on a structure of an aircraft, or to wings of the aircraft, including a first attachment mechanism that can be secured to the pylon and a second attachment mechanism that can be secured to the structure of the aircraft. A connection mechanism connects the first and second attachment mechanism, the connection mechanism configured to allow movement of the first attachment mechanism in relation to the second attachment mechanism between first and second positions. | 08-27-2015 |
| 20150239553 | FIBER REINFORCEMENT FOR MAKING AN ELONGATE MECHANICAL PART OUT OF COMPOSITE MATERIAL - The invention relates to fiber reinforcement for making an elongate mechanical part ( | 08-27-2015 |
| 20150239183 | METHOD OF IDENTIFYING AND/OR TRACKING DEFORMATION OF A TURBINE ENGINE PART - The invention relates to a method of identifying and/or tracking deformation of a mechanical part ( | 08-27-2015 |
| 20150233463 | DEVICE FOR SEALING AN OPENING OF AN ENCLOSURE WALL FOR ACCESS TO A ROTARY SHAFT - The invention relates to a device for sealing an opening of an enclosure wall for access to a rotary shaft. The device is capable of being sealingly inserted in said opening and of being secured against the wall by securing elements. The device includes two cylindrical parts assembled slidably relative to one another, coaxially relative to the opening: a first part capable of being statically inserted in the opening, and a second part capable of being secured to the wall by the securing elements and subjected to the action of a resilient means provided between the parts and tending to axially separate the second part from the wall. | 08-20-2015 |
| 20150233324 | TWO-MODE IGNITOR AND A TWO-MODE METHOD OF INJECTION FOR IGNITING A ROCKET ENGINE - A two-mode ignitor and to a two-mode method of injection into the ignitor, which includes a feed for a first propellant, a feed for a second propellant, a feed for a high pressure fluid, a first buffer tank, a second buffer tank, a first switch device, a second switch device, and a torch-forming combustion chamber; a downstream orifice from the first buffer tank and a downstream orifice from the second buffer tank both open out into the combustion chamber; the first switch device and second switch device devices are configured respectively to connect an upstream orifice of the first buffer tank with either the first feed or with the feed for high pressure fluid, and to connect the upstream orifice of the second buffer tank either with the second feed or with the feed for the high pressure fluid. | 08-20-2015 |
| 20150231746 | METHOD FOR MANUFACTURING AT LEAST ONE METAL TURBINE ENGINE PART - A method of fabricating at least one metal part for a turbine engine, the method including the steps of casting a metal alloy by centrifuging into a permanent metal mold for making a blank; obtaining a cast blank of elongate shape and of section that is circular or polygonal; and machining the blank to make the part. | 08-20-2015 |
| 20150231699 | METHOD OF MANUFACTURING A COMPONENT COVERED WITH AN ABRADABLE COATING - A method of fabricating a part covered in an abradable coating ( | 08-20-2015 |
| 20150226087 | FAN ROTOR, IN PARTICULAR FOR A TURBINE ENGINE - A turbine engine fan rotor having a disk carrying blades, a substantially frustoconical cover mounted on the disk, and axial retention device for retaining the blades and including a ring mounted in an annular groove in the disk and forming a bearing surface for roots of the blades. The ring is festooned or crenellated and co-operates with a festooned radial annular lip of the disk. The rotor also has at least one axial tooth inserted in hollow portions of the ring and of the lip of the disk. Two coaxial parts arranged radially inside the disk have respective first and second fastener flanges for fastening to the disk, said flanges being axially interposed between the cover and the disk, being circumferentially offset relative to one another, and being fastened independently of one another to the disk. | 08-13-2015 |
| 20150226082 | INSTRUMENTED VANE - A vane intended to be mounted in a supply fluid pattern, the vane comprising:
| 08-13-2015 |
| 20150226078 | TURBINE ENGINE CASING AND ROTOR WHEEL - The invention relates to an assembly comprising a turbine engine casing and a bladed rotor wheel arranged therein. The casing presents an inside wall having a circumferential strip of abradable material. Facing the tips of the blades, the casing presents upstream the strip of abradable material, and downstream a circumferential groove. The strip of abradable material is defined downstream by the circumferential groove. The downstream end of the circumferential groove is in register with or downstream from the trailing edges of the blades. This arrangement optimizes the use of abradable material in the casings of the turbine engines. | 08-13-2015 |
| 20150226074 | TURBOMACHINE GUIDE VANES WITH IMPROVED VANE PROFILE - A set of turbomachine guide vanes including plural vanes arranged around an annulus, each vane having a leading edge extending between root and tip ends, the leading edge offset between these two ends being greater than 10% of the blade height. A tangential stacking of the guide vanes towards the suction face side, the curve of tangential stacking, of the position, in the direction tangential to the annulus, of centers of gravity of successive vane cross sections along the vane height, is a curve that increases constantly towards the suction face side. The curve, near the vane tip end, has an accentuated gradient towards the suction face side compared with the rest of the curve, and has a mean gradient near the vane tip end that is greater than at least 1.2 times the mean gradient of the curve over the portion between 30% and 90% of the vane height. | 08-13-2015 |
| 20150224693 | INJECTION MOLD CORE FOR MAKING A PART OUT OF COMPOSITE MATERIAL, THE PART HAVING A CLOSED BOX - The invention provides an injection mold core ( | 08-13-2015 |
| 20150224684 | DEVICE AND METHOD FOR PRODUCING PREFORMS - The invention relates to an appliance ( | 08-13-2015 |
| 20150224568 | SHELL MOULD HAVING A HEAT SHIELD - A field of casting, and more particularly to a shell mold, and also to methods of fabricating and using such a shell mold. This shell mold includes a central cylinder, a plurality of molding cavities arranged in an assembly around the central cylinder, and at least one heat shield that is substantially perpendicular to the main axis. The central cylinder extends along a main axis between a casting cup and a base. Each molding cavity is connected to the casting cup by at least one feed channel, and also, by a baffle-selector with a starter in the base. The at least one heat shield completely surrounds each molding cavity in a plane that is substantially perpendicular to the main axis. | 08-13-2015 |
| 20150224567 | CASTING PATTERN - A casting pattern for a lost-pattern casting, the pattern being in a shape of a turbine engine blade with a root and a body on either side of a platform that is substantially perpendicular to a main axis of the blade, and a method of producing a shell mold from the pattern, and a casting method using the shell mold. The blade body presents a pressure side, a suction side, a leading edge, and a trailing edge. The pattern also includes an expansion strip adjacent to the trailing edge, and a refractory core embedded in the pattern but presenting, both on the pressure side and on the suction side, a respective flush varnished surface between the trailing edge and the expansion strip. A web extends between the platform and the expansion strip and presents a free edge between them. | 08-13-2015 |
| 20150222097 | SEMICONDUCTOR IGNITER PLUG FOR AN AIRCRAFT TURBOMACHINE, COMPRISING SCOOPS FOR DISCHARGING POSSIBLE FUEL RESIDUES - The invention relates to an igniter plug ( | 08-06-2015 |
| 20150219539 | METHOD OF DETERMINING THE NON-PROPAGATION THRESHOLD OF FATIGUE CRACKS AT HIGH FREQUENCY - A method of determining the non-propagation threshold of fatigue cracks at high frequency, wherein cyclic loading is exerted on at least one testpiece having an elliptical hole in a testpiece zone, the elliptical hole having a notch at one end and the testpiece being held between two rigid masses with two rigid pre-stress plates being arranged on either side of the at least one testpiece and each fastened at its two ends to the two rigid masses, which cyclic loading is at a frequency that is selected as being equal to the resonant frequency of the assembly including the testpiece, the masses, and the stress plates, so as to generate a fatigue crack from the notch, and then once it has been observed that the crack has stopped propagating, the final length of the crack is measured and a chart is used to determine the non-propagation threshold. | 08-06-2015 |
| 20150219528 | METHOD FOR MONITORING A THRUST FAULT OF AN AIRCRAFT TURBOFAN - A method for monitoring a thrust fault of a turbofan during a modification of the thrust setting of the turbofan, the method including a step of processing the thrust setting via a filtering function and a transient-phase model such as to obtain a modelled thrust, a step of comparing the modelled thrust to the actual thrust such as to determine a thrust difference, a step of comparing the thrust difference to an alarm threshold; and a step of emitting an alarm in the event of exceeding the alarm threshold, wherein at a given iteration, in which the prior modelled thrust is known, the transient-phase model provides a time constant in accordance with the prior modelled thrust, and the filtering function provides a modelled thrust in accordance with the time constant obtained, the prior modelled thrust and the thrust setting. | 08-06-2015 |
| 20150219014 | DEVICE FOR THE TRANSFER OF HEAT BETWEEN A LUBRICATION PIPE AND A TURBOMACHINE BLADE PITCH ACTUATOR CONTROL HYDRAULIC PIPE - An aircraft turbomachine including a lubricant circulation pipe and a hydraulic pipe for controlling an actuator for changing a pitch of blades of a propeller of the turbomachine. The assembly, integrated to a receiver of the turbomachine, further includes a mechanism forming a thermal bridge between the lubricant circulation pipe and the hydraulic pipe. | 08-06-2015 |
| 20150217854 | TURBINE ENGINE HAVING A PAIR OF PROPELLERS FOR AN AIRCRAFT - The turbine engine includes respective systems for changing the pitch of the propeller blades, the system ( | 08-06-2015 |
| 20150212013 | METHOD OF CHARACTERIZING AN ARTICLE MADE OF COMPOSITE MATERIAL - A characterization method for characterizing an article made of composite material having woven, braided, or sewn fiber reinforcement, the method including a determination step of using X-ray tomography to determine gray levels of at least a portion of the article, followed by an exploitation step of exploiting the gray levels to obtain information concerning the weaving by distinguishing between at least the free matrix and the threads of fibers mixed with the matrix, the threads being considered as being a material that is homogeneous. | 07-30-2015 |
| 20150211801 | HEAT EXCHANGER OF A TURBOMACHINE - The invention relates to a heat exchanger for an air circulation channel of a turbomachine, with the heat exchanger being configured to be passed through by a fluid to be cooled and comprises a plurality of fins protruding with respect to a support surface, each fin extends axially over a length in the direction of the circulation of air and comprises a leading edge and a trailing edge, with the heat exchanger characterised in that each fin further comprises a central body, between the leading edge and the trailing edge, with the central body having in a plane parallel to the support surface a curved central profile. | 07-30-2015 |
| 20150211382 | ABRADABLE COATING MADE OF A MATERIAL HAVING A LOW SURFACE ROUGHNESS - The present invention relates to an abradable coating for a turbine engine part, characterized by the fact that said coating includes a layer made of an abradable material, the surface asperities of which are filled with thermally bonded ceramic grains, forming a smooth, free surface having a low roughness | 07-30-2015 |
| 20150209861 | METHOD OF PREHEATING A SET OF SHELL MOLDS FOR LOST-WAX CASTING - The invention relates to a method of preheating a set of N shell molds ( | 07-30-2015 |
| 20150206458 | DEVICE FOR SIMULATING THE INGESTION OF CHUNKS OF ICE BY AN ENGINE - A device for simulating an ingestion of chunks of ice by an engine, including: a main tank forming a cavity for a fuel, and connected to an inlet of the engine by a pipe; an injection system including an injection member arranged in the pipe; a secondary tank forming a cavity for a fuel, which tank is connected to the injection system by a selector member; and a reservoir connected firstly to a reserve of water and secondly to the injection system via the selector member. The selector member is configured to place the injection system selectively in communication with the secondary tank or with the reservoir to inject a determined quantity of water into the engine. | 07-23-2015 |
| 20150205655 | ENGINE-CONTROL COMPUTER AND METHOD FOR DETECTING FAILURES OF SUCH A COMPUTER - An engine-control computer including switches wherein switch voltage type outputs are configured to control some actuators and a device for detecting internal or external failures with respect to the computer including: a circuit for acquisition of current flowing in such a switch; a circuit for acquisition of an input voltage of the switch; a circuit for acquisition of an output voltage of the switch; an electrical monitoring circuit wherein the three inputs are connected respectively to outputs of each of the three circuits, which tests current and voltage level, delivers an invalid status if the current is less than a defined limit current and if the voltage is less than a defined threshold voltage and configured to detect an external failure with respect to the computer. A method detects failures of such a computer. | 07-23-2015 |
| 20150204597 | COOLING METHOD - A cooling method for cooling a device connected to a cryogenic tank via a main admission duct for feeding the device with cryogenic fluid once the device is cooled. In contrast, during cooling, a cryogenic fluid is introduced into the device via a cooling admission duct that is different from the main admission duct and that presents a flow section that is narrower than the flow section of the main admission duct. | 07-23-2015 |
| 20150204339 | SYSTEM FOR HOLDING BLADES AND ASSEMBLY METHOD - The invention relates to a blower ( | 07-23-2015 |
| 20150204246 | DRIVE GEARBOX ON A TURBOMACHINE, CONSISTING OF A DRIVE TRAIN WITH GEAR LINES EXTENDING INTO NON-PARALLEL PLANES - This A gearbox to be mounted on a turbomachine and driven by a radial drive shaft of the latter. The gearbox has a three-dimensional or sinuous shape, which can house a large quantity of equipment to be driven, without occupying a large amount of space in any dimension, since the gearbox remains close to the turbomachine and the equipment can be distributed over a large surface. The drive train of gears successively extends into several non-parallel planes and comprises an axial branch on the turbomachine and a branch forming an arc of circle around the turbomachine. | 07-23-2015 |
| 20150204240 | CONSTANT-VOLUME COMBUSTION (CVC) CHAMBER FOR AN AIRCRAFT TURBINE ENGINE INCLUDING AN INTAKE/EXHAUST VALVE HAVING A SPHERICAL PLUG - A constant-volume combustion chamber for an aircraft turbine engine, including a compressed gas intake valve configured to adopt an open position and a closed position, and in the closed position blocking intake of compressed gas into the chamber, and a combusted gas exhaust valve configured to adopt a closed position, in the closed position blocking exhaust of combusted gas outside the chamber. At least one of the intake and exhaust valves includes at least one spherical plug. | 07-23-2015 |
| 20150204198 | METHOD OF MEASURING THE TEMPERATURE REACHED BY A PART, IN PARTICULAR A TURBINE ENGINE PART - A method of measuring temperature reached by a part, for example a turbine engine part, in operation, the method including: mechanically treating the part; oxidizing the part; and depositing a layer including a temperature indicator for indicating the temperature reached by the part in operation. | 07-23-2015 |
| 20150198565 | METHOD OF CHARACTERIZING AN OBJECT INCLUDING, AT LEAST LOCALLY, A PLANE OF SYMMETRY - A method of characterizing an object that includes, at least locally, a plane of symmetry, the method including performing at least one observation of ultrasound transmitted through the object, each observation being performed on an axis perpendicular to the plane of symmetry, each observation resulting from an emission of ultrasound generated along a respective one of the axes and meeting the object along the axis at an angle of incidence other than normal, the ultrasound meeting the object to follow a path that is symmetrical relative to the plane of symmetry. | 07-16-2015 |
| 20150198221 | BALANCING DEVICE AND METHOD - A balancing device including a nut having an internal thread, and a countersunk collar is disclosed. The countersunk collar has a through-hole with a diameter greater than the diameter of the internal thread of the nut. The countersunk collar includes a balancing weight. | 07-16-2015 |
| 20150198065 | TURBOMACHINE ASSEMBLY COMPRISING TWO BODIES AND MEANS FOR GUIDING A FLUID FLOWING FROM ONE BODY TO THE OTHER - The primary subject-matter of the invention is a turbomachine assembly ( | 07-16-2015 |
| 20150198060 | TOOLING FOR REMOVING SAND FROM A TURBINE ENGINE - Tooling for removing sand from a turbine engine, such as an airplane turbojet, the tooling including at least one endoscopic display device including a display and a duct having light guide and image transmission device mounted therein, a suction device having a suction device connected to a suction duct fastened to the duct of a display device, and a plasma jet generator device including a plasma torch connected to gas supply and electricity power suitable for operating the plasma torch, the plasma torch being fastened to the duct of an above-mentioned display device. | 07-16-2015 |
| 20150192499 | METHOD FOR DETECTING DETERIORATION IN A TURBOMACHINE BY MONITORING THE PERFORMANCE OF SAID TURBOMACHINE - A method for detecting degradation of a turbine engine by monitoring performance of the turbine engine, the turbine engine including plural functional modules, the method including: measuring plural physical parameters of the turbine engine to form a current performance index for the turbine engine; calculating plural degraded performance indices for the turbine engine, assuming that, for each degraded performance index, only one functional module of the turbine engine has degraded; calculating plural cost indices corresponding to the difference between the current performance index and a degraded performance index; determining an optimum cost index corresponding to the one with a lowest value for all the degraded performance indices; and detecting degradation of the module of the turbine engine, the degraded performance index of which is associated with optimum cost index. | 07-09-2015 |
| 20150192033 | COOLING OF AN OIL CIRCUIT OF A TURBOMACHINE - A turbomachine or a turbojet engine or a turboprop engine of an aircraft, including at least one oil circuit and a cooling mechanism including a refrigerant circuit including a first heat exchanger configured to exchange heat between the refrigerant and air and forming a condenser, a second heat exchanger configured to exchange heat between the refrigerant and the oil of the oil circuit and forming an evaporator, an expander mounted downstream from the first exchanger and upstream from the second exchanger, in a direction in which the refrigerant circulates, and a compressor mounted downstream from the second exchanger and upstream from the first exchanger. | 07-09-2015 |
| 20150192032 | METHOD FOR MANUFACTURING A TURBOMACHINE CASING FROM A COMPOSITE MATERIAL AND ASSOCIATED CASING - A method for manufacturing a turbomachine casing from composite material including: creating a semi-rigid protective layer from dry glass fibers that protects against galvanic corrosion, arranging the protective layer on a profiled mandrel by applying the protective layer against the annular radial flange thereof, forming and densifying the fibrous reinforcement on the mandrel while covering the protective layer. | 07-09-2015 |
| 20150192024 | TURBOMACHINE VANE HAVING AN AIRFOIL DESIGNED TO PROVIDE IMPROVED AERODYNAMIC AND MECHANICAL PROPERTIES - A turbomachine vane including a plurality of vane sections stacked along a radial axis, each vane section extending along a longitudinal axis between a leading edge and a trailing edge, and along a tangential axis between an active surface and a passive surface, the vane sections being distributed according to longitudinal and tangential distribution laws defining positioning of respective centers of gravity thereof in relation to the longitudinal and tangential axes according to a height of the vane extending from a foot of the vane to a top thereof. Each of the longitudinal and tangential distribution laws involves a change in direction of the slope at between 90% and 100% of the height of the vane. | 07-09-2015 |
| 20150186568 | FORECASTING MAINTENANCE OPERATIONS TO BE APPLIED TO AN ENGINE - A method and system forecasting maintenance operations to be applied to an engine or a part of the engine including a set of components, the system including: a processor building a lifetime model for each component of the set of components; a processor analysing the lifetime model associated with each component to build a set of failure models corresponding to the set of components, each component being associated with a failure model defining an inter-inspection interval reflecting an advanced degradation risk rate lower than a predetermined safety threshold; a processor defining a maintenance strategy including opportunistic inspections on the set of components; and a processor iteratively simulating maintenance actions on the set of components by using the set of failure models and the maintenance strategy to build a global model of relaxed maintenance operations which takes the opportunistic inspections into account while fulfilling a predetermined safety threshold of each component. | 07-02-2015 |
| 20150184531 | GASKET DEVICE FOR THE BEARING OF A TURBOMACHINE, COMPRISING TWO ELASTIC SEALS - A gasket device for a turbomachine bearing, configured to separate an oil enclosure and an air enclosure from the turbomachine, including a segmenting gasket for providing most of tightness of the device and a supporting jacket for holding the segmented gasket. The supporting jacket includes a first groove accommodating a first elastic seal for centering the supporting jacket. The supporting jacket includes a second groove accommodating a second elastic seal for centering the supporting jacket, or aligning the axis of the supporting jacket with the axis of the rotor. | 07-02-2015 |
| 20150184526 | CORROSION-RESISTANT ABRADABLE COVERING - A corrosion-resistant abradable covering to adhesively bond to a wear portion of a structural part, the covering including at least a polyester-based matrix and an aluminum alloy filler that are molded together. | 07-02-2015 |
| 20150183387 | DEVICE FOR VENTILATING AND SUPPLYING ELECTRICAL POWER TO AN AIRCRAFT ENGINE COMPUTER - A device for ventilating and electrically powering a computer of an engine of an aircraft, the device including a feed mechanism feeding air to a proximity of the computer and a fan connected to a drive mechanism and configured to generate a stream of air for ventilating the computer. The fan is mounted in the air feed mechanism, and the drive mechanism includes an electrical machine configured to operate as a motor for driving the fan, and as a generator for powering the computer, a rotor of the machine when operating as a generator being driven by the fan, which is itself driven by a stream of air flowing in or leaving the air feed mechanism. | 07-02-2015 |
| 20150179383 | POWER SUPPLY CIRCUIT - A power supply circuit for electronic equipment that might be affected by overheating or by a fire, the power supply circuit including a bistable switch switchable between a first state in which the input terminal is connected to the output terminal, and a second state in which the input terminal is not connected to the output terminal, a first coil, and a second coil, the bistable switch being configured to switch to the first state when the magnetic field induced by the second coil is greater than the magnetic field induced by the first coil, and to switch to the second state when the magnetic field induced by the first coil is greater than the magnetic field induced by the second coil. | 06-25-2015 |
| 20150177101 | DETECTION DEVICE FOR INITIATING FAILURES OF A MECHANICAL SYSTEM - The invention relates to a method and a device for detection of initiating failures in a mechanical system, comprising:
| 06-25-2015 |
| 20150176419 | PART TO MODIFY THE PROFILE OF AN AERODYNAMIC JET - A part to modify the profile of an aerodynamic jet, including: a first face configured to be secured on the aerodynamic jet, and a second face defining a modified aerodynamic jet profile, configured to modify an initial profile of the aerodynamic jet. | 06-25-2015 |
| 20150176415 | BLADE COMPRISING A SUPPORT, PROVIDED WITH A PORTION WITH A DEPRESSION - The support ( | 06-25-2015 |
| 20150175269 | CASING FOR A PROPULSION UNIT - An aircraft propulsion unit comprising an engine and a nacelle including an axisymmetric casing ( | 06-25-2015 |
| 20150175268 | SUSPENSION FOR A TURBINE ENGINE - A rear suspension for attaching an aeroengine ( | 06-25-2015 |
| 20150174676 | MULTIPURPOSE ELECTRICAL DISCHARGE MACHINING TOOL FOR A RINGSECTOR - The invention relates to an electrical discharge machining tool of a ring sector for an aircraft turbomachine. The ring sector comprises an abradable member and a support element to which the abradable member is fixed. The ring sector comprises one or more gripping holes opening on a radially outer surface of a central body of the support element. The machining tool comprises at least two machining sets chosen from groove, notch, opening, length-cutting, or abradable element electro-machining sets. The machining tool also has a gripping device for the ring sector by means of the gripping holes. The gripping device is configured to move the ring sector from one of the electro-machining sets to another of the electro-machining sets. | 06-25-2015 |
| 20150174646 | DEVICE FOR HANDLING WAX SPIDER-LIKE SPRUES - A device for handling spider-like sprues, includes a first support forming a first plane, the first support including a supporting device for supporting a wax spider-like sprue; a second support forming a second plane, the first support and the second support forming a first pre-determined angle (α | 06-25-2015 |
| 20150159771 | VALVE FOR FUEL CIRCUIT OF AN AIRCRAFT ENGINE - The invention relates to a motive flow valve ( | 06-11-2015 |
| 20150159554 | AIRCRAFT TURBOFAN COMPRISING AN INTERMEDIATE RING WITH SIMPLIFIED DOWNSTREAM SUPPORT - This invention relates to an assembly ( | 06-11-2015 |
| 20150159496 | SEALING RING FOR A TURBINE STAGE OF AN AIRCRAFT TURBOMACHINE, COMPRISING SLOTTED ANTI-ROTATION PEGS - A sealing ring configured to be pressed against a rotor disc of a turbine stage for an aircraft turbomachine, the ring including a plurality of anti-rotation pegs which prevent it from rotating in relation to the rotor disc, each peg protruding axially from a ring body and including two opposite circumferential-end surfaces, respectively configured to be located facing two directly consecutive blades carried on the rotor disc. An axially opening slot passes radially through at least one of the anti-rotation pegs. | 06-11-2015 |
| 20150158146 | METHOD FOR COMPACTING ANODIC PAINTS, INCLUDING THE COLLISION OF SANDBLASTING JETS - A method for compacting anodic paints by sandblasting, the method including directing at least two jets of an abrasive material toward a part covered with the paint, the jets being directed in a convergent manner and meeting at a focal point, and the focal point is located upstream from the part. | 06-11-2015 |
| 20150154505 | INFORMATION PROCESSING SYSTEM AND METHOD FOR MONITORING A COMPLEX SYSTEM - A data processor system for monitoring a complex system, the processor system configured to receive a plurality of pieces of state information and to merge at least the pieces of state information into a piece of failure information, at least one of the pieces of state information being associated with a confidence flag, and the piece of failure information also being associated with a confidence flag. The system performs the merging by implementing a fuzzy logic technique to produce the piece of failure information while taking account of the respective confidence flag of the pieces of state information and to produce the confidence flag associated with the failure information. | 06-04-2015 |
| 20150152918 | BEARING CAGE WITH A PERIPHERAL VIBRATION DAMPING RING - The invention relates to an annular bearing cage for a roller bearing of a turbine machine rotating shaft. The bearing cage comprises a vibration damping ring corresponding to deformation modes of the bearing cage. The bearing cage also comprises at least one external rim. The external rim comprises an at least partially annular housing that extends around a central axis of the bearing cage. The damping ring is located in the housing. | 06-04-2015 |
| 20150152880 | AIRPLANE TURBOJET FAN BLADE OF CAMBERED PROFILE IN ITS ROOT SECTIONS - A fan blade for an airplane turbojet, the blade including an airfoil extending axially between a leading edge and a trailing edge and including a plurality of airfoil sections stacked radially between a root section and a tip section. All of the airfoil sections situated between the root section and an airfoil section situated at a radial height corresponding to 30% of a total radial height of the airfoil possess a skeleton curve having a point of inflection. | 06-04-2015 |
| 20150152790 | METHOD AND DEVICE FOR ADJUSTING A THRESHOLD VALUE OF A FUEL FLOW RATE - A method of adjusting a fuel flow rate in a turbine engine propelling an aircraft, including: obtaining a first estimate of a flow rate of fuel injected into a combustion chamber of the turbine engine propelling an aircraft and as delivered by a fuel metering device of the turbine engine; obtaining a second estimate of the fuel flow rate, which second estimate is more accurate than the first estimate for at least one range of fuel flow rate values and being delivered by an estimator device having a flow meter; and adjusting the fuel flow rate threshold value with help of a difference evaluated between the first estimate and the second estimate, the threshold value being for use in an open loop for regulating the turbine engine. | 06-04-2015 |
| 20150152788 | GAS TURBINE ENGINE COMPRISING AN EXHAUST CONE ATTACHED TO THE EXHAUST CASING - An assembly including an exhaust casing and an exhaust cone for a gas turbine engine, each including an axial annular flange, the two flanges being inserted into one another, one being radially external and the other radially internal, and held together by a mechanical attachment, and the assembly further including a guide by which, during operation of assembling the annular flanges to each other, the exhaust cone is in a predetermined angular position relative to the exhaust casing. | 06-04-2015 |
