Patent application number | Description | Published |
20080232953 | INTER-TURBINE CASING WITH COOLING CIRCUIT, AND TURBOFAN COMPRISING IT - The invention relates to an inter-turbine casing ( | 09-25-2008 |
20080240845 | JOINING DEVICE FOR JOINING TWO ASSEMBLIES, FOR EXAMPLE FOR A STATOR OF A TURBOMACHINE - The present invention relates to a joining device ( | 10-02-2008 |
20090004006 | DEVICE FOR COOLING SLOTS OF A TURBOMACHINE ROTOR DISK - The invention relates to a device for cooling the slots of a turbomachine rotor disk, the device comprising a rotor disk having a plurality of slots and a flange that extends upstream from a radially upstream face of the disk. The device also comprises a retaining annulus having a flange that is placed around the flange of the disk, co-operating therewith to provide a space forming a cooling air diffusion cavity, said cavity opening out into the bottom of each of the slots of the disk, and a plurality of air admission orifices opening out into the diffusion cavity at the upstream end thereof, the cavity having means at its downstream end for reducing the flow rate of air penetrating into the slots of the disk that are situated radially in register with air admission orifices. | 01-01-2009 |
20090004018 | DEVICE FOR AXIALLY RETAINING BLADES MOUNTED ON A TURBOMACHINE ROTOR DISK - The invention relates to a device for axially retaining blades mounted on a turbomachine rotor disk, the device comprising a rotor disk having a plurality of slots and a flange extending radially outwards, cooperating with a bearing face of the disk to define a groove that is open radially outwards. The device also comprises a plurality of blades, each having a root mounted in a slot of the disk, each blade root having a respective radial bearing face that corresponds to the bearing face of the disk and that has at least one nib extending radially inwards thereover to define a notch that is open radially inwards, and a retaining ring that is mounted against the bearing faces of the disk and of the blade roots, said retaining ring being housed in the groove of the disk, being held outwardly in the notches of the blade roots, and being constituted by a plurality of angular segments placed end to end. | 01-01-2009 |
20090004023 | DEVICE FOR COOLING THE SLOTS OF A ROTOR DISK IN A TURBOMACHINE HAVING TWO AIR FEEDS - The invention relates to a device for cooling slots in a turbomachine rotor disk, comprising a rotor disk having a plurality of slots and a flange. The device also comprises blades, each having its root mounted in a respective slot, a retaining annulus having one end mounted against the upstream radial face of the disk, and a flange disposed around the flange of the disk and co-operating therewith to define a space forming a cooling air diffusion cavity that opens out into the bottom of each of the slots, together with air admission orifices opening out into the diffusion cavity at the upstream end thereof, the end of the retaining annulus that is mounted against the upstream radial face of the disk including a plurality of openings that open out radially into the bottom of each of the slots in the disk, at the upstream ends thereof. | 01-01-2009 |
20090104018 | COOLED BLADE FOR A TURBOMACHINE - The present invention relates to a cooled blade forming an upstream guide vane element for a turbomachine, wherein the airfoil comprises a longitudinal cavity with a first opening at one end and a second opening at the other end, a tubular sleeve being housed in the cavity with a first end in the first opening and a second end in the second opening, first spacers on the side of the first end and second spacers on the side of the second end of the sleeve making a space between the outer face of the sleeve and the wall of the cavity, the blade being arranged so that the sleeve is inserted into the cavity through the first opening. | 04-23-2009 |
20090123279 | CONNECTION OF RADIAL ARMS TO A CIRCULAR SLEEVE VIA AXES AND SPACERS - The connection assembly of an arm ( | 05-14-2009 |
20090129917 | SEALING A ROTOR RING IN A TURBINE STAGE - A turbine stage in a turbomachine, the stage comprising a wheel mounted in a ring carried by a turbine casing, and a nozzle situated upstream from the wheel and including an annular fastener rim for fastening to the turbine casing, sealing being provided between the outer rim of the nozzle and the upstream end of the ring by a radial annular sheet bearing axially at its inner and outer peripheries against a downstream face of the outer rim of the nozzle, with its middle annular portion being axially spaced apart from the outer rim of the nozzle and bearing axially against the upstream end of the ring. | 05-21-2009 |
20090134270 | MEANS FOR PREVENTING THE ROTATION OF A PIN SUPPORTING A TURBINE ENGINE SUSPENSION MEMBER - The present invention relates to a device for mounting a suspension member on the casing of a turbine engine comprising a yoke with at least one lug, secured to the casing, a pin fixed to said yoke supporting said member via a ring surrounding the pin, said device comprising a rotation-prevention means comprising a counter-rotation plate attached to the lug. The device is one wherein said plate and the pin comprise an assembly consisting of a peg and of a cutout or a hole, into which said peg fits in order to prevent the pin from rotating in the yoke. | 05-28-2009 |
20090199534 | OIL RECOVERY DEVICE - It comprises two bearing supports ( | 08-13-2009 |
20110038667 | CONNECTING RADIAL ARMS TO A CIRCULAR FERRULE BY IMBRICATING ATTACHED PARTS - Assembly of the connection of an arm to a ferrule is done by imbricating a side wing ( | 02-17-2011 |
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 |
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 |
20120195766 | CMC TURBINE ENGINE BLADES AND A ROTOR WHEEL FOR A TURBINE ENGINE AND A TURBINE ENGINE INTEGRATING THEM - A rotor wheel of a turbine engine includes a plurality of CMC blades each having a first portion constituting a blade airfoil and root and made as a single piece with a second portion forming an outer platform. The blades are held under twisting prestress by mutual engagement via contact zones between the outer platforms of adjacent blades, and the contact zones that are situated on opposite sides of the outer platform of a blade are defined by at least one insert that is integrated in the outer platform and that is, for example, made of a carbon-based material. | 08-02-2012 |
20130028746 | TURBINE ENGINE TURBINE BLADE MADE OF A CERAMIC-MATRIX COMPOSITE WITH RECESSES MADE BY MACHINING - A turbine engine turbine blade of ceramic matrix composite. The root of the blade includes a single densified fiber preform including at least one recess made by machining, each point of the root of the blade being situated at a distance from a free surface of the root that is no greater than twice the maximum penetration distance into the preform of densification gas for densifying the preform, and the distal portion of the root of the blade includes a distal wall that is continuous and in a single piece. | 01-31-2013 |
20130183142 | ARRANGEMENT FOR THE GUIDING OF THE FLOW OF A LIQUID IN RELATION TO THE ROTOR OF A TURBOMACHINE - An arrangement for the guiding of the flow of a liquid in relation to the rotor of a turbomachine, which includes an intermediary disc and a downstream disc of which the internal diameter and the axial position of the discs are defined in such a way that the tank is arranged inside the discs. The rotor supports a guide flange with an element of revolution of which the diameter of the section increases in the downstream direction, according to the direction of flow of the gases in the turbomachine. The downstream axial end of the flange is fixed to a portion of the rotor located downstream of the downstream disc and the upstream axial end of the flange is connected to the internal radial end of the intermediate disc. | 07-18-2013 |
20140205442 | SEALING DEVICE FOR A TURBOMACHINE TURBINE NOZZLE - A sealing device for a nozzle of a turbomachine turbine including a turbine rotor. The turbine nozzle includes at least one inner annular platform. The turbine rotor includes a downstream spoiler disposed substantially axially. The sealing device includes at least one sealing sheet disposed, radially, between the inner face of the inner platform and the downstream spoiler of the rotor of the turbine so as to form an overlap clearance. | 07-24-2014 |
20140205463 | Turbine Engine Rotor Including Blade Made of Composite Material and Having an Added Root - A turbine rotor includes a plurality of blades of composite material comprising fiber reinforcement densified by a matrix. Each blade comprises a blade body extending between an inner end having a blade root and an outer end forming the tip of the blade. The rotor also includes outer platform elements of composite material comprising fiber reinforcement densified by a matrix, each outer platform element including an opening in which the outer end of a blade is engaged. The portion of the outer end of each blade that extends beyond the outer platform element includes a slot or a notch for receiving a locking element. | 07-24-2014 |