| SNECMA Patent applications |
| Patent application number | Title | Published |
|---|
| 20120134822 | HUB FOR A PROPELLER HAVING VARIABLE PITCH BLADES - A hub for a propeller having variable pitch blades for a turbine engine, for example for a propfan turbine engine. The propeller hub includes: a polygonal ring having substantially radial cylindrical housings distributed about a central axis of the ring for receiving the blades; a rotor element for the turbine of the turbine engine; a supporting flange attached to the ring so as to connect the ring to the rotor element; and a plurality of backup retaining members linked to the rotor element, and each of which includes at least one bearing surface opposite an outer surface of the ring with a radial spacing. | 05-31-2012 |
| 20120134788 | LOW PRESSURE TURBINE FOR AN AIRCRAFT TURBOMACHINE, COMPRISING A SEGMENTED NOZZLE WITH AN IMPROVED DESIGN - The invention relates to a low pressure turbine ( | 05-31-2012 |
| 20120132326 | METHOD FOR PRODUCING MARTENSITIC STEEL WITH MIXED HARDENING - A method of producing a martensitic steel including a content of other metals such that it can be hardened by intermetallic compound and carbide precipitation, with an Al content of between 0.4% and 3%. The heat shaping temperature of a last heat shaping pass of the steel is lower than the solubility temperature of aluminum nitrides in the steel, and a treatment temperature for each potential heat treatment after the last heat shaping pass is lower than the solid-state solubility temperature of the aluminum nitrides in the steel. | 05-31-2012 |
| 20120131903 | ROCKET ENGINE WITH CRYOGENIC PROPELLANTS - A cryogenic-propellant rocket engine includes: at least a first tank for a first liquid propellant; a second tank for a second liquid propellant; a third tank for an inert fluid; an axisymmetrical nozzle including a combustion chamber, a device for injecting first and second liquid propellants into the combustion chamber, a nozzle throat, and a divergent section; and a heater device including at least one duct for conveying the inert fluid and arranged outside the nozzle in immediate proximity thereof, but without making contact therewith, to recover energy of thermal radiation emitted when the rocket engine is in operation and to heat the inert fluid. | 05-31-2012 |
| 20120128934 | PART COMPRISING A SUBSTRATE CARRYING A CERAMIC COATING LAYER - The invention relates to a part comprising a substrate made of an electron-conducting material and a coating over at least a portion of the surface of the substrate, the coating comprising a ceramic coating layer. In characteristic manner, said coating layer is based on cerium oxides and said coating layer presents oxygen vacancies at a concentration greater than or equal to 1×10 | 05-24-2012 |
| 20120128503 | PRESTRESSING DEVICE HAVING RADIAL ACTIVITY - A prestressing device extending about an axis between a first plane that is substantially perpendicular to the axis and a second plane that is substantially parallel to the first plane and axially offset relative to the latter. The device includes a first annular body extending in the first plane, and a first series of at least three tabs, each of which is connected to the first body and extending in an essentially radial direction, each of the tabs of the first series including a planar surface extending in the second plane. This arrangement ensures surface contact between the parts of the elements to be subjected to prestressing. The device can be used for example for a rotor, and for example for a rotor of an unducted propeller for a turbine engine. | 05-24-2012 |
| 20120128490 | PRESTRESSING DEVICE HAVING CIRCUMFERENTIAL ACTIVITY - A prestressing device extending about an axis between a first plane and a second plane, the first plane being located at a predetermined distance from the second plane, each plane being perpendicular to the axis. The device includes at least three deformation areas. The deformation areas extend in the first plane. The device further includes, between each deformation area, a planar contact surface extending in the second plane. | 05-24-2012 |
| 20120128482 | OUTER SHELL SECTOR FOR A BLADED RING FOR AN AIRCRAFT TURBOMACHINE STATOR, INCLUDING VIBRATION DAMPING SHIMS - An assembly forming an outer shell sector, for a bladed ring sector configured to be used on a compressor or turbine stator in an aircraft turbomachine, including a plurality of elementary sectors and vibration damping shims each of them being inserted between two elementary sectors associated with it. A profile of each vibration damping shim is approximately the same as a profile of the elementary sectors. | 05-24-2012 |
| 20120128481 | ANTI-WEAR DEVICE FOR THE BLADES OF A TURBINE DISTRIBUTOR IN AN AERONAUTICAL TURBINE ENGINE - A blade sector of a turbine distributor to be carried by a turbine casing of an aeronautical turbine engine, including a front connection mechanism and a rear connection mechanism, wherein the front connection mechanism is adapted so as to bear against a holder carried by the turbine casing. The sector further includes an anti-wear device formed by a piece of a metal material surrounding the front end of the front connection mechanism and provided between the front connection mechanism and the holder to ensure a sliding contact between the two parts. The anti-wear device is axially maintained in position on the blade sector using an attachment mechanism engaging with the front connection mechanism. | 05-24-2012 |
| 20120128476 | NOZZLE STAGE FOR A TURBINE ENGINE - A nozzle stage for a turbine engine includes two substantially cylindrical rings, respectively an inner ring and an outer ring, with, extending between them: vanes carried by a first one of the rings; vanes carried by the second ring; and spacer-forming vanes interconnecting the two rings; the vanes of the first and second rings being arranged in alternation. | 05-24-2012 |
| 20120126484 | SEALING SYSTEM WITH ANNULAR BRUSH SEAL - The invention concerns a system for providing a seal between two volumes (V | 05-24-2012 |
| 20120125778 | METHOD OF FABRICATING A THERMAL BARRIER - The invention relates to a method of fabricating a thermal barrier comprising a ceramic coating layer covering at least a portion of the structure of a substrate, wherein the ceramic coating layer is deposited on the substrate solely by a cathodic electrodeposition process between at least one cathode ( | 05-24-2012 |
| 20120124834 | METHOD FOR MANUFACTURING A FORGED PART WITH ADAPTIVE POLISHING - A method for manufacturing a part by forging, including producing a semifinished part by precision forging and polishing the part by an abrasive strip, compliant geometric characteristics of the part to be obtained being predetermined in a theoretical model. The method includes: measuring the geometrical characteristics of the semifinished part after the forging operations and comparing the characteristics with the theoretical model; determining noncompliant areas on the surface of the part; determining the amount of material to be removed from each noncompliant area to make the area compliant; and polishing the part using the abrasive strip, controlling the strip so as to remove the amount of material from each noncompliant area. The method can be used for example for polishing turbine engine fan blades. | 05-24-2012 |
| 20120122631 | METHOD AND SYSTEM FOR CONTROLLING AIRCRAFT ENGINE STARTER/GENERATOR - A system and a method for controlling an aircraft engine starter/generator. The system includes an AGB of fixed gear ratio for coupling mechanically to a turbine shaft of the engine to enable the engine to be started, a gearbox having multiple gear ratios mechanically coupled to a gearwheel of the AGB, a starter/generator mechanically coupled to a gearwheel of the gearbox, and a controller to cause the gear ratio of the gearbox to be changed as a function of the mode of operation of the starter/generator. | 05-17-2012 |
| 20120121428 | BLADE RETENTION DISK - A blade retention disk includes, on its external surface, a peripheral annular groove configured to receive a plurality of blade roots of the hammer attachment type, the peripheral annular groove including a loading orifice intended for the introduction of blade roots inside the peripheral annular groove. The retention disk also includes: a crown covering the peripheral annular groove; a crown centering device to center the crown, the crown centering device and the crown forming an air supply enclosure from the bottom of the peripheral annular groove; at least one orifice opening in the air supply enclosure, the orifice being configured to introduce cooling air into the air supply enclosure. The blade retention disk finds a direct application in the field of low pressure turbines for aircraft turbine engines. | 05-17-2012 |
| 20120119056 | BEAM FOR SUSPENDING A TURBOSHAFT ENGINE FROM AN AIRCRAFT STRUCTURE - A beam for suspending a turboshaft engine from an aircraft structure, including a first attachment mechanism configured to be secured to the aircraft structure and at least one second attachment mechanism configured to be secured to the engine. The beam is at least partially made from a metal-matrix composite material including reinforcing fibres. In one embodiment, the beam takes a form of a circle arc. | 05-17-2012 |
| 20120118398 | TURBOMACHINE NOZZLE COWL HAVING PATTERNS WITH LATERAL FINS FOR REDUCING JET NOISE - An annular cowl for a turbomachine nozzle, the cowl including a plurality of patterns arranged to extend a trailing edge of the cowl and circumferentially spaced apart from one another. Each pattern has an outline of substantially polygonal shape with a base formed by a portion of the trailing edge of the cowl and at least one vertex that is spaced downstream from the base and that is connected thereto by lateral edges, and in each of its lateral edges, each pattern includes at least one fin, each fin being inclined radially relative to the pattern in a plane that is inclined at an angle lying in the range 0° to 45° relative to a radial direction. | 05-17-2012 |
| 20120109486 | METHOD AND A DEVICE FOR MONITORING A REDUNDANT MEASUREMENT SYSTEM - The invention relates to monitoring a redundant measurement system of an aeroengine by means of an electronic unit. The monitoring comprises a step of obtaining first measurements of a physical magnitude measured in said engine, and a step of obtaining second measurements of said physical magnitude. According to the invention, the method includes a step of calculating detection residues as a function of differences between the first and second measurements, a step of determining a mean-jump flag, a step of determining a variance-jump flag, a step of determining a change-of-slope flag, and a step of generating a diagnostic notice as a function of said mean-jump flag, of said variance-jump flag, and of said change-of-slope flag. | 05-03-2012 |
| 20120107125 | REINFORCED FAN BLADE SHIM - A shim configured to be inserted between a fan blade root of a turbojet and a bottom of a compartment in which this root is housed, the compartment being delimited by a fan disk. The shim includes a metal stiffener including at least one external element made of an elastomer material, and including a support surface of the external element. The support surface includes at least one corrugated zone. | 05-03-2012 |
| 20120107110 | THERMAL PROTECTION COATING FOR A TURBINE-ENGINE PART, AND A METHOD OF MAKING IT - A thermal protection coating, in particular for a turbine-engine part ( | 05-03-2012 |
| 20120107088 | DEVICE AND METHOD FOR POSITIONING VARIABLE-GEOMETRY EQUIPMENT FOR A TURBOMACHINE, USING A RELATIVE-MEASUREMENT JACK - A device for controlling positioning of variable-geometry equipment of a turbomachine, including a computer, an actuator of variable geometry driven by the computer, and a drive train, the actuator including moving parts including a sensor for measuring its elongation, the drive train being connected at one of its ends to a point of attachment of the moving parts and at another end to a point of attachment of the equipment, the point of attachment moving under action of the actuator along a travel limited by an end stop and the drive train being elastically deformable under the action of the actuator when the point of attachment is against the end stop. An elongation instruction supplied by the computer to the moving parts is defined as a difference with respect to the value of the elongation of the moving parts that corresponds to contact between the point of attachment and the end stop. | 05-03-2012 |
| 20120102900 | DEOILER LAYOUT - A deoiler including a hub mounted on the vent shaft and a cover mounted on the hub between two stop faces which fix the cover avoiding the need to weld or bolt the cover. | 05-03-2012 |
| 20120101706 | METHOD AND A DEVICE FOR MONITORING A SERVO-CONTROL LOOP OF AN ACTUATOR SYSTEM FOR ACTUATING VARIABLE-GEOMETRY COMPONENTS OF A TURBOJET - A method for monitoring a servo-control loop ( | 04-26-2012 |
| 20120099989 | PROPELLER HUB - A hub of a propeller with variable-pitch blades for a turbine engine, for example for a propfan engine. The hub of the propeller includes a polygonal ring with substantially radial cylindrical recesses distributed about a central axis of the ring for receiving the blades, a turbine rotor element of the turbine engine, and a securing flange that is attached to the ring so as to connect the ring to the rotor element. The hub further includes a plurality of back-up hooks inserted with clearance in openings, the back-up hooks being connected either to the ring or to the rotor element, and the openings being connected to the other one of the two. | 04-26-2012 |
| 20120099988 | DRIVE MECHANISM FOR A PAIR OF CONTRA-ROTATING PROPELLERS THROUGH AN EPICYCLIC GEAR TRAIN - A turbine driving a planet gear and an epicyclic gear train and including a planet pinion cage and a ring driving two propellers in rotation, is connected to the planet gear through a flexible sleeve surrounding a turbine support shaft rather than through a support shaft itself to achieve a flexible assembly with a limit stop position in contact with the shaft to limit parasite internal forces applied to the epicyclic gear train without tolerating a loose assembly or breakage of the sleeve due to a condition of the limit stop after a clearance has been eliminated. | 04-26-2012 |
| 20120099987 | STATIONARY ACTUATOR DEVICE FOR CONTROLLING THE PITCH OF FAN BLADES OF A TURBOPROP - A device for controlling pitch of fan blades of a turboprop including at least one set of variable-pitch fan blades constrained to rotate with a rotary ring centered on a longitudinal axis and mechanically connected to a turbine rotor, each blade coupled for pitch adjustment to a synchronization ring. A turntable is mounted via a rotary connection to a rod of an actuator that is secured to a stationary structural element of the turboprop, the turntable being mechanically connected to the synchronization ring by a plurality of connection arms hinge-mounted on the turntable and connected to the synchronization ring such that a longitudinal movement of the turntable under drive from the actuator causes the synchronization ring to turn about the longitudinal axis. | 04-26-2012 |
| 20120099982 | TURBINE DISTRIBUTOR ELEMENT MADE OF CMC, METHOD FOR MAKING SAME, DISTRIBUTOR AND GAS TURBINE INCLUDING SAME - A turbine nozzle element including an inner annular platform sector, an outer annular platform sector, and at least one vane extending between the platform sectors and connected to both of them. The nozzle element includes a single piece of composite material including fiber reinforcement densified by a matrix that is at least partially ceramic, and the fiber reinforcement includes a fiber structure that is woven by three-dimensional or multi-layer weaving, and that presents continuity throughout the volume of the nozzle element and throughout the periphery of the vane. | 04-26-2012 |
| 20120099981 | AEROENGINE FAN CASING MADE OF COMPOSITE MATERIAL, AND A METHOD OF FABRICATING IT - An aeroengine fan casing is made of composite material comprising fiber reinforcement densified by a matrix. The casing ( | 04-26-2012 |
| 20120098531 | DEVICE FOR THE NONDESTRUCTIVE TEST OF A PART - A device for testing to detect defects at a surface or at shallow depth in a part, for example a blade root for an airplane engine fan. The device includes a probe including a sensor, the probe being hinge-mounted to the end of a handle, a guide presenting a reference surface, and a mechanism adjusting the position of the guide parallel to an axis of the handle. | 04-26-2012 |
| 20120097443 | DEVICE FOR SPACING ELECTRICAL HARNESSES IN A TURBOMACHINE - The invention relates to a spacer device for spacing electrical harnesses in a turbomachine such as an airplane turboprop or turbojet, the device comprising clips fastened on a support. A first clip is mounted on a harness via retention means for preventing the device from moving relative to the harness, and the device includes a strip mounted around the first clip in order to close it after a harness has been mounted in the clip, the strip being fastened to the support in non-releasable manner. | 04-26-2012 |
| 20120094148 | PROCESS FOR DEPOSITING A COATING FOR PROTECTION AGAINST OXIDATION AND AGAINST HOT CORROSION ON A SUPERALLOY SUBSTRATE, AND COATING OBTAINED - Process for depositing a coating for protection against oxidation and against hot corrosion on a superalloy substrate, and coating obtained | 04-19-2012 |
| 20120093652 | UNDUCTED PROPELLER WITH VARIABLE PITCH BLADES FOR A TURBOMACHINE - A turbomachine including at least one unducted propeller with variable pitch blades, the blades being carried by respective plates mounted to pivot in radial housings of a rotor element and connected to a control ring that is driven in rotation about the axis of the turbomachine together with the rotor element, and that is movable in translation along the axis to pivot the plates about their axes, the control ring being centered and guided in rotation about the axis on a mechanism that is stationary in rotation and movable in translation along the axis by an actuator carried by the stator of the turbomachine. | 04-19-2012 |
| 20120087795 | ROTOR FOR TURBOMACHINERY - A rotor includes a disc, on which are fixed vanes, and platforms between these vanes. The rotor is particularly remarkable in that the platforms are fixed securely and tightly to the disc. To this end, the disc includes between two successive vanes an upstream stop projecting axially from the upstream surface, and each platform includes: a plate, a retaining groove extending axially and in which the upstream stop of the disc is engaged, an axial stop bearing axially against the upstream surface of the disc. | 04-12-2012 |
| 20120086441 | BENCH AND A METHOD FOR MAGNETOSCOPICALLY TESTING A TURBINE ENGINE SHAFT - A bench for magnetoscopically testing a tubular part, the bench including a tool of elongate shape for inserting inside the part and carrying an endoscopic mechanism for ultraviolet illumination of the inside surface of the part and for observing any defects of the part, and an indexing mechanism co-operating by mutual engagement with external references of the tool that are regularly distributed over at least a fraction of its length to control accurately the advance and the position of the tool inside the part. | 04-12-2012 |
| 20120085861 | DEVICE FOR ACOUSTIC TREATMENT OF THE NOISE EMITTED BY A TURBOJET - The invention provides a device for acoustical treatment of the noise emitted by a bypass turbojet comprising a primary cowl having in an outer surface an inner annular acoustic treatment panel and a secondary cowl including in an inner surface an outer annular acoustic treatment panel arranged facing the inner panel. The inner and outer panels include respective central panel portions facing each other and extending axially over a common predetermined length, the length of the central panel portions lying in the range one-fifth to four-fifths of the total length of the panels, and the ratio between the acoustic resistances of the central panel portions being not less than 2. | 04-12-2012 |
| 20120085859 | SUSPENSION FOR AN ENGINE ON AN AIRCRAFT STRUT INCLUDING A SUSPENSION ARCH - A suspension for an engine on an aircraft strut, the suspension comprising a beam with a plate provided with fixing means for fixing to said strut and a suspension arch linked to the beam by at least one pivot link whose axis is intended to be parallel to the axis of the engine, the suspension arch having, at each of its ends, fixing means for fixing to a case of the engine. | 04-12-2012 |
| 20120085156 | DEVICE FOR CHECKING A TURBOMACHINE ENGINE - A device for non-destructive in situ inspection of parts of a turbine engine, the device including a stick carrying at its distal end a pivoting finger carrying at one of its ends a blade for supporting an inspection probe, and at its opposite end a skid for bearing against and/or catching on an element of the engine, the skid being movable in a direction parallel to the longitudinal axis of the finger. | 04-12-2012 |
| 20120085101 | METHOD OF TESTING A SYSTEM FOR PROTECTING A TURBOMACHINE AGAINST OVERSPEED WHILE STARTING - In a testing overspeed protection system: a) on receiving an order to start a turbomachine, an electronic regulation system (ERS) of the turbomachine sends an order to a control circuit of a fuel cutoff member to close the fuel cutoff member or to keep it in the closed position; b) the closed state of the FCM is verified on the basis of information transmitted to the ERS and representative of the position of the FCM; c) if the result of the verification in b) is positive, the ERS sends an order to the FCM control circuit to authorize opening of the FCM and enable the starting procedure to continue; and d) if the result of the verification in b) is negative, the ERS issues fault information concerning the overspeed protection system. | 04-12-2012 |
| 20120084958 | 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. | 04-12-2012 |
| 20120079832 | DEVICE AND METHOD FOR DETECTING A FAULT IN A LOW-PRESSURE FUEL PUMP OF A TURBOJET AND TURBOJET INCLUDING ONE SUCH DEVICE - A device for detecting a fault in a low-pressure fuel pump of a turbojet. The pump is driven by an accessory gearbox including a gear for mechanically driving the accessories. The device measures the vibration frequencies of the accessory gearbox and detects, from among the frequencies, at least one vibration frequency of the low-pressure fuel pump. The device allows a fault in the low-pressure fuel pump to be detected as soon as it occurs. | 04-05-2012 |
| 20120077417 | METHOD AND DEVICE FOR MACHINING THE LEADING EDGE OF A TURBINE ENGINE BLADE - A method and a device for machining the leading edge of a turbine engine blade by a machining center for which parameters are set is disclosed. The method includes: acquiring a 3D profile of the leading edge of the blade; calculating at least one characteristic of the leading edge from the 3D profile; comparing the value of the calculated characteristic with a known theoretical value of the characteristic to obtain an elementary difference for the characteristic; calculating at least one undulation of the leading edge between at least two consecutive elementary sections from the 3D profile; optimizing the elementary differences obtained as a function of the undulation; setting the parameters of the machining center as a function of the optimized elementary differences for the elementary sections to define machining passes over the leading edge; and machining the leading edge of the blade with the machining center with parameters set. | 03-29-2012 |
| 20120073259 | TURBOMACHINE HAVING AN ANNULAR COMBUSTION CHAMBER - A turbomachine including an annular combustion chamber, the combustion chamber presenting a connection flange at its downstream end for connection to an outer casing. The connection flange bears axially against the outer casing and is blocked in an axial direction by the upstream end of an inner casing of a high pressure turbine. | 03-29-2012 |
| 20120070298 | OPTIMIZED AERODYNAMIC PROFILE FOR A TURBINE BLADE, IN PARTICULAR FOR A ROTARY WHEEL OF THE SECOND STAGE OF A TURBINE - When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y,Z′ given in Table 1, in which the coordinate Z′ is the quotient D/H where D is the distance of the point under consideration from a first reference plane P | 03-22-2012 |
| 20120070292 | MOVABLE ACTUATOR DEVICE FOR CONTROLLING THE PITCH OF FAN BLADES OF A TURBOPROP - A device for controlling pitch of fan blades of a turboprop including at least one set of adjustable-pitch fan blades secured to rotate with a rotary ring centered on the longitudinal axis, and mechanically connected to a turbine rotor, each blade of the set being coupled for pitch adjustment to a synchronization ring centered on the longitudinal axis. An actuator is secured to rotate with the turbine rotor and is mechanically connected to the synchronization ring by a plurality of connection arms connected to the actuator rod and hinge-mounted on the synchronization ring such that actuating the actuator causes the synchronization ring to move in turning about the longitudinal axis. | 03-22-2012 |
| 20120070291 | PROPELLER AND SYSTEM OF COUNTER-ROTATING PROPELLERS COMPRISING IMPROVED MEANS FOR LIMITING PITCH, AND A TURBINE ENGINE COMPRISING THEM - A propeller for an aircraft turbine engine, comprising means for adjusting the pitch of the blades comprising a hydraulic actuator borne by the rotor and including a cavity and a piston displaceable in said cavity and dividing said cavity into two chambers, as well as means for limiting the stroke of the piston in order to prevent displacement of said blades in a predetermined direction beyond a predetermined limiting pitch angle, and comprising hydraulic connection means with which both chambers may be put into communication with each other as soon as the pitch angle of the blades becomes equal to said predetermined limiting pitch angle during the displacement of said blades in said predetermined direction, these hydraulic connection means being borne by said rotor of the propeller. | 03-22-2012 |
| 20120070290 | DEVICE FOR CONTROLLING THE PITCH OF FAN BLADES OF A TURBOPROP - A device for controlling pitch of fan blades of a turboprop including at least one set of adjustable-pitch fan blades secured to rotate with a rotary ring mechanically connected to a turbine rotor, each blade of the set being coupled for pitch adjustment to a synchronization ring. The device includes a rolling bearing including an inner cage slidably mounted on a turbine casing and connected to the rod of an actuator, and an outer cage that is mechanically connected to the synchronization ring by a plurality of connection arms connected to the actuator rod and hinge-mounted on the synchronization ring such that actuating the actuator causes the synchronization ring to move in turning about the longitudinal axis. | 03-22-2012 |
| 20120070289 | BELLOWS TYPE SEALING DEVICE FOR PARTITION PENETRATION BY A CONNECTING ROD OF A TURBOPROP FAN BLADE ORIENTATION CONTROL SYSTEM - The invention relates to a sealing device for the partition penetration of a connecting rod of a turboprop fan blade orientation control system. The device includes a bellows ( | 03-22-2012 |
| 20120064254 | A METHOD AND A DEVICE FOR COATING CERAMIC MATERIAL FIBERS IN METAL BY A LIQUID TECHNIQUE - A method of coating ceramic material fibers in metal using a liquid technique and a device implementing the method. The method maintains a charge of molten metal in levitation in a substantially spherical shape inside a crucible and causes a tensioned ceramic material fiber to travel at a predetermined speed between a bottom pulley and a top pulley disposed on either side of the crucible such that a portion of fiber is immersed in the charge to be covered in a metal coating. During coating, the portion of fiber that is immersed in the charge is shifted as a function of the remaining volume of the charge such that the instantaneous height of fiber that is immersed in the charge remains substantially constant throughout the coating operation. | 03-15-2012 |
| 20120063914 | LOW-PRESSURE TURBINE - A low-pressure turbine for a turbomachine including turbine disks with festooned annular flanges for fastening to a festooned annular flange of a drive cone connecting the turbine disks to a turbine shaft, solid portions of the festooned annular flanges of the turbine disks and of the drive cone being connected to peripheries of the turbine disks and of the drive cone, respectively, via concave filets that are asymmetrical. | 03-15-2012 |
| 20120063912 | PROCESS FOR SMOOTHING THE SURFACE OF A PART MADE OF CMC MATERIAL - A method of smoothing the surface of a ceramic matrix composite material part that presents a surface that is undulating and rough. The method includes depositing a refractory vitreous coating on the surface of the part, the vitreous coating essentially containing silica, alumina, baryte, and lime. | 03-15-2012 |
| 20120063907 | CIRCUMFERENTIAL BLOCKING DEVICE OF CLAMP VANES FOR TURBINE ENGINE, WITH IMPROVED RADIAL DEPLOYMENT - The invention relates to a device ( | 03-15-2012 |
| 20120063905 | BUSHING FOR A VARIABLE SET BLADE - A bushing for a variable set blade includes a cylindrical part configured to receive the blade, the root of the blade being able to rotate in the cylindrical part, and a base including: a first side able to be put in contact with a first edge of a circumferential groove of the ring, and/or a second side able to be put in contact with a second edge of the circumferential groove of the ring. At least one of the first side or second side of the base includes at least one bevel through which the first side or the second side is able to be put in contact with one of the first edge or second edge of the circumferential groove so as to block the bushing in rotation. The invention finds a particularly interesting application in the field of aircraft. | 03-15-2012 |
| 20120063904 | LEVER-ARM VIBRATION DAMPER FOR A ROTOR OF A GAS TURBINE ENGINE - A vibration damper for a rotor blade of a gas turbine engine, includes a plate for placing between an inner bearing surface and an outer bearing surface of the rotor, the bearing surfaces extending in directions that are substantially axial and being radially spaced apart from each other, the plate being folded so as to form two plate portions that are inclined relative to each other, the mass of the plate being distributed in such a manner that its center of gravity is situated on the side of one of these plate portions, the free end of the other plate portion being designed to bear radially against the inner bearing surface, and the junction zone between the two plate portions being designed to bear radially against the outer bearing surface under the effect of centrifugal force when the rotor is rotating so as to provide axial sealing against gas. | 03-15-2012 |
| 20120062214 | CONTACTLESS ELECTRICAL CONNECTOR FOR AN INDUCTION SENSOR, AND SENSOR INCLUDING SUCH A CONNECTOR - An electrical connector between an induction sensor and a cable for transmitting a signal provided by the sensor, including a current transformer with a primary coil and a mechanism for electrically coupling to the sensor, and a secondary coil with a mechanism for electrically coupling to the cable, the primary and secondary coils being attached together by a removable attachment mechanism. | 03-15-2012 |
| 20120055609 | METHOD FOR PRODUCING A TURBOMACHINE BLADE MADE FROM A COMPOSITE MATERIAL - A method of fabricating a composite-material turbomachine blade having platform incorporated therein includes separately making a blade platform element that comprises rigidified fiber reinforcement and that has a shape close to that of a platform of the blade to be fabricated, with at least one opening being formed through the platform element. The opening has the shape of the profile of the airfoil of the blade to be fabricated. Three-dimensional weaving is used to make a flexible fiber blank as a single piece that includes blade airfoil-and-root preform portions. The platform element is engaged, via its opening, on the flexible fiber blank while deforming it so as to assemble the platform element with the fiber blank. The fiber blank is shaped together with the platform element assembled thereon to obtain a blade preform of a shape that is close to the shape of the blade to be fabricated. After shaping, the blade preform is consolidated in its shape in a shaper. Additionally, final densification of the consolidated blade preform is performed in order to obtain a composite-material blade having an incorporated platform. | 03-08-2012 |
| 20120055164 | TURBOMACHINE COMBUSTION CHAMBER COMPRISING IMPROVED MEANS OF AIR SUPPLY - Annular combustion chamber ( | 03-08-2012 |
| 20120055137 | FAN BLADES WITH CYCLIC SETTING - A fan portion of a dual flow turbojet engine including a plurality of fan blades, a disk supporting the blades and configured to be rotated relative to a stator portion of the fan, along a longitudinal axis of the fan, and a system for setting the angle of attack associated with each fan blade, the systems configured such that the angle of attack of each blade varies according to a same setting law according to the angular position of the blade relative to the stator portion, along the longitudinal axis, the same setting law being periodic with a period of P=360°/n, where n is an integer at least equal to 1. | 03-08-2012 |
| 20120046896 | MONITORING PARTICLES IN A LUBRICATION SYSTEM - A process for monitoring a machine including moving pieces, a lubrication system and an electromagnetic sensor fitted with a magnet and two electrodes is disclosed. The sensor is capable of collecting particles present in the lubrication system between the electrodes. The monitoring process includes a step for obtaining measurements of resistance between the electrodes of the sensor, taken during an operating period of the machine; a step for determining from said measurements a first autoregressive mathematical model characterizing the resistance; a step for comparison between the first model and a predetermined reference model; and a step for working out an opinion on maintenance of the machine as a function of the comparison result. | 02-23-2012 |
| 20120045341 | FAN ROTOR FOR AN AIRPLANE TURBOJET - A fan rotor for an airplane turbojet including locking blade roots in the respective grooves of an airplane turbojet fan rotor. Each blade root is housed in a groove that is closed by a main latch and by an additional latch that is distinct from the main latch and that is spaced apart therefrom by a predetermined distance. | 02-23-2012 |
| 20120045334 | UNDUCTED FAN WITH VARIABLE-PITCH BLADES FOR A TURBINE ENGINE - A non-streamlined propeller including blades with a variable setting for a turbine engine, the blades of the propeller being rotatably mounted about the axes thereof in radial recesses of a rotor element, and each blade being supported by a plate held in a recess by a sectored ring, and including an inner portion mounted, by interlocking, in a groove of the plate, the ring sectors being inserted into the recess from the inside and locked by a nut screwed onto the plate. | 02-23-2012 |
| 20120042657 | METHOD AND DEVICE FOR FEEDING A TURBOMACHINE COMBUSTION CHAMBER WITH A REGULATED FLOW OF FUEL - High-pressure fuel is supplied at a controlled rate to a combustion chamber via a position-controlled valve and a variable-restriction stop-and-pressurizing cut-off valve. A value representative of the real mass flow rate of fuel as delivered is calculated by a calculation unit on the basis of information representative of the pressure difference between the inlet and the outlet of the cut-off valve and of the flow section through the cut-off valve, e.g. as represented by the position X of the slide of the cut-off valve. The position-controlled valve has a variable position that is controlled by the calculation unit as a function of the difference between the calculated value representative of the real mass flow rate and a value representative of a desired mass flow rate. | 02-23-2012 |
| 20120039738 | METHOD FOR MANUFACTURING AN ASSEMBLY INCLUDING A PLURALITY OF BLADES MOUNTED IN A PLATFORM - A method of manufacturing an assembly, including a plurality of blades mounted in a platform preparing a mixture of metal powder and thermoplastic binder, includes manufacturing the blades separately from the platform, and finishing the blades after the manufacturing. The method also includes injecting the mixture into a mold to obtain a platform blank, removing the binder from the platform blank prior to assembling the finished blades with the blank, inserting one end of the finished blades into a housing formed in the platform blank in order to assemble the assembly, and sintering the assembly comprising the platform blank and the finished blades to unify the assembly. | 02-16-2012 |
| 20120039710 | INTERMEDIATE CASING OF AIRCRAFT TURBOMACHINE INCLUDING STRUCTURAL CONNECTING ARMS WHICH PERFORM SEPARATE MECHANICAL AND AERODYNAMIC FUNCTIONS - A structural connecting arm for an intermediate casing of an aircraft turbomachine with a ducted fan, wherein the arm is configured to connect a hub and an outer ferrule of the casing, and including an aerodynamic outer surface manufactured such that the arm also forms an outlet guide vane. Multiple metal ties extend in the longitudinal direction of the arm, together with a shell made from composite material surrounding the ties and forming the aerodynamic outer surface. | 02-16-2012 |
| 20120037764 | ELBOW BRACKET FOR AERONAUTICAL EQUIPMENT - An elbow bracket for cables or pipes, supported by a structure of an aeronautical device, in which a reinforcing rib of the elbowed main plate is not assembled with the elbowed main plate by welding but by tightening following a twisting of end-pieces traversing slots of the main plate and causing an outer face of the plate to be trapped against an upper face of oblong slits partially cutting into the end-pieces. The support is faster to construct, and has sufficient resistance. | 02-16-2012 |
| 20120037280 | METHOD FOR PRODUCING A PART MADE FROM A SUPERALLOY BASED ON NICKEL AND CORRESPONDING PART - A method for manufacturing a blank part in Ni-base superalloy, wherein an alloy is prepared and heat treatments are conducted characterized in that: the said superalloy contains at least a total of 2.5% of Nb and Ta; heat treatment is conducted comprising a plurality of steps: a first step at between 850 and 1000° C. held for at least 20 minutes to precipitate the δ phase at the grain boundaries; a second step held at a temperature higher than the temperature of the first step allowing partial dissolution of the δ phase obtained at the first step; ageing treatment comprising a third step and optionally one or more additional steps at a temperature below the temperature of the first step and allowing precipitation of the hardening phases γ′ and γ″. Part thus obtained. | 02-16-2012 |
| 20120036827 | ROTATING INLET COWL FOR A TURBINE ENGINE, COMPRISING AN ECCENTRIC FORWARD END - A rotating inlet cowl for a turbine engine, having a rotation axis and for which the forward end is arranged to be eccentric relative to this rotation axis. Furthermore, a forward cone of the cowl is truncated by a truncation surface defining the forward end of the inlet cowl. | 02-16-2012 |
| 20120032809 | METHOD OF DETECTING AN ICING STATE OR A NEED FOR MAINTENANCE IN A TURBOMACHINE FUEL CIRCUIT - Detecting a state of icing in a turbomachine fuel circuit includes reading information representative of a first temperature T | 02-09-2012 |
| 20120031177 | SEALING HEAD FOR AN INSTALLATION FOR FLUID TESTS ON AN AIRCRAFT TURBINE ENGINE PART - A sealing head for an installation configured to perform fluid tests on an aircraft turbine engine part. The sealing head includes a sealing element crossed by a passage for flowing of a gas flow, the sealing element including a sealing surface configured to come into contact with a part to be tested, at an aperture of the part to be tested configured to be fed with the gas flow. The sealing head includes a mechanism centering the sealing element relatively to the aperture of the part, the centering mechanism being firmly attached to the sealing element and protruding towards the front of the surface having an outer portion surrounding the centering mechanism. | 02-09-2012 |
| 20120028056 | METHOD FOR FABRICATING A THERMAL BARRIER COVERING A SUPERALLOY METAL SUBSTRATE, AND A THERMOMECHANICAL PART RESULTING FROM THIS FABRICATION METHOD - A fabrication method of fabricating a thermal barrier covering a superalloy metal substrate, the thermal barrier including at least an underlayer and a ceramic layer, the method including: smoothing a surface state of the underlayer by at least one physicochemical and/or mechanical process prior to depositing the ceramic layer such that a number of defects presenting a peak-to-peak difference lower than or equal to 2 μm is at most five over any distance of 50 μm, and then depositing the ceramic layer. The method can be applied to turbine blades. | 02-02-2012 |
| 20120027605 | TURBOMACHINE BLADE, A ROTOR, A LOW PRESSURE TURBINE, AND A TURBOMACHINE FITTED WITH SUCH A BLADE - The invention relates to a turbomachine blade made of composite material and presenting a root with a bulb-shaped end suitable for engaging in a slot of a rotor disk. In characteristic manner, the end of the root of the blade is provided, beside one of its front faces, with a projecting portion having two symmetrical fins about the axial midplane of the root, each fin having a bearing face suitable for limiting tilting of the blade relative to the rotor disk about the axial direction. | 02-02-2012 |
| 20120027572 | TURBINE RING ASSEMBLY - A turbine ring assembly includes a ring support structure and a plurality of ring sectors, each including a single piece of ceramic matrix composite material. Each ring sector includes a first portion forming an annular base with an inside face defining an inside face of the turbine ring and an outside face from which there extends two tab-forming portions including ends that are engaged in housings in the ring support structure. The ring sectors present a section that is substantially π-shaped and the ends of the tabs are held without radial clearance by the ring support structure. The tabs can have a free length in meridian section that is not less than three times their mean width. | 02-02-2012 |
| 20120024631 | CIRCUIT AND A METHOD FOR FEEDING OIL TO ROLLING BEARINGS IN A TURBOMACHINE - The invention relates to a circuit and a method for feeding oil to rolling bearings in a turbomachine, the circuit comprising an oil supply, an oil duct connecting the supply to lubrication enclosures, each containing at least one rolling bearing, an oil feed pump located between the supply and the lubrication enclosures, an oil recovery pump connected downstream from each lubrication enclosure, and a pressurizing valve placed in the duct between the oil feed pump and the lubrication enclosures, said pressurizing valve being adapted to open when the pressure at its inlet exceeds a predetermined threshold pressure; a branch connection duct connecting the inlet of the pressurization valve to one of the lubrication enclosures in order to feed it with oil; and means for feeding the lubrication enclosures at a small oil flow rate so long as the pressure at the inlet of the pressurization valve has not reached the predetermined threshold. | 02-02-2012 |
| 20120020806 | OPTIMIZED AERODYNAMIC PROFILE FOR A TURBINE VANE, IN PARTICULAR FOR A NOZZLE OF THE FOURTH STAGE OF A TURBINE - When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y,Z′ given in Table 1, in which the coordinate Z′ is the quotient D/H where D is the distance of the point under consideration from a first reference plane PO situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P | 01-26-2012 |
| 20120020800 | OPTIMIZED AERODYNAMIC PROFILE FOR A TURBINE VANE, IN PARTICULAR FOR A NOZZLE OF THE THIRD STAGE OF A TURBINE - When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y,Z′ given in Table 1, in which the coordinate Z′ is the quotient D/H where D is the distance of the point under consideration from a first reference plane P | 01-26-2012 |
| 20120020799 | OPTIMIZED AERODYNAMIC PROFILE FOR A TURBINE BLADE, IN PARTICULAR FOR A ROTARY WHEEL OF THE THIRD STAGE OF A TURBINE - When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y,Z′ given in Table 1, in which the coordinate Z′ is the quotient D/H where D is the distance of the point under consideration from a first reference plane P | 01-26-2012 |
| 20120020796 | RETAINING RING - A retaining ring presenting, on its periphery, a plurality of radial bores, each of the bores being able to receive a blade root. The retaining ring also includes at least one first radial opening traversed by a compression tube and at least one second radial opening, the at least first radial opening and the at least second radial opening being separated from each other by at least one of the bores of the plurality of radial bores. The ventilation device finds a particularly interesting application in the field of turbine engines including a pusher open rotor. | 01-26-2012 |
| 20120020774 | ASSEMBLY BETWEEN A COMPRESSOR SHAFT TRUNNION AND A BEVEL GEAR FOR DRIVING AN ACCESSORY GEARBOX OF A TURBOMACHINE - The invention relates to an assembly between a compressor shaft trunnion and a bevel gear for driving an accessory gearbox of a turbomachine. The assembly comprises a bevel gear, a compressor shaft trunnion arranged coaxially inside the bevel gear, torque transmission means between the compressor shaft trunnion and the bevel gear, a lock nut for preventing the bevel gear from moving axially on the compressor shaft trunnion, the lock nut being suitable for being screwed onto the bevel gear and including a shoulder projecting radially outwards and suitable for coming into axial abutment firstly upstream against a stop nut screwed onto an upstream end of the compressor shaft trunnion, and secondly downstream against a bearing surface of the compressor shaft trunnion, and an anti-rotation pin for preventing the lock nut from rotating. | 01-26-2012 |
| 20120018543 | DIFFUSER/RECTIFIER ASSEMBLY FOR A TURBINE ENGINE - A diffuser-nozzle assembly for mounting at an outlet from a compressor in a turbomachine, the assembly including a nozzle including two substantially cylindrical walls, a radially inner wall and a radially outer wall that are connected together by radial vanes. The walls of the nozzle are extended downstream beyond the radial vanes and the radial spacing therebetween varies downstream from the vanes to be at a minimum substantially in register with the vanes and at a maximum between the vanes. | 01-26-2012 |
| 20120018079 | ROTOR BLADE OF A GAS TURBINE ENGINE MADE OF COMPOSITE MATERIAL COMPRISING A CONNECTING YOKE, METHOD FOR MANUFACTURING THE BLADE - A rotor blade of a turbine engine comprising a body made of composite material consisting of a fibre-reinforced thermosetting resin and a connecting yoke designed to be attached to a fastener of a rotor disc of the said turbine engine, the said blade characterized in that the connecting yoke comprises a metal reinforcement and a casing made of composite material encasing the said reinforcement. | 01-26-2012 |
| 20120017603 | DOUBLE-BODY GAS TURBINE ENGINE PROVIDED WITH AN INTER-SHAFT BEARING - A double-body gas turbine engine, including a low-pressure body LP and a high-pressure body HP, rotatably mounted about a single shaft in a stationary casing, the low-pressure body LP including a compressor and a turbine connected by a low-pressure shaft LP. The low-pressure shaft LP is supported by an upstream LP bearing, a first downstream LP bearing, and an additional downstream LP bearing by the stationary casing, the high-pressure body being supported by an upstream HP bearing and a downstream HP bearing which is an inter-shaft bearing including an inner track rigidly connected to the HP turbine rotor and an outer track rigidly connected to the LP shaft. | 01-26-2012 |
| 20120017431 | WORKSHOP FOR PREPARING AIRCRAFT ENGINES FOR SHIPPING - A workshop for preparing aeroengines for shipping, the workshop including a station for fitting test and measurement mechanism on an engine, a mechanism for transporting the engine to test premises and for returning the engine to the workshop, a station for removing the test and measurement mechanism, a station for endoscopic inspection, a finishing station, and a shipping station. The engines are transported from one station to another by spreaders fastened on the engines and attached to hoists that are movable in translation along an overhead structure arranged in the workshop, each station being fitted with computer terminals for displaying and tracking the tasks to be performed on the engine in the corresponding station. | 01-26-2012 |
| 20120014810 | TURBINE VANE WITH DUSTING HOLE AT THE BASE OF THE BLADE - A cooled turbine vane for a turbine engine, that includes a blade mounted on a platform carried by a base, the blade including one or more cavities formed therein for cooling air circulation, the cavity extending along the trailing edge and being supplied with cooling air by a supply duct connecting an air intake located in a lower portion of the base and the cavity of the trailing edge by defining a bend within the base. The duct includes, on an axis substantially radial relative to the air intake a bell-shaped niche located under the platform, the niche being open at a top thereof via a dusting hole extending through the platform and being defined at a foot of the base by walls extending substantially radially from the platform to close the platform laterally. | 01-19-2012 |
| 20120011826 | TURBOJET ENGINE WITH AN ELEMENT OF THE NACELLE ATTACHED TO THE INTERMEDIATE CASING - The present invention relates to a turbojet engine with a fan ( | 01-19-2012 |
| 20120003085 | COMPRESSOR CASING WITH OPTIMIZED CAVITIES - The invention relates to a compressor for a turbine engine including a casing ( | 01-05-2012 |
| 20120000177 | TURBINE ENGINE WITH NONSTREAMLINED IMPELLERS - The present invention relates to a turbine engine comprising two respectively upstream and downstream external impellers ( | 01-05-2012 |
| 20110318513 | METHOD FOR MAKING A FORM PARTY BY 3D WEAVING, AND RESULTING FORM PART - A hollow part is obtained by 3D weaving and by impregnation. A preform is made by three-dimensional weaving and by ensuring partial non-interlinking during the weaving, thereby subsequently making it possible to define a cavity within the woven mass, and then to stabilize a shape of the preform during an impregnation stage. | 12-29-2011 |
| 20110318170 | TURBINE STAGE - A turbine stage for a turbomachine, the stage comprising a rotor wheel mounted inside a sectorized ring carried by an outer casing, and a sectorized nozzle fastened to the casing downstream from the wheel, each ring sector having a downstream end that is held bearing radially outwards against a cylindrical rail of the casing by means of the nozzle, the casing rail including an annular row of through radial notches reducing the areas for heat exchange by conduction both between the casing and the ring sectors and between the casing and the nozzle. | 12-29-2011 |
| 20110314828 | BLEEDING OF AIR VIA THE DIFFUSER OF A CENTRIFUGAL COMPRESSOR OF A TURBINE ENGINE - Diffuser intended to straighten the flow of air issuing from a centrifugal compressor in a turbine engine, the said diffuser having a cylindrical shape and comprising a first part having the form of two substantially parallel discs extending substantially radially relative to the axis of symmetry of the diffuser, a second bent part and a third part intended to open out into a downstream cavity, positioned downstream of the said diffuser and fed with air issuing from the said compressor, characterized in that the first part is traversed by a plurality of channels distributed evenly over its circumference and opening out on its downstream face so as to bring the air contained in the said downstream cavity into communication with a bleed cavity situated upstream of the said diffuser. | 12-29-2011 |
| 20110311368 | COMPOSITE MATERIAL TURBINE ENGINE VANE, AND METHOD FOR MANUFACTURING SAME - A method of fabricating a turbomachine blade out of a composite material including fiber reinforcement densified by a matrix, the method including making a one-piece fiber blank by three-dimensional weaving; shaping the fiber blank to obtain a one-piece fiber preform having a first portion forming a blade airfoil and root preform and at least one second portion forming a preform for an inner or outer blade platform; and densifying the preform with a matrix to obtain a composite material blade having fiber reinforcement constituted by the preform and densified by the matrix, fowling a single part with incorporated inner and/or outer platform. | 12-22-2011 |
| 20110311361 | SYSTEM OF COMPACT CONTRA-ROTATING PROPELLERS - A system of contra-rotating propellers for an aircraft jet engine, including: a free power turbine; a first and second propeller, contra-rotating, the first propeller being placed in a predetermined direction relative to the second propeller, each including a hub, an outer ferrule, and coupling arms linking the two; and a casing inserted between the free turbine and the propellers, the propellers arranged in the predetermined direction relative to the casing and the free turbine arranged in the opposite direction relative to the casing, the casing including a casing extension in the given direction, rotatably supporting the hub of the propeller. The coupling arms extend in the opposite direction, radially towards the outside. | 12-22-2011 |
| 20110311349 | ROTOR ELEMENT WITH A FLUID PASSAGE AND PASSAGE-BLOCKING MEMBER AND TURBINE ENGINE INCLUDING THE ROTOR ELEMENT - A rotor element including an annular surface portion about the rotor rotational axis, a fluid passage being formed through the surface portion, a passage-blocking mechanism including a blocking element that is deformable depending on the rotor rotating speed and arranged so as to adjust the fluid flow depending on the rotor rotating speed, and an annular collar with a free edge engaging with the blocking element so as to form the blocking mechanism. The free edge of the annular collar defines, together with the blocking portion of the blocking element, a diaphragm that blocks the fluid passage. | 12-22-2011 |
| 20110308634 | TURBOJET NACELLE HAVING A REMOVABLE AIR INTAKE STRUCTURE - A turbojet engine nacelle, including an air intake structure for directing an airflow towards a fan of the turbojet engine, a middle structure attached to the air intake structure for surrounding the fan of the turbojet engine, the air intake structure including an inner panel attached to the middle structure and defining a fixed structure with the middle structure, and an outer panel including an air intake lip at the end thereof opposite the middle structure, the outer panel being longitudinally translatably movable relative to the inner panel. The nacelle further includes at least one rod having one end attached onto a flange of the air intake lip and a mechanism rigidly connected to the middle structure for securing and locking the other end of each rod by applying a traction force thereon. | 12-22-2011 |
| 20110308306 | DEVICE FOR MONITORING THE OBSTRUCTION OF AT LEAST TWO FILTERS OF A FLUID CIRCULATION SYSTEM OF AN AIRCRAFT GAS TURBINE ENGINE - A device for monitoring the obstruction of at least two fluid filters of a fluid circulation system of a gas turbine engine of an aircraft, the device comprising a first obstruction sensor, intended to monitor a first fluid filter, set up to send a first detection signal of an obstruction of the first filter and a processor comprising a monitoring input linked to said first sensor to measure the first detection signal. The device also comprises a second obstruction sensor, intended to monitor a second fluid filter, set up to send a second detection signal of an obstruction of the second filter, the monitoring input of the processor being connected to the first obstruction sensor to measure said second detection signal over a single monitoring input. | 12-22-2011 |
| 20110308083 | DEVICE FOR REPAIRING THE CASING HOLDER OF AN AERONAUTICAL ENGINE - A device for repairing a casing holder of an aeronautical engine extending radially relative to the engine rotational axis and including a plurality of lips, each having a hole drilled therein and evenly distributed on the circumference of the holder. The device includes at least one reinforcement holder that can be attached to clean lips of the case holder via through-holes or blind-holes, the reinforcement holder having two orthogonal planes of symmetry. The device further includes a reconditioning holder mounted on the reinforcement holder via a first part using attachment means positioned in one of the planes of symmetry of the reinforcement holder. | 12-22-2011 |
| 20110307431 | STANDARDIZING DATA USED FOR MONITORING AN AEROENGINE - A method and a system for standardizing data used for monitoring an aeroengine, and including: operating over time to collect time-series measurements from the aeroengine; calculating from the time-series measurements a set of indicators Y=(y | 12-15-2011 |
| 20110307220 | IDENTIFYING FAILURES IN AN AEROENGINE - A method and a system for identifying failures in an aeroengine. The system includes: a mechanism defining a set of standardized indicators representative of operation of the aeroengine; a mechanism constructing an anomaly vector representative of a behavior of the engine as a function of the set of standardized indicators; a mechanism selecting in an event of an anomaly being revealed by the anomaly vector a subset of reference vectors having directions belonging to a determined neighborhood of a direction of the anomaly vector, the subset of reference vectors being selected from a set of reference vectors associated with failures of the aeroengine and determined using criteria established by experts; and a mechanism identifying failures associated with the subset of reference vectors. | 12-15-2011 |
| 20110305575 | DEVICE WITH COUNTER-ROTATING PROPELLERS HAVING A PROPELLER PITCH ALTERING MEANS - A device including a pair of counter rotating propellers with variable pitch which may be modified by an actuator located in a central cavity of the shafts. A system for transporting energy to the actuator includes a conduit passing into a static case in proximity to an epicycloidal gear train, and then control conduits leading to the actuator and crossing the planet carrier of an epicycloidal gear train. The junction is affected by a dynamic joint with a collector. This transport path avoids a high temperature turbine. | 12-15-2011 |
| 20110305560 | COOLING DEVICE FOR COOLING THE SLOTS OF A TURBOMACHINE ROTOR DISK DOWNSTREAM FROM THE DRIVE CONE - The invention relates to a cooling device for cooling the slots of a turbomachine rotor disk, the turbomachine comprising an upstream rotor disk having a fastener flange with a periphery that is festooned, a downstream rotor disk, an endplate for holding blades and arranged around the ring of the downstream disk and co-operating therewith to form an air diffusion cavity, a cone for driving disks in rotation, the cone having a fastener flange with a periphery that is festooned, and a plurality of bolted connections passing from upstream to downstream through the solid portions of the fastener flanges of the upstream disk and of the cone, the fastener flange of the endplate, and the fastener flange of the downstream disk. The fastener flange of the endplate is pierced by ventilation orifices opening out into the air diffusion cavity in order to feed it with cooling air, said cavity opening out into the slots of the downstream disk at their upstream ends in order to cool them. | 12-15-2011 |
| 20110301822 | METHOD AND SYSTEM FOR CONTROLLING A GAS TURBINE AND A GAS TURBINE INCLUDING SUCH A SYSTEM - A method for controlling a gas turbine including a compressor assembly including at least one variable geometry portion, a combustion chamber, and a turbine assembly. The method generates a flow rate setpoint value for fuel to be fed to the combustion chamber as a function of a desired speed of the gas turbine, computes threshold values for maintaining the fuel flow setpoint value in a given range, the threshold values depending on a thermodynamic state of the gas turbine, and controls the position of the variable geometry portion by controlling an actuator as a function of the difference between position information representative of the instantaneous position and setpoint position information. The threshold values are automatically adjusted by computation in real time as a function of the instantaneous position information of the variable geometry portion or of the difference between this position information and the setpoint position information. | 12-08-2011 |
| 20110299974 | LUBRICATING AND COOLING EPICYCLIC STEPDOWN GEARING - A lubricating and cooling epicyclic stepdown gearing, for example in an aeroengine turbomachine, including a cylindrical casing mounted on a planet-carrier of the gearing and forming a centrifugal scoop surrounding stationary oil-delivery strips, the cylindrical casing including radial ducts feeding nozzles pointing towards zones where the planet gears mesh with outer ring(s) of the gearing. | 12-08-2011 |
| 20110298901 | METHOD FOR THE NON-DESTRUCTIVE INSPECTION OF A MECHANICAL PART - An automatic method of non-destructive inspection of a mechanical part by comparing images of the surface of the part with reference images recorded in a database, by a digital image acquisition device including an image sensor, a lighting source, and a mechanism for moving the image sensor and the lighting source relative to the mechanical part. | 12-08-2011 |
| 20110296846 | AERONAUTICAL ENGINE WITH COOLING OF AN ELECTRIC STARTING DEVICE - An aeronautical engine including a fuel pumping device including a high pressure fuel pump including an inlet connected to a low pressure fuel conduit and an outlet connected to a main circuit for feeding high pressure fuel, an electric device starting the engine, and a device cooling the electric starting device connected to the pumping device to ensure cooling by circulation of fuel. The cooling device is supplied with fuel by a pump that includes an inlet connected to the pumping device, upstream from the high pressure pump, and that is driven by an electric motor independently of the high pressure pump. | 12-08-2011 |
| 20110296842 | CONTROL OF AXIAL THRUST BY GUIDANCE OF THE AIR DRAWN OFF FROM A CENTRIFUGAL COMPRESSOR - Inner combustion chamber casing of a turbomachine, which casing is intended to be placed downstream of a centrifugal compressor, the said casing having the shape of a disc, pierced by a central circle, and comprising on its disc at least one guide vane of the drawn-off air, the said guide vane extending longitudinally over the said disc between the periphery of the disc and the central circle and spreading out axially from the disc so as to form with the downstream face of the said centrifugal compressor a guide channel for the air which is drawn off upon exit from the said compressor, | 12-08-2011 |
| 20110296687 | METHOD OF MACHINING ROTOR BLADE WEAR INDICATORS, AND ROTOR BLADE PLUG FOR IMPLEMENTING THE METHOD - A method for machining at least one aircraft gas turbine engine rotor ( | 12-08-2011 |
| 20110293409 | METHOD OF REPAIRING A FLANGE OF A CASING - The invention relates to a method of repairing a flange of a casing for an airplane turboprop or turbojet, the flange including at least one through hole for passing a bolt for fastening equipment, the hole opening out in a face of the flange that is worn by friction against the equipment. The method consists in mounting a bearing member on the flange, the bearing member comprising a radial wall covering the worn face of the flange, said wall including a hole that comes into register with the hole in the flange and having thickness for compensating the wear of the face of the flange, said member further including an abutment for bearing against the periphery of the flange, and being fastened to the flange by adhesive. | 12-01-2011 |
| 20110293406 | VARIABLE-PITCH VANE FOR STATOR STAGE, INCLUDING A NON-CIRCULAR INNER PLATFORM - A variable-pitch vane for a stator stage including includes an active part of the vane either side of which are positioned a radially inner platform and a radially outer platform, where the active part of the vane, which has a surface forming a convex surface, and a surface forming a concave surface, separate the platform into a part positioned on the convex side and a part positioned on the concave side. Seen along the direction of the vane's axis of rotation, the part has an outer outline superimposed on a circle, at the distance of which, and inside which, is at least a part of the outer outline of the part of the platform. | 12-01-2011 |
| 20110288836 | DETECTION OF ANOMALIES IN AN AIRCRAFT ENGINE - A method and system for detecting anomalies in an aeroengine. The method and system define a behavior model of a controller of the aeroengine using a time regression modeling the behavior of the controller as a function of a data set relating to the controller and including measurements of past behaviors and command and state measurements of the controller; continuously recalculate the behavior model for each new data set; and monitor statistical variation of the behavior model to detect a behavior anomaly of the controller representing an operating anomaly of the engine. | 11-24-2011 |
| 20110280735 | VENTILATION OF A HIGH-PRESSURE TURBINE IN A TURBOMACHINE - A turbomachine high-pressure turbine including a rotor disc with upstream and downstream annular flanges separating a radially internal annular cavity in which the hub of the disc extends from two radially external annular cavities, of which one is upstream of the disc and receives a ventilation air flow and of which the other is downstream of the disc, the upstream flange of the disc including a mechanism connecting to the upstream eternal cavity and the internal cavity for ventilating the hub of the disc. | 11-17-2011 |
| 20110276247 | METHOD AND A SYSTEM FOR MONITORING VIBRATORY PHENOMENA THAT OCCUR IN AN AVIATION GAS TURBINE ENGINE IN OPERATION - The invention relates to a method and a system for monitoring vibratory phenomena that occur in an aviation gas turbine engine in operation. The method consists: in establishing (E | 11-10-2011 |
| 20110274541 | ANNULAR FLANGE FOR FASTENING A ROTOR OR STATOR ELEMENT IN A TURBOMACHINE - A radial annular flange including in inner or outer periphery alternating solid portions including orifices for passing fastener bolts, and hollow portions having bottoms that are substantially flat. The bottom of at least one keying hollow portion is situated radially inside, or outside, respectively, a circle centered on the axis of the flange and externally, or respectively internally, tangential to the orifices. Two hollow portions are situated on either side of the keying hollow portion having bottoms of concave curved shapes situated radially on the outside, or respectively on the inside, relative to the flat bottoms of the other hollow portions. | 11-10-2011 |
| 20110274540 | TURBOMACHINE CASING - A turbomachine casing forming a continuous annular ring extending over 360° around a bladed wheel and serving as a propagation medium for rotating waves, each rotating wave being generated by two standing waves of the same frequency, and the casing including at least one longitudinal stiffener at its outer periphery that is dimensioned and positioned in such a manner as to separate the frequencies of the two standing waves of at least one given rotating wave. | 11-10-2011 |
| 20110273724 | DEVICE FOR MEASURING THE TWIST OF A ROTATING SHAFT - Measuring the twist of a rotating shaft by means of a laser beam and polarizing filters. The measurement device includes a laser beam generator, two polarizing filters secured to the shaft and spaced apart from each other, and a laser radiation receiver receiving the laser beam after it has passed through both filters. | 11-10-2011 |
| 20110271682 | DEVICE FOR INJECTING A MIXTURE OF AIR AND FUEL INTO A TURBOMACHINE COMBUSTION CHAMBER - A device for injecting a mixture of air and fuel into a turbomachine combustion chamber includes a centering ring for centering an injector and a primary swirler situated downstream from the ring, the ring including axial air-passing orifices and the swirler including curved air-passing channels, a number of orifices in the ring being no greater than a number of channels in the swirler, and downstream outlets of the orifices in the ring being situated between the channels in the swirler. | 11-10-2011 |
| 20110271678 | TURBOMACHINE COMBUSTION CHAMBER WALL HAVING A SINGLE ANNULAR ROW OF INLET ORIFICES FOR PRIMARY AIR AND FOR DILUTION AIR - A turbomachine combustion chamber including coaxial walls forming surfaces of revolution that include inlet orifices for admitting primary air and dilution air into the chamber, the orifices in each wall being substantially in alignment with one another along the longitudinal axis of the chamber and forming a single annular row of orifices. | 11-10-2011 |
| 20110268577 | METHOD FOR SMOOTHING THE SURFACE OF A PART MADE FROM A CMC MATERIAL - A method of smoothing the surface of a ceramic matrix composite part presenting a surface that is undulating and rough. The method includes forming a ceramic coating on the surface of the part, the coating being made by applying a liquid composition on the surface of the part, the composition containing a ceramic-precursor polymer and a factory solid filler, curing the polymer, and transforming the cured polymer into ceramic by heat treatment. The method further includes impregnating the ceramic coating with a liquid metallic composition. | 11-03-2011 |
| 20110268566 | METHOD FOR THE MANUFACTURE OF A CIRCULAR REVOLUTION THERMOMECHANICAL PART INCLUDING A TITANIUM-BASED LOAD-BEARING SUBSTRATE LINED WITH STEEL OR SUPERALLOY, A TURBOMACHINE COMPRESSOR HOUSING WHICH IS RESISTANT TO TITANIUM FIRE OBTAINED USING THIS METHOD - A method for manufacture of a compressor housing which is resistant to a titanium fire (burning titanium). A ring made of steel, steel alloy, or superalloy which is incombustible in the presence of a titanium fire is ring roll-bonded with a ring made from titanium or titanium alloy. | 11-03-2011 |
| 20110268561 | TURBINE ENGINE ROTOR WHEEL WITH BLADES MADE OF A COMPOSITE MATERIAL PROVIDED WITH A SPRING RING - A turbomachine rotor wheel including blades made of composite material; an annular mounting plate; a plurality of composite material blades mounted on the mounting plate, each blade also including a top platform at its tip carrying radial labyrinth teeth; an orientation disk fastened coaxially around the mounting plate and including at its outer periphery a plurality of axial slots that are open at one end, each slot presenting a cross-section that matches the cross-section of a blade root so as to hold it angularly in position by co-operation of shapes; and a variable-diameter spring ring housed in part in an axial notch formed in each blade root and projecting axially relative thereto, the spring ring to come into radial abutment against an inside surface of the orientation disk during radial outward movement of the blades relative to the mounting plate. | 11-03-2011 |
| 20110259997 | SUSPENSION RUDDER BAR FOR AN AIRCRAFT TURBOJET AND A SUSPENSION WITH FAN HANGER PROVIDED THEREWITH - This invention aims at making a rudder bar with a reduced master-couple in the case of a breaking of a connecting rod. To this end, this invention provides shifting the contact areas to the interior of the rudder bar and thereby reducing the transversal bulk thereof. | 10-27-2011 |
| 20110259093 | METHOD FOR DETECTING RESONANCE IN A ROTOR SHAFT OF A TURBINE ENGINE - A method for detecting resonance in a rotor shaft of a turbine engine, the resonance frequency (Fr) of the said rotor shaft belonging to a resonance band centred on an estimated resonance frequency (Fr | 10-27-2011 |
| 20110258977 | OIL-SEPARATOR ROTOR FOR A TURBOMACHINE - An oil separator rotor for a turbomachine, including a tubular hub that includes an external annular flange and an annular cover which, in cross section, is substantially L-shaped and mounted around the hub. The hub flange includes, at its external periphery, a mechanism to radially retain the free end of the cylindrical wall of the cover, so as to center this end and prevent it from deforming in the radially outwards direction under the effect of centrifugal force. | 10-27-2011 |
| 20110256809 | METHOD OF POLISHING BLADED DISKS FOR A TURBOMACHINE AND POLISHING DEVICE - A device for polishing centrifugal impellers for a turbomachine including a vat configured to be filled with a polishing agent, and an impeller support configured to make the impeller rotate around its axis and move it along its axis such that all of points of the impeller have a helical movement whereof the pitch is close to that of the helix from which the general shape of the airflow channels of the impeller comes, delimited by the blades of the impeller. | 10-20-2011 |
| 20110255983 | DEVICE FOR ATTACHING HAMMER CLAMP BLADES, ASSOCIATED COMPRESSOR HUB, COMPRESSOR AND TURBINE ENGINE - The invention relates to a locking device for enabling the circular locking of a set of blades provided with a hammer base ( | 10-20-2011 |
| 20110253231 | FUEL FEED DEVICE FOR AVIATION ENGINE - A jet pump ( | 10-20-2011 |
| 20110252644 | DEVICE FOR HEATING A CYLINDRICAL COMPONENT AND USE IN ASSEMBLING AN INTER-SHAFT BEARING IN A TURBOMACHINE - A device for heating a cylindrical component of given diameter is disclosed. The device includes at least two heaters each delivering a stream of hot gas and emerging in an annular chamber. The inside diameter of the annular chamber is slightly greater than the diameter of the cylindrical component. The device may be used for heating a metal journal in which a bearing ring for an inter-shaft bearing in a double-body turbomachine is mounted. | 10-20-2011 |
| 20110250061 | STATIONARY VANE ASSEMBLY FOR A TURBINE ENGINE HAVING A REDUCED WEIGHT, AND TURBINE ENGINE COMPRISING AT LEAST ONE SUCH STATIONARY VANE ASSEMBLY - A stationary vane assembly of a turbine engine including an inner casing and a high-pressure turbine guide vane assembly including at least two angular sectors including blades, the angular sectors being fixed on the casing, each angular sector including a platform and a fastening tab. The fastening tab protrudes from the platform radially inwardly. The casing includes a first annular groove receiving the fastening tabs, radial retaining pins for the angular sectors being introduced into bores made in the casing and the fastening tabs, the axial retaining pins being axially stopped by a ring mounted in a second annular groove of the casing. | 10-13-2011 |
| 20110248416 | METHOD FOR MANUFACTURING A TURBINE ENGINE VANE - Fabricating a blade by 3D weaving a preform that is to be impregnated with resin. According to the invention, the visibility of the cut ends of certain yarns of the preform ( | 10-13-2011 |
| 20110247664 | CLOSED-CIRCUIT INSTALLATION FOR THE SURFACE-TREATMENT OF COMPONENTS IN A LIQUID BATH - The installation comprises a bath storage reservoir ( | 10-13-2011 |
| 20110246151 | METHOD AND A SYSTEM FOR ESTIMATING A STREAM TEMPERATURE IN A TURBOJET - An estimation method that can estimate a stream temperature in a turbojet including: digitally modeling the stream temperature with help of a modeled signal; and correcting the modeled signal with help of an error signal, a signal obtained after correction representing an estimate of the stream temperature. When predetermined conditions relating to at least one operating stage of a turbojet and to temperature stability are satisfied, the error signal is updated from the modeled signal and from a measurement signal of the stream temperature as delivered by a temperature sensor. | 10-06-2011 |
| 20110243772 | FUEL SUPPLY INSTALLATION OF AN AIRCRAFT TURBOJET - Optimisation of components of a fuel supply installation for a turbojet. | 10-06-2011 |
| 20110243744 | SEAL FOR A PLATFORM IN THE ROTOR OF A TURBINE ENGINE - A seal for an intermediate platform provided between two adjacent blades in the rotor of a turbine engine, the seal having an elongate shape with an upstream end and a downstream end, and including transversally, in the direction of the width thereof, a contact portion, an attachment portion, and a flexible portion between the attachment portion and the contact portion. The cross section of the seal has an open-ended shape between the two ends thereof. | 10-06-2011 |
| 20110243742 | STATOR STAGE FOR TURBOMACHINE COMPRESSOR - A turbomachine stator stage comprising two coaxial shrouds, respectively an inner shroud and an outer shroud with substantially radial vanes extending therebetween, the radially outer ends of the vanes being welded to the outer shroud and the radially inner ends of the vanes passing through orifices in an outer ring of the inner shroud, the inner ends being held by elastomer spacers in an annular cavity formed between the outer ring and an inner ring that is fastened to the outer ring. | 10-06-2011 |
| 20110243735 | SYSTEM OF CONTRA-ROTATING PROPELLERS DRIVEN BY A PLANETARY GEAR TRAIN PROVIDING A BALANCED DISTRIBUTION OF TORQUE BETWEEN THE TWO PROPELLERS - A system of contra-rotating propellers for an aircraft turbomachine, including: a free power turbine including a first rotor; first and second propellers; and a mechanical transmission system including a planetary gear train fitted with a sun gear driven by the rotor, at least one planet gear driving the first propeller, and a ring driving the second propeller. The free power turbine also includes a second rotor that is contra-rotating relative to the first rotor, and rotating the ring. | 10-06-2011 |
| 20110240181 | METHOD FOR MANUFACTURING A TITANIUM PART THROUGH INITIAL BETA FORGING - The invention relates to a method of fabricating a titanium alloy part, the method comprising:
| 10-06-2011 |
| 20110239661 | ROTOR FOR A GAS TURBINE ENGINE COMPRISING A ROTOR SPOOL AND A ROTOR RING - A one-piece rotor spool ( | 10-06-2011 |
| 20110238351 | METHOD AND SYSTEM FOR CORRECTING A TEMPERATURE MEASUREMENT SIGNAL - A method including digitally modelling a temperature measured by a sensor by using a modeled signal and estimating a lag error signal for the sensor from the modeled signal and a signal obtained by filtering the modeled signal, the filter having as a parameter an estimate of a time constant of the sensor, and correcting the measurement signal delivered by the sensor by the estimated lag error signal. The time constant of the sensor is estimated as a function of time from the measurement signal and the modeled signal. | 09-29-2011 |
| 20110236212 | FEATHERING DEVICE FOR THE FAN BLADES OF A TURBOPROP ENGINE - The invention concerns a feathering device for the fan blades of a turboprop engine that includes at least one set of fan blades ( | 09-29-2011 |
| 20110236192 | COMPRESSOR HOUSING RESISTANT TO TITANIUM FIRE, HIGH-PRESSURE COMPRESSOR INCLUDING SUCH A HOUSING AND AIRCRAFT ENGINE FITTED WITH SUCH A COMPRESSOR - A compressor housing resistant to a titanium fire (burning titanium). A mixed housing is constructed, in which a structure holding stator blades includes a single-cast part made from titanium or titanium alloy, and at least one element forming a shield made from refractory alloy(s), and which is incombustible in presence of burning titanium, where each shield is secured to the single-cast part by fasteners. The fasteners are positioned with each shield so as to define jointly an inner wall demarcating an outer contour of the compressor airstream. | 09-29-2011 |
| 20110234236 | METHOD AND A DEVICE FOR DETECTING AN ELECTRICAL FAILURE AFFECTING AN ELECTRIC CONTROL SYSTEM OF A HYDRAULIC ACTUATOR OF VARIABLE GEOMETRIES OF AN AEROENGINE - After the control system has been started, which system has two control paths that are used as alternatives for delivering a control electric current to an electrohydraulic member for transforming said current into hydraulic power that is delivered to the actuator, and before powering a starter-generator of the engine, the detection method comprises implementing the following steps for each of the control paths in succession:
| 09-29-2011 |
| 20110232479 | PISTON WITH A DUCT UNDER A GASKET - The invention relates to a piston having a first face, a second face opposite to the first face, a third face connecting said first and second faces together and presenting a groove, and a sealing gasket housed in said groove. The piston includes a duct constituted by a first segment situated inside the piston and connecting said first face to said groove, by a second segment situated inside the piston and connecting said second face to said groove, and by an intermediate segment connecting together said first and second segments and crossing said groove, the walls of said intermediate segment being formed by the walls of said groove and by said sealing gasket in such a manner that said intermediate segment forms a leaktight tube that opens out solely via the first segment and via the second segment, said intermediate segment presenting at least one obstacle suitable for impeding the flow of fluid that flows along said intermediate segment. | 09-29-2011 |
| 20110232288 | METHOD OF REDUCING COMBUSTION INSTABILITIES BY CHOOSING THE POSITION OF A BLEED AIR INTAKE ON A TURBOMACHINE - Method of reducing acoustic vibratory phenomena in the environment of a combustion chamber of a turbomachine, said chamber being positioned in a cavity delimited by an exterior casing and an interior chamber casing, characterized in that it includes at least the following steps:
| 09-29-2011 |
| 20110229326 | STRUCTURAL AND AERODYNAMIC MODULE FOR A TURBOMACHINE CASING AND CASING STRUCTURE COMPRISING A PLURALITY OF SUCH A MODULE - The invention relates to a structure and aerodynamic module comprising two blades each extending along a longitudinal axis, each blade each comprising a leading edge, a trailing edge, a radially inner edge and a radially outer edge, the module also comprising a radially inner platform mechanically connecting the radially inner edges of the two blades, and a radially outer platform mechanically connecting the radially outer edges of the two blades such that the two blades and the radially outer and inner platforms delimit a flow stream, the two blades and the platforms being made from a composite material and the two blades being fixed on the radially outer and inner platforms using screw-nut assemblies. | 09-22-2011 |
| 20110229314 | HIGH-PRESSURE TURBINE FOR TURBOMACHINE, ASSOCIATED GUIDE VANE SECTOR AND AIRCRAFT ENGINE - An assembling of a guide vane assembly of a turbomachine turbine, formed by an annular row of stationary flow-stabilizing vanes. An outer edge of the guide vane assembly is axially bearing on a line of an external casing of the turbine and an inner edge of the guide vane assembly is in axial sliding connection with the line of the internal casing of the turbine, the axial sliding connection allowing the inner edge to be free along the motor axis with the axial stop being achieved by the axial bearing of the outer edge of the vane. | 09-22-2011 |
| 20110229310 | SYSTEM FOR CONTROLLING VARIABLE GEOMETRY EQUIPMENT OF A GAS TURBINE ENGINE PARTICULARLY COMPRISING A BARREL LINK - A system for controlling at least two variable geometry apparatuses of a gas turbine engine that includes at least a first body and a second body, the first apparatus including a stator blade stage with a variable setting angle of a compressor of the first body capable of switching between a closed position in an idle mode and an open position in a high-speed mode, and the second apparatus including at least one discharge valve of a compressor of the second body capable of switching between an open position in an idle mode and a closed position in a high-speed mode. The system further includes an actuator for actuating the two apparatuses. | 09-22-2011 |
| 20110223008 | TURBINE ENGINE FAN COMPRISING A BALANCING SYSTEM WITH BLIND HOLES FOR ACCOMMODATING MASSES - A fan for an aircraft turbine engine, including an intake cone including a balancing system including a plurality of mass accommodation holes and at least one balancing mass mounted in one of the holes. The balancing system further includes an attachment mechanism exerting pressure that flattens the balancing mass against the bottom of its mass accommodation hole, the accommodation hole being made blind in the intake cone, so as to open out inside the intake cone. | 09-15-2011 |
| 20110220217 | AIR INLET OF AN AEROENGINE HAVING UNDUCTED PUSHER PROPELLERS - An air intake for an aeroplane engine of type with unducted propellers, which intake can be connected by a pylon to a fuselage of an aeroplane, a local length of the air intake, measured parallel to the axis of the engine between a point on a leading edge of the air intake and a transverse plane situated at an inlet impeller of the engine compressor, is longer in a region of the air intake connected to the pylon and shorter in a region of the air intake opposite the pylon. | 09-15-2011 |
| 20110217172 | AIRFOIL ATTACHMENT HOLDING AN AIRFOIL ROOT IN A BROACH FITTING - Airfoil attachment comprising a support ( | 09-08-2011 |
| 20110211945 | METHOD FOR THE MANUFACTURE OF A CIRCULAR REVOLUTION THERMOMECHANICAL PART INCLUDING A TITANIUM-BASED LOAD-BEARING SUBSTRATE LINED WITH STEEL OR SUPERALLOY, A TURBOMACHINE COMPRESSOR HOUSING WHICH IS RESISTANT TO TITANIUM FIRE OBTAINED ACCORDING TO THIS METHOD - A method for manufacture of a compressor housing which is resistant to a titanium fire (burning titanium). An explosion cladding of a circular blank made of steel, or steel alloy, or superalloy which is incombustible in the presence of a titanium fire is accomplished on a circular blank made from titanium or titanium alloy. | 09-01-2011 |
| 20110208497 | COMPUTER AIDED DESIGN METHOD FOR CREATING A SURFACE IN A COMPLEX SYSTEM - This method may be applied by a computer ( | 08-25-2011 |
| 20110206530 | VIBRATION DAMPER DEVICE FOR TURBOMACHINE BLADE ATTACHMENTS, ASSOCIATED TURBOMACHINE AND ASSOCIATED ENGINES - A vibration-damping device for a turbomachine blade including a blade root configured to be inserted into a pocket of a carrier disk of a bladed wheel, the device configured to be positioned between the blade root and a retaining wall of the pocket. The device includes at least one shim including an assembly of layers of rigid materials and of viscoelastic materials, and including two portions, each forming a lateral branch which can be inserted along one of the two retaining walls, the two lateral branches being connected to one another, so as to constitute a single part, by a third portion forming a shim bottom of rigid material. At least one layer of viscoelastic material is positioned between two layers of rigid materials. | 08-25-2011 |
| 20110206504 | FIXED VANE ASSEMBLY FOR A TURBINE ENGINE HAVING A REDUCED WEIGHT, AND TURBINE ENGINE COMPRISING AT LEAST ONE SUCH FIXED VANE ASSEMBLY - A stationary vane assembly for a turbine engine including an inner casing and at least two angular sectors forming a high-pressure guide vane assembly, each angular sector including a fastening tab for fastening the angular sector on the casing. The stationary vane assembly including a ring of abradable material fixed on the casing, on the side of a mobile vane assembly using a plurality of screw-nut assemblies, the stationary vane assembly also including radial retaining pins for the angular sectors introduced into first bores formed in the fastening tabs and in the mounting clip, the bores having axes substantially parallel to the longitudinal axis, the mounting clip being fixed on the casing by the same screw-nut assemblies as those fixing the ring of abradable material support on the casing. | 08-25-2011 |
| 20110206503 | METHOD FOR THE MANUFACTURE OF A CIRCULAR REVOLUTION THERMOMECHANICAL PART INCLUDING A TITANIUM-BASED LOAD-BEARING SUBSTRATE LINED WITH STEEL OR SUPERALLOY, A TURBOMACHINE COMPRESSOR HOUSING WHICH IS RESISTANT TO TITANIUM FIRE OBTAINED ACCORDING TO THIS METHOD - A method for manufacture of a compressor housing which is resistant to a titanium fire (burning titanium). A circular blank made of steel, or steel alloy, or superalloy which is incombustible in the presence of a titanium fire is hydroformed against a circular blank made from titanium or titanium alloy. | 08-25-2011 |
| 20110204227 | COUNTING INCLUSIONS IN ALLOYS BY IMAGE ANALYSIS - A method of counting and analyzing an alloy by image analysis. The method includes a) preparing a sample of the alloy; b) determining inclusion detection thresholds by observation, with magnification, of at least one field of the sample; c) detecting inclusions of the sample as a function of the threshold defined in b), and counting the inclusions; d) acquiring images of each of the inclusions detected in c) and determining a size of each of the inclusions; e) determining the chemical composition of each of the detected inclusions by chemically analyzing each of them; and f) making a map of the sample from the images acquired in d), the map showing spatial distribution of the inclusions, in which each of the detected inclusions is represented by a graphics element, a size of the graphics element being proportional to the size of the inclusion, and a color of the graphics element being correlated to the chemical composition of the inclusion. | 08-25-2011 |
| 20110203294 | FUEL INJECTION SYSTEM FOR A COMBUSTION CHAMBER OF A TURBOMACHINE - A fuel injection system for an annular combustion chamber of a turbomachine, the system comprising support means for supporting and centering a fuel injector head, and a bowl arranged downstream from the support means and including at its downstream end an annular collar that extends radially outwards and that is cooled by air impacting against its upstream radial surface, and including on said surface means for disturbing the flow of cooling air and for increasing the heat exchange area between the air and the collar. | 08-25-2011 |
| 20110200442 | TURBINE BLADE WITH IMPROVED AERODYNAMIC PERFORMANCE - One or more protuberances are provided on a turbine blade on its suction side in a vicinity of its trailing edge. The protuberances serve to reduce a separation zone in a vicinity of a blade surface that is responsible for disturbances that affect efficiency of the turbine. | 08-18-2011 |
| 20110199249 | METHOD FOR DIGITIZING AN ANALOGUE SIGNAL WITH AN ANALOGUE-DIGITAL CONVERTER OF DETERMINED SHANNON FREQUENCY - A method for forming a global spectrum (Sg) of an analogue signal (A) to be digitized, in which:
| 08-18-2011 |
| 20110198155 | METHOD AND SYSTEM FOR LUBRICATING A TURBINE ENGINE - A method and a system for lubricating a turbine engine including at least three separate housings each including at least one roller bearing. The method pressurizes the housings through seals, of which two main housings are pressurized at a pressure higher than that of a remaining secondary housing, lubricates a secondary roller bearing only by injecting an oil mist from at least one of the main housings, the oil mist being supplied by a pressure difference between the main housings and the secondary housing, recovers a remainder of the lubrication oil injected into the main housings to supply the same to an oil tank, and supplies the air/oil mixture from the secondary housing to an oil separator. | 08-18-2011 |
| 20110194944 | TURBINE BLADE EQUIPPED WITH MEANS OF ADJUSTING ITS COOLING FLUID FLOW RATE - A turbine blade cooled by an automatically variable internal flow of cooling fluid. The blade includes orifices situated under the blade root via which the cooling fluid penetrates, and an adjustment plate including holes situated in register with the orifices, the adjustment plate having a coefficient of expansion that is different from the coefficient of expansion of the blade root. | 08-11-2011 |
| 20110192509 | METHOD FOR FORGING A TITANIUM ALLOY THERMOMECHANICAL PART - A method for forging a thermomechanical part and including: providing a billet produced in a titanium alloy having a beta transus temperature; carrying out at least one operation of forging a blank of the billet at a temperature T | 08-11-2011 |
| 20110190950 | SYSTEM FOR CONTROLLING VARIABLE GEOMETRY EQUIPMENT OF A GAS TURBINE ENGINE ESPECIALLY COMPRISING A GUIDING TRACK CONNECTION - A system for controlling at least two sets of variable geometry equipment of a gas turbine engine including at least one first body and a second body, the first set of equipment being a stage of variable stator vanes of a compressor of the first body moving between a closed position during idling and an open position at high speed, and the second set of equipment being at least one bleed valve of a compressor of the second body moving between an open position during idling and a closed position at high speed. An actuator actuates the two sets of equipment. | 08-04-2011 |
| 20110189023 | BLADE WITH NON-AXISYMMETRIC PLATFORM: RECESS AND BOSS ON THE EXTRADOS - A blade for a turbomachine impeller including an airfoil, and at least one platform at one of the ends of the airfoil, the blade configured to be arranged with a plurality of substantially identical blades so as to form a ring around a ring axis. In the blade, a suction surface profile at the surface of the platform and along the suction surface has a first recessed part located axially in an upstream half of the airfoil and a first boss-like part located axially downstream of the first recessed part. Due to this configuration, efficiency of the blade is improved. | 08-04-2011 |
| 20110189012 | TURBOMACHINE OPTIMIZED FOR FASTENING A ROTARY SHAFT BEARING. A METHOD OF MOUNTING SAID BEARING ON SAID TURBOMACHINE - A turbomachine including a shaft, a bearing for supporting the shaft and including an outer ring, and a support for said bearing, the support having a flange to which the outer ring is fastened by fasteners; each fastener comprising a fastener bolt and a nut screwed together; the turbomachine also including for each fastener, position-retention means for retaining the bolt, and suitable for retaining the bolt in a position that is stationary relative to the bearing support or the outer ring, even in the absence of the nut. The head of the fastener bolt and the position-retention means may be of small dimensions, thereby enabling the fastening of the flange to the bearing support to be optimized, and in particular enabling the weight of said fastening to be optimized. The invention also provides a method of mounting said bearing of the turbomachine. | 08-04-2011 |
| 20110188993 | RING SECTOR OF TURBOMACHINE TURBINE - A turbine ring sector comprising:
| 08-04-2011 |
| 20110188992 | METHOD AND A DEVICE FOR BALANCING PRESSURE IN A TURBOJET BEARING ENCLOSURE - A pressure-balancing device for balancing pressure in at least one bearing enclosure of a turbojet, the enclosure including a mechanism feeding the bearing with lubricating liquid, an air intake, at least one sealing system placed between the stator and the rotor in front of and/or behind the bearing, a recovery mechanism recovering the lubricating liquid, and a removal mechanism removing the mixture of air and of traces of lubricating liquid towards a venting circuit. Downstream from the bearing enclosure and in the venting circuit, the balancing device includes a regulator system regulating the air removal flow rate, thereby enabling the flow rate to be variable as a function of the speed of the engine, to remain non-zero, and, at high speeds, to be lower than when the regulator system is not included. | 08-04-2011 |
| 20110184573 | SYSTEM FOR CONTROLLING VARIABLE GEOMETRY EQUIPMENT FOR A TURBINE ENGINE, ESPECIALLY BY BELLCRANKS - A system for controlling at least two sets of variable geometry equipment of a turbine engine. The turbine engine includes at least one first body and a second body, the first set of equipment being a stage of variable stator vanes of a compressor of the first body moving between a closed position during idling and an open position at high speed, and the second set of equipment being at least one bleed valve of a compressor of the second body moving between an open position during idling and a closed position at high speed. The actuator drives the second set of equipment by an actuating part that is actuated over part of the course of the actuator and idle on an abutment over the rest of the course, and by a sliding joining element providing a backlash in the actuation of the second set of equipment. | 07-28-2011 |
| 20110182716 | SYSTEM FOR CONTROLLING VARIABLE GEOMETRY APPARATUSES IN A TURBINE ENGINE - A control system for controlling at least two variable-geometry devices of a turbomachine, and a turbomachine including such a control system, the system including an actuator that actuates both devices; one of the devices including at least one stage of variable-pitch stator vanes, and the other device being an air-bleed valve for a turbomachine body. The system is configured to control progression opening of the vane stage and progressive closing of the air-bleed valve as an actuation parameter of the actuator increases. As a result, the control system serves advantageously to control two devices using a single control system. | 07-28-2011 |
| 20110180171 | OBSTRUCTIVE CAP FOR A ROTATING HOLLOW TRANSMISSION SHAFT - A sealing plug for a hollow shaft used to impart a rotational speed, the hollow shaft including a first end adapted to be located in a chamber containing lubricant, and a second end adapted to be located outside the chamber. The sealing plug has a substantially cylindrical surface, a first face and a second face for insertion into the first end of the hollow shaft. The plug also includes a cavity that is open at the second face and a first radial duct opening, at one of its ends, at the cavity and, at its opposite end, at the substantially cylindrical surface of the sealing plug. The device is applied particularly in the field of turbomachines equipped with an open rotor. | 07-28-2011 |
| 20110179798 | SEALING BETWEEN A COMBUSTION CHAMBER AND A TURBINE NOZZLE IN A TURBOMACHINE - A turbomachine including an annular combustion chamber, a sectorized turbine nozzle arranged at an outlet from the chamber, and a sealing mechanism interposed axially between the chamber and the nozzle, the sealing mechanism including an annular gasket that is axially resilient. The gasket includes a first axial bearing mechanism for bearing against a downstream end of the chamber and a downstream annular lip that is sectorized, each sector of the downstream lip being in alignment with a sector of the nozzle and including a second axial bearing mechanism for bearing against an upstream end of the nozzle sector. | 07-28-2011 |
| 20110179764 | TURBO-ENGINE COMPRESSOR TIP COMPRISING DE-ICING MEANS - The de-icing system comprises a flexible bladder ( | 07-28-2011 |
| 20110178772 | METHOD AND SYSTEM FOR MONITORING A TURBOJET ENGINE - A method and a system for monitoring a turbojet engine. The method acquires a signal representative of a vibratory level of an operating rotor of the turbojet engine, acquires a rotation speed of the rotor during operation, compares the amplitude of the signal with at least one predetermined threshold based on the rotor rotation speed and, in event an amplitude peak exceeds the threshold, analyzes the signal over a time slot defined around the amplitude peak to determine if the phenomenon at the origin of the amplitude peak is a mechanical shock undergone by the rotor of the turbojet engine or an electronic interference of the signal. | 07-21-2011 |
| 20110176924 | DEVICE ADAPTED TO BE FITTED WITH PROPELLER BLADES - A device adapted to be fitted with propeller blades includes a first retention ring including over a periphery thereof a plurality of radial bores; and a second retention ring including over a periphery thereof a plurality of radial bores, the first and second retention rings being mounted one on top of the other in the radial direction, each bore in the first retention ring being positioned opposite a bore in the second retention ring, a bore in the first retention ring arranged opposite a bore in the second retention ring forming a bore pair adapted to receive a foot of a blade. | 07-21-2011 |
| 20110176921 | METHOD OF REPAIRING OR REWORKING A TURBOMACHINE DISK AND REPAIRED OR REWORKED TURBOMACHINE DISK - The invention relates to a method of repairing or of reworking a turbomachine disk comprising, on it's rim, at least one external radial tab with an axial bore to accept an axial pin comprising a head and a shank with a threaded portion, the pin being slipped into the bore in such a way that the head comes to press against one face of the tab through the tightening of a nut on to the shank with threaded portion against the opposite face of the tab, said pin forming a retaining means to keep a tab secured to a component attached to the rim. | 07-21-2011 |
| 20110176911 | ASSEMBLING TITANIUM AND STEEL PARTS BY DIFFUSION WELDING - A method of assembling together titanium parts and steel parts by diffusion welding, the method interposing two thin layers of niobium or vanadium and copper respectively between a titanium part and a steel part, evacuating the assembly of parts and interposed metal layers, and subjecting the assembly to hot isostatic compression at a temperature lying in a range 900° C. to 950° C. and at a pressure lying in a range 1000 bars to 1500 bars for about two hours. The method can be applied to fabricating turbine shafts for turbomachines. | 07-21-2011 |
| 20110168837 | AIRCRAFT PROPULSION SYSTEM - An aircraft propulsion system including a bypass turbojet engine surrounded by a nacelle together with a mechanism attaching the engine to a pylon of an aircraft. The nacelle includes an inner structure forming a body of revolution including a rigid framework formed by an upstream annular frame fastened to an intermediate casing of the engine, a downstream annular frame supporting the exhaust casing of the engine, and longitudinal arms connecting the frames together, the annular downstream frame being fastened to the pylon by a flexible or hinged suspension mechanism. | 07-14-2011 |
| 20110167835 | TURBINE ENGINE WITH A POWER TURBINE EQUIPPED WITH AN ELECTRIC POWER GENERATOR - The present invention relates to a turbine engine for aircraft comprising a gas generator as well as to a receiver driven by a power turbine ( | 07-14-2011 |
| 20110164971 | NOZZLE STAGE FOR A TURBOMACHINE COMPRESSOR - The invention relates to a nozzle stage for a turbomachine compressor, the stage comprising two coaxial shrouds, a radially inner shroud and a radially outer shroud, and radial vanes extending between the shrouds and being connected via their ends to the shrouds, together with a support for abradable material that is mounted by crimping onto the upstream and downstream edges of the inner shroud, the inner shroud presenting openings in which the radially inner ends of the vanes are inserted and fastened. The radially inner ends of the vanes are plane and do not have any projecting tenons. | 07-07-2011 |
| 20110163207 | AIRPLANE HAVING ENGINES PARTIALLY ENCASED IN THE FUSELAGE - An airplane provided with dual-flow turbojet engines having nacelles at least partially encased in the fuselage, wherein the air intake of each engine is connected to the fuselage by two boundary layer guiding walls, the walls extending towards the upstream side of the air intake and being spaced apart towards the upstream side. | 07-07-2011 |
| 20110150657 | TURBOMACHINE FAN ROTOR - A turbomachine fan rotor including a disk carrying blades with roots that are engaged in axial grooves of the disk, a spacer being interposed between the bottom of each groove and the corresponding blade root, the spacer including at its upstream end a nib for retaining the blade root, the nib including a downstream abutment face against which the upstream end of the blade root bears in event of a violent force being applied thereto, the abutment face being oblique relative to the axis of rotation of the rotor. | 06-23-2011 |
| 20110150567 | MECHANICAL DRIVE DEVICE FOR DRIVING THE HIGH PRESSURE SUB ASSEMBLYSUB ASSEMBLY OF AN AIRPLANE ENGINE - Providing manual mechanical drive to the high pressure sub assembly of a turbojet, in particular during endoscopic inspection of the high pressure turbine. According to the invention, a coupling element suitable for coupling with an external actuator such as a crank handle is fitted on the axis of a specific alternator that is normally driven mechanically via the high pressure sub assembly, thereby providing a coupling suitable for driving said high pressure sub assembly. | 06-23-2011 |
| 20110148051 | TOOL ATTACHMENT FOR INSTALLING KEY-LOCKING INSERTS, AND A KIT INCLUDING SUCH A TOOL ATTACHMENT - A tool attachment for installing key-locking inserts, and a kit including such a tool attachment. For installing the key-locking insert, which is configured to be locked by a key, the tool attachment can be mounted on a power head, and connected to a pneumatic power supply, and includes a tightening torque transmission device, tightening the insert, and, in a casing, a key striker device configured to crimp the key onto the insert when crimping pressure is applied to the key by the pneumatic power supply. The striker device includes plural plates that are substantially perpendicular to the tightening axis. Crimping pressure applied suddenly to the plates inside the casing drives the key striker device and to crimp the keys. The tool attachment does not include moving mechanical parts, and is highly reliable. | 06-23-2011 |
| 20110143089 | MECHANICAL COMPONENT COMPRISING AN INSERT MADE OF COMPOSITE - A method of manufacturing a mechanical component, and winding device to implementing the method. The component includes at least one insert of metal matrix composite, within which matrix ceramic fibers extend, the composite insert obtained from a plurality of coated filaments each including a ceramic fiber coated with a metal sheath. The method manufactures an insert preform by winding a bonded lap or bundle of coated filaments about a cylindrical component. At least some of the winding is performed in at least one rectilinear direction. The method further inserts the insert preform in a first container; performs hot isostatic compaction of the first container; and machines the first container to form a rectilinear insert. | 06-16-2011 |
| 20110142615 | INNER WALL FOR A TURBOMACHINE NACELLE - An inner wall for a nacelle of a turbomachine, the inner wall including an outer annular fan casing for surrounding the fan blades and including at its upstream end a flange for fastening to a ring in axial alignment therewith, and a soundproofing inner annular structure for extending upstream from the fan blades, the fan casing extending substantially as far as an upstream end of the soundproofing structure such that the upstream flange of the fan casing is situated in a vicinity of the upstream end of the soundproofing structure. | 06-16-2011 |
| 20110142608 | TURBOJET NACELLE - The invention provides a nacelle for a bypass turbojet, the nacelle comprising: an aerodynamic fairing; a maintenance cover fastened to the aerodynamic fairing by means of at least one connection hinged about a longitudinal axis of the nacelle; a cold stream inner shroud and a cold stream outer shroud placed concentrically inside the aerodynamic fairing so as to define between them a flow passage for a cold stream, the inner shroud having at least one opening closed by a removable access hatch; and the outer shroud includes at least one opening closed by a removable access hatch that is fastened on the maintenance cover. | 06-16-2011 |
| 20110138926 | METHOD FOR TESTING THE COATING OF A VANE BASE - A method for testing a coating for blade roots, includes: providing a disk test piece including at least one bearing surface and a blade test piece including at least one bearing surface coated with the coating to be tested, the blade test piece including two test piece halves adapted to be engaged on either side of the disk test piece, and subjecting the blade test piece engaged with the disk test piece to tensile cycles during which the test pieces undergo tensile stress with respect to each other in a tensile direction, the tensile strain being transmitted via the bearing surfaces contacting the blade test piece and the disk test piece. The method allows for very faithful reproduction of the behavior and ageing of the coating and thus allows for accurate evaluation of the quality of the coatings. | 06-16-2011 |
| 20110138773 | DEVICE FOR MOUNTING A FLAME-HOLDER ARM ON AN AFTERBURNER CASING - A flame-holder device for an afterburner of a turbofan, the turbofan including a first inner annular casing and a second inner annular casing, these defining a passage for a primary flow, and an outer annular casing defining with the first inner annular casing a passage for a secondary flow, including at least one arm-support made of metallic material configured to be fixed to the outer casing by an upper plate and at least one flame-holder arm of a one-piece structure of composite material including two mutually attached walls arranged to define a groove whose profile is approximately a V. The walls support, on their upper part situated in the secondary flow, a fixing mechanism for fixing to the arm-support. The upper parts are approximately planar and are positioned facing each other. | 06-16-2011 |
| 20110135496 | COOLING OF THE TIP OF A BLADE - A turbine blade including an open cavity at its distal tip, the cavity being defined by a bottom wall and a side wall extending along the perimeter of the distal tip in an extension of the upper and lower walls of the blade, the side wall of the cavity including an opening in a vicinity of the leading edge of the blade opening into the cavity. A deflector extends at least in the middle portion of the cavity between the leading edge and the trailing edge. | 06-09-2011 |
| 20110129336 | ASSEMBLY INCLUDING A TURBINE DISK FOR A GAS TURBINE ENGINE AND A BEARING-SUPPORTING JOURNAL, AND COOLING CIRCUIT FOR THE TURBINE DISK OF SUCH AN ASSEMBLY - The invention relates to an assembly including a turbine disk ( | 06-02-2011 |
| 20110129332 | AXIAL-CENTRIFUGAL COMPRESSOR HAVING SYSTEM FOR CONTROLLING PLAY - In an axial-centrifugal compressor, the rotor of which includes an impeller, axial play is controlled by a special air ventilation to the rotor, by a circuit including two parallel arms, flow rates of which are both controlled by respective veins, and moreover the temperature in one of them is changed by a heat exchanger. The ventilation air is thus controlled, both in terms of temperature and flow rate. | 06-02-2011 |
| 20110129310 | ANGLE-ROUNDING METHOD AND TOOL - A method of angle rounding at an intersection between two surfaces of a workpiece, the method including machining away a minimum volume of material from the intersection of the two surfaces, thereby giving a convex rounded shape to the intersection of the two surfaces, the curved shape being located relative to the workpiece on the outside of a circular arc tangential to the two surfaces at the point where the curved shape connects with the two surfaces. | 06-02-2011 |
| 20110127352 | NOZZLE FOR A TURBOMACHINE TURBINE - A turbine nozzle for a turbomachine, including inner and outer annular platforms connected together by vanes, the inner platform carrying annular elements of abradable material co-operating with annular wipers of a rotor of the turbomachine to form a labyrinth seal, these elements of abradable material being carried by annular sheet-metal sectors of substantially L-, S-, or C-shaped section that are fastened by brazing or welding at their outer peripheries to the inner platform and at their inner peripheries to the elements of abradable material. | 06-02-2011 |
| 20110123341 | DEVICE FOR AXIAL RETENTION OF MOBILE VANES MOUNTED ON A ROTOR DISC - A device for axial retention of mobile vanes mounted on a rotor disc includes two open rings, superimposed. At least one of the rings includes a rotating stop mechanism configured to cooperate with at least one hook of the disc. The two open rings are mounted in a discontinuous groove formed in the hooks, at the end of teeth situated on the periphery of the rotor disc, such that the rotating stop mechanism of the first ring is placed in the opening of the second ring. The significance of contact surfaces between the two rings allows a damping of vibrations during operation. | 05-26-2011 |
| 20110121150 | UNIT FOR LOCKING RING SECTORS ON A TURBOMACHINE CASING, COMPRISING RADIAL PASSAGES FOR GRIPPING IT - A unit locking a ring sector attachment device onto an aircraft turbomachine casing, the unit including two clamping arms connected to each other at their aft ends by a connecting arm extending approximately parallel to the general direction between the two clamping arms. The unit also includes a passage enabling gripping of the unit on each side of a fictitious median plane orthogonal to the circumferential direction, each passage being formed in the connecting arm, extending along a direction line approximately parallel to the direction between the arms. | 05-26-2011 |
| 20110120144 | ANNULAR COMBUSTION CHAMBER FOR A TURBOMACHINE - An annular combustion chamber for a turbomachine, such as a jet engine or a turboprop engine for an aircraft, including at the downstream end of one of its external or internal walls of revolution an annular flange for fastening to a casing of the turbomachine, the downstream end of the other wall of revolution of the chamber including a bearing mechanism which are spaced apart from another casing of the turbomachine when cold and bear radially on this casing when hot. | 05-26-2011 |
| 20110118865 | METHOD OF DETERMINING THE CONDITIONS OF A PHASE FOR MACHINING A WORKPIECE WITH MODULATED CUTTING RATE - A method of determining conditions for machining a part so as to avoid vibration appearing during the machining. A machining stage is simulated by provisionally setting parameters of a function for modulating cutting speed, by deducing a corresponding surface state, by modifying parameters iteratively with the machining stage being simulated each time until the surface state reaches an acceptable value, and by performing the machining stage by causing the cutting speed to vary in application of the corresponding modulation function. | 05-19-2011 |
| 20110116931 | METHOD FOR INCREASING THE COEFFICIENT OF ADHESION BETWEEN TWO PARTS ROTATING AS ONE WITH A ROTOR - A method for increasing the coefficient of adhesion between two parts that rotate as one with a rotor, for example a turbomachine rotor, those parts pressing against one another via pressing faces. The method includes milling at least one of the pressing faces so as to modify its surface finish and increase its roughness, then covering the or each machined face with a thin layer of a material that is hard and has a high coefficient of friction. | 05-19-2011 |
| 20110113789 | GAS TURBINE ENGINE COMBUSTION CHAMBER COMPRISING CMC DEFLECTORS - A gas turbine engine combustion chamber including at least one deflector mounted on the chamber end wall and including an opening for a carburetted air supply device. The deflector includes an opening, corresponding to the chamber end wall opening, with an annular cylindrical part for attachment to the wall, the cylindrical part including a mechanical attachment mechanism collaborating with a complementary attachment mechanism on a metal sleeve secured to the wall and a cylindrical centering cup fixed by one end to the sleeve and housed inside the cylindrical part of the deflector. | 05-19-2011 |
| 20110113748 | GUIDING AN IGNITION SPARK PLUG IN A TURBOMACHINE COMBUSTION CHAMBER - The invention relates to a turbomachine combustion chamber including at least one ignition spark plug carried by an outer casing and extending in guide means carried by a wall of the chamber, the wall forming a body of revolution, the guide means comprising a tubular guide having the spark plug passing axially therethrough and mounted with axial and transverse clearance on a chimney fastened to the wall of the chamber and opening out into the chamber. In order to reduce wear of the spark plug in operation, the spark plug is mounted by being fastened in a sheath, the tubular guide being slidably mounted around the sheath. | 05-19-2011 |
| 20110113747 | GUIDE FOR AN IGNITION PLUG IN A TURBOMACHINE COMBUSTION CHAMBER - The invention relates to a turbomachine combustion chamber including at least one ignition plug carried by an outer casing and extending within guide means carried by a wall of the chamber, said wall forming a body of revolution, and including a tubular guide having the plug passing axially therethrough and mounted with axial and transverse clearance on a chimney fastened to the wall of the chamber and opening out into the chamber, the guide extending at least in part in an air flow stream outside the chamber. The guide means comprise a deflector surrounding the portion of the guide that is situated in the air flow stream so as to reduce the aerodynamic pressure on the guide and reduce the contact pressure of the guide on the plug. | 05-19-2011 |
| 20110113627 | METHOD OF MANUFACTURING A BLADING COMPONENT - A method of manufacturing a metal blading sector for low-pressure guide vanes of a turbomachine of which at least one blade includes an internal cavity configured to accept or communicate with a gas detection probe and at least one hole formed in the wall constituting a passage for gas from a low-pressure zone of the turbomachine toward the cavity and the probe through the fitting, into a casting mold, of a core corresponding to the cavity and the casting of a molten metal in the cavity of the casting mold. The core includes, for each hole for communication with the cavity, a protrusion penetrating the internal surface of the mold and constituting the only element holding the core in position in the casting mold. | 05-19-2011 |
| 20110110788 | BLADE WITH 3D PLATFORM COMPRISING AN INTER-BLADE BULB - A blade for a turbomachine impeller including an airfoil, and a platform extending at one of the ends of the airfoil in a direction globally perpendicular to a longitudinal direction of the airfoil, the blade configured, together with other identical blades, to form a ring around a ring axis, with the adjacent blade platforms joining in pairs so as to form an inter-airfoil surface linking the pressure surface of one airfoil to the suction surface of the neighboring airfoil. In this blade, the inter-airfoil surface includes, in an upstream half of the airfoil, a boss located closer to the pressure surface than to the suction surface, and a recessed passage located between the same and the suction surface. | 05-12-2011 |
| 20110110787 | STATOR VANE FOR 3D COMPOSITE BLOWER - A method of fabricating a guide vane. The method produces a fiber preform by 3D weaving a single piece, the preform including a first portion extending along the longitudinal axis and constituting the preform for an airfoil of the vane, and at a longitudinal end of the first portion, a second portion constituting the preform for the platform of the vane, the second portion being produced as a first layer and a second layer facing the first layer and separated from the first layer by unlinking without cutting while producing the preform; folding the first and second layers such that each of them lies in a plane perpendicular to the longitudinal axis, substantially symmetrically to each other relative to the first portion, and such that a first region of the first layer covers a second region of the second layer in front of a front edge of the first portion; conforming the preform in a mold; and densifying the preform with a polymer matrix. | 05-12-2011 |
