| Patent Number |
Title Of Patent |
Date Issued |
| 7422644 |
Thin parts made of .beta. or quasi-.beta. titanium alloys; manufacture by forging |
September 9, 2008 |
| The present invention provides non-axially symmetrical manufactured parts of thickness less than 10 mm, made of .beta. or quasi-.beta. titanium alloy, having a core microstructure constituted by whole grains presenting a slenderness ratio greater than 4 and an equivalent diameter lyi |
| 7351030 |
Connection device for making a connection between a turbomachine nozzle and a feed enclosure for |
April 1, 2008 |
| A connection device between a nozzle and a feed enclosure for feeding cooling fluid to at least one injector in a turbomachine, the device comprises at least one bushing having open axial ends engaged in orifices in a wall of the nozzle and in a wall of the feed enclosure, together w |
| 7347672 |
Rotor disk balancing device, disk fitted with such a device and rotor with such a disk |
March 25, 2008 |
| A rotor disc includes a rim and a balancing device, which includes housings formed in the rim, and balancing masses housed in at least some of the housings. |
| 7341380 |
Installation layout for two coaxial shaft lines |
March 11, 2008 |
| In an assembly with two concentric shafts, the internal shaft projecting beyond the external shaft, a seal support sleeve placed between the shafts has a conical shape and bears on a spacer mounted on the external shaft between an assembly nut of the forward end of the external shaft |
| 7340882 |
Turbomachine with means for axial retention of the rotor |
March 11, 2008 |
| The turbomachine of the invention extends longitudinally along an axis, and includes a rotor attached to drive shaft, arranged to rotate around an axis, supported by at least a first bearing, mounted on the fixed structure of the turbomachine by a bearing support element. The turboma |
| 7336281 |
Optimizing ergonomic movement of a virtual dummy |
February 26, 2008 |
| A multi-agent method and system for moving a virtual dummy in a virtual environment, the dummy being defined by an overall position and by a plurality of degrees of freedom for joints. The method includes a contribution from an attraction agent acting on the plurality of degrees of f |
| 7335616 |
Target for vaporizing under an electron beam, a method of fabricating it, a thermal barrier and |
February 26, 2008 |
| The invention relates to a composite target in the form of a bar made of ceramic powders and designed to be evaporated under an electron beam, the target comprising zirconia and at least one zirconia stabilizer. In characteristic manner, said target is wherein said zirconia stabilizer is |
| 7334332 |
Method of manufacturing a hollow blade for a turbine engine |
February 26, 2008 |
| The invention relates to a method of manufacturing a hollow blade for turbine engine comprising a foot and a rotor blade, the method comprising a production stage of two external parts (14) as well as an assembling stage via diffusion bonding of these two external parts so as to obtain a |
| 7328582 |
Annular combustion chamber for a turbomachine |
February 12, 2008 |
| An annular turbine engine combustion chamber configured so that in an axial half-section, values of first acute angles formed between a line that is effectively the median of the half-section located between an external axial wall and an internal axial wall, and the principal directi |
| 7326035 |
Device for attaching a moving blade to a turbine rotor disk in a turbomachine |
February 5, 2008 |
| An attachment device for attaching a blade to a turbine rotor disk in a turbomachine, the blade root forming a male portion engaged and held radially in a cavity of complementary shape in the rotor disk, with means for preventing the blade root from moving axially in the cavity, the |
| 7325770 |
Mounting of engine onto an aircraft structure |
February 5, 2008 |
| The invention pertains to an engine mount onto an aircraft structure comprising at least one connection means between a first and a second element such as an engine case and said structure, characterized by the fact that said connection means comprises an eccentric member housed in a |
| 7325307 |
Installation for shaping a hollow blade |
February 5, 2008 |
| A hollow blade is shaped by superplastic inflation of a blank made up of welded-together sheets. A die comprising two hollow shapes clamping the outline of the blank is placed inside an autoclave-forming enclosure in order to subject the blank to superplastic inflation, and the two hollo |
| 7322181 |
Turbofan engine with the fan fixed to a drive shaft supported by a first and a second bearing |
January 29, 2008 |
| The turbojet includes a fixed structure, a fan rotor fixed to a drive shaft supported by a first bearing and a second bearing. The second bearing is mounted on the fixed structure through a bearing support part. The first bearing is mounted on the fixed structure of the turbojet thro |
| 7322180 |
Turbo-jet engine with fan integral with a drive shaft supported by first and second bearings |
January 29, 2008 |
| A turbo-jet engine including a fixed structure and a fan rotor mounted on a drive shaft supported by a first bearing and a second bearing. The engine further comprises an axial retaining device configured to form an emergency bearing and to cooperate with the fixed structure and mounted |
| 7318685 |
Tension decoupler device |
January 15, 2008 |
| A tension decoupler includes first frangible rupture members, arranged in parallel to each other, and second structural rupture members, arranged in parallel to each other and parallel to the first rupture members. The frangible rupture members and the structural rupture members are desi |
| 7318466 |
Lost wax casting method |
January 15, 2008 |
| A method of manufacture of a multilayer ceramic shell mould out of a master pattern includes the steps of dipping the master pattern in a first slip containing ceramic particles and a binder, depositing sand particles to form a contact layer, dipping the master pattern in a second sl |
| 7311493 |
Metal sheet, including means for fixing it to a support and a gasket seal |
December 25, 2007 |
| The metal sheet of the invention includes means for fixing it to a support and a seal gasket laid out along these means. The fixing means comprise at least one lumen provided on the metal sheet by punching, with a cavity for receiving a head of a fixing component corresponding to a metal |
| 7309209 |
Device for tuning clearance in a gas turbine, while balancing air flows |
December 18, 2007 |
| A device for tuning clearance at rotor blade tips in a gas turbine rotor, the device comprising at least one annular air flow duct that is mounted around the circumference of an annular casing of a stator of the turbine, the annular air flow duct being designed to discharge air onto the |
| 7305898 |
Installation for non-destructive inspection of a part |
December 11, 2007 |
| An installation for non-destructive inspection makes use simultaneously of sensors responsive to different physical characteristics. In an example, a sensor support, e.g. a kind of carriage having running wheels via which it comes into contact with the surface to be inspected, is fitted |
| 7299621 |
Three-spool by-pass turbojet with a high by-pass ratio |
November 27, 2007 |
| The invention relates to aerodynamically matching the rear fan of a turbojet having two fans and a low-pressure compressor at the front of the intermediate casing, said fans being driven by two independent shafts. Said compressor is disposed between the blades of the two fans and inc |
| 7296415 |
Labyrinth seal device for gas turbine engine |
November 20, 2007 |
| This invention refers to a labyrinth seal for a gas turbine engine incorporating from upstream to downstream ends, a high pressure compressor with a rotor, a diffuser and a fixed wall element forming at least one part of the internal envelope of the combustion chamber said seal compr |
| 7296397 |
Ventilation system for a convergent divergent exhaust nozzle |
November 20, 2007 |
| The invention relates to a ventilation system for a convergent divergent exhaust nozzle in a bypass turbojet comprising an afterburn chamber surrounded by an annular passage through which circulates a stream of cooling air, a convergent divergent axisymmetric nozzle arranged downstre |
| 7290982 |
Arrangement for the attachment of distributor sectors supporting vanes around an arc of a circle |
November 6, 2007 |
| The distributor sectors (25) of a turbomachine are secured adjacent to a casing (31) with sealing sectors (32) alternating with them in the axial direction. The distributor sectors (25) are provided with force resistant faces (37; 39) through which forces exerted on the distributor secto |
| 7290769 |
Sealing device with a brush gasket and flexible washer for a high-pressure turbine of a turbomac |
November 6, 2007 |
| A sealing device for sealing between two static portions of a turbomachine includes a brush gasket formed by a plurality of resilient bristles which are, at least in part, held in a housing. Each bristle has a main portion and a secondary portion interconnected by a bent portion. The sec |
| 7287955 |
Gas turbine clearance control devices |
October 30, 2007 |
| A clearance control device for controlling clearance between rotary blade tips and a stationary bushing of a gas turbine having a casing that is provided with at least two annular ridges, the clearance control device including a circular tuning unit that includes air circulation means fo |
| 7287389 |
Feeding energy to a gas terminal from a ship for transporting liquefied gas |
October 30, 2007 |
| The invention relates to feeding a gas terminal with energy from a ship transporting liquefied gas while said liquefied gas is being transferred between a tank of the ship and a tank of the gas terminal, wherein a portion of the energy produced by the propulsion system of the ship is |
| 7287383 |
Afterburner arrangement |
October 30, 2007 |
| The invention relates to a burner ring for turbofan jet engines. The ring includes an upstream annular envelope which forms a channel which is open axially in the downstream direction, and a manifold for injecting fuel into the channel. The ring includes multiple sectors connected togeth |
| 7281892 |
Control lever for the pitch angle of a blade in a turbomachine |
October 16, 2007 |
| A control lever for the pitch angle of a blade in a turbomachine, said lever having a first end intended to be mounted on a blade pivot so as to rotate it and a second end comprising a cylindrical peg for mounting on a control annulus, this peg being fixed by crimping of one of its ends |
| 7278827 |
Cooling air evacuation slots of turbine blades |
October 9, 2007 |
| A turbine blade of a turbomachine, having at least a bottom platform connected to the base of the blade by a bottom connection zone, and a cooling circuit consisting of at least one cooling cavity, of a plurality of evacuation slots arranged along the trailing edge of the blade, said |
| 7267301 |
Aircraft engine with means of suspension from the structure of an aircraft |
September 11, 2007 |
| An aircraft engine includes a mounting attached to an aircraft structure and transmitting forces between an engine casing and the aircraft structure. The mounting includes a fail safe assembly with a safety clevis with two lugs and a tab arranged between the two lugs. Either the clev |
| 7264441 |
Hybrid cycle high pressure compressor and turbine engine including such a compressor |
September 4, 2007 |
| The invention relates to a hybrid cycle HP compressor (104) for a turbine engine, comprising in particular a first rotor wheel (16), a first rectifier (118) and a second rotor wheel (20), as well as a separation slot (22) fitted between the first rectifier and the second rotor wheel |
| 7261784 |
Method of making a coating on a metal substrate and/or an article, such a coating, such a metal |
August 28, 2007 |
| The method of the invention enables a coating to be made on at least one face to be protected of a metal substrate and/or article in order to improve its performance in terms of resistance to wear by friction, in particular at high temperature. The method comprises the following steps: |
| 7255260 |
Assembly for the manufacture of a hollow mechanical part by diffusion bonding and superplastic f |
August 14, 2007 |
| A method for manufacturing an assembly including a stack of at least two primary parts, the primary parts being joined together around their periphery with the exception of a place forming a passage so as to define between the two of them a cavity, and the primary parts having, facing |
| 7241961 |
TIG welding method |
July 10, 2007 |
| A TIG welding method of welding a first part with a first wall and an end edge to a second part with a second wall and an edge along a junction surface between said edges and along which the first wall forms a salient angle with the second wall. The TIG welding electrode is moved along t |
| 7241112 |
Turbomachine blade, in particular a fan blade, and its method of manufacture |
July 10, 2007 |
| The composite turbomachine blade of the present invention comprises a preform made of yarns or fibers woven in three dimensions and a binder maintaining the relative disposition between the yarns of the preform. Said preform is made up of warp yarns and of weft yarns, the direction of |
| 7237959 |
Breakable coupling system for a turbojet fan shaft |
July 3, 2007 |
| The invention relates to a rotary shaft arrangement carrying equipment at one end and extending rearwards from the equipment, the shaft (1) being supported by a first bearing (2) behind the equipment, and by a second bearing (3) behind the first bearing (2), the first bearing (2) being |
| 7237378 |
Turbomachine with low noise emissions for aircraft |
July 3, 2007 |
| The invention relates to a turbomachine (1) for an aircraft comprising a gas generator (4) designed such that hot gases are ejected from a combustion chamber (28) towards the upstream side of the turbomachine, and also comprising a plurality of hollow mixer struts (40) connected to a |
| 7234920 |
Turbine casing having refractory hooks and obtained by a powder metallurgy method |
June 26, 2007 |
| A turbine stator casing comprising a jacket and fastener hooks for fastening a turbine distributor nozzle, the hooks projecting from the inside face of the jacket, said jacket being made of a first alloy by hot isostatic compression using metal powder, said fastener hooks being made |
| 7217100 |
Holding system for a rotor end plate |
May 15, 2007 |
| A device for holding an annular end plate against a radial face of a rotor disc, the disc having in the radial face an annular recess behind a collar extending radially outwards, and the end plate having, in its radially inner part, an annular base bearing against the radially outer |
| 7214034 |
Control of leak zone under blade platform |
May 8, 2007 |
| A system for controlling a leakage zone under platforms of blades of a turbomachine blade-wheel by liners having edges that flare radially inwards, and that are disposed in inter-blade cavities defined by the platforms, by upstream and downstream radial walls of the blades and by the |
| 7214030 |
Guide system for the outer pivot of a variable stator vane, for a turbojet stator |
May 8, 2007 |
| The system enables an increase in the guidance length of the outer pivot of the vane, so that the bushing can be extracted without needing to open the stator casing. It mainly includes a bushing placed inside a bossing of the stator, the length of which is greater than the length of the |
| 7213393 |
Device for supplying cooling air to exhaust nozzle flaps |
May 8, 2007 |
| A device for supplying cooling air to a hollow flap of an exhaust nozzle in a turbojet engine. The device includes a tube connecting the hollow flap to a cooling air source. The tube comprises at least one telescopic portion and at least one ball-joint connection. |
| 7210909 |
Connection between bladed discs on the rotor line of a compressor |
May 1, 2007 |
| A first rotor piece includes a first ring provided with a succession of holes and notches. An assembly is formed by a second rotor piece fixed to a third rotor piece. The second piece ends downstream in a second ring including holes. The third piece ends upstream in a third ring includin |
| 7210901 |
Assembly of sectors of a dispensing unit in a gas turbine |
May 1, 2007 |
| The retaining hooks (32) of a flange (22) of straightening sectors (20), bearing fixed blades in a turbomachine, are advantageously placed on an end plate (30) distinct from the casing (21) but assembled on the latter. In this way, these hooks no longer constitute weak points in the casi |
| 7204675 |
Cooled gas turbine engine vane |
April 17, 2007 |
| A cooled gas turbine vane includes a cast part and a longitudinal sleeve obtained by shaping metal sheet The cast part includes a longitudinal body provided with a longitudinal cavity having a first opening and a second opening at the ends The sleeve is mounted in the cavity by being |
| 7201529 |
Retaining device for a connection device, decoupling system equipped with such a device |
April 10, 2007 |
| A retaining device is designed to retain a portion of an assembly device. The portion of the assembly device is released during failure of the assembly device. The retaining device includes a fixed part, a mobile part capable of sliding with respect to the fixed part, a housing, formed |
| 7197882 |
Turbojet diffuser |
April 3, 2007 |
| A turbojet diffuser disposed between a compressor and a combustion chamber, and secured to an outer upstream annular flange of an outer casing of the combustion chamber by suspension means which comprise a first frustoconical wall extending from the outer longitudinal wall of the dif |
| 7194887 |
Press for holding and pressing a workpiece |
March 27, 2007 |
| The press of the invention includes a first component and a second component for holding and pressing a workpiece to be processed between them, the first component being driven into translation relatively to the second component by an air cylinder. Thus, the first component is floata |
| 7192250 |
Hollow rotor blade for the future of a gas turbine engine |
March 20, 2007 |
| A hollow blade includes an internal cooling passage, an open cavity located at the tip of the blade and bounded by an end wall and a rim and cooling channels that connect the said internal cooling passage to the outer face of the pressure wall. The cooling channels are inclined to the |
| 7185499 |
Device for passive control of the thermal expansion of the extension casing of a turbo-jet engin |
March 6, 2007 |
| The invention relates to a device for passive control of the thermal expansion of the extension casing of a turbo-jet engine, said extension casing surrounding the casing of the high pressure compressor of the turbo-jet engine, and including a flange for attachment to an upstream fla |
