Patent application number | Description | Published |
20090155061 | SECTORIZED NOZZLE FOR A TURBOMACHINE - A sectorized nozzle for a turbomachine, the nozzle being made up of cylindrical sectors and comprising two annular platforms interconnected by substantially radial vanes, together with an annular rail for supporting elements of abradable material, each inner platform having longitudinally-extending edges that are V-shaped, and each rail sector having, on at least one of its sides, means for bearing axially on corresponding means provided on an adjacent nozzle sector. | 06-18-2009 |
20090155085 | TURBOMACHINE BLADE THAT IS CAST WITH A LOCAL FATTENING OF THE SECTION OF THE AIRFOIL - The monocrystalline turbomachine blade according to the invention that is cast and directionally solidified, comprising:
| 06-18-2009 |
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 |
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 |
20120328415 | VIBRATION DAMPER COMPRISING A PEG BETWEEN OUTER PLATFORMS OF ADJACENT COMPOSITE-MATERIAL BLADES OF A TURBINE ENGINE ROTOR WHEEL - A vibration damper between outer platforms of adjacent composite-material blades of a turbine engine rotor wheel, the damper including a peg having a substantially spherical portion at each of its two ends, and two hollow inserts for being received in tangential cavities that are provided facing each other in outer platforms of two adjacent composite-material blades of a turbine engine rotor wheel, each spherical portion of the peg coming to bear with point contact against the inside of one of the inserts. | 12-27-2012 |
20130230404 | METHOD OF OPTIMIZING THE PROFILE OF A COMPOSITE MATERIAL BLADE FOR ROTOR WHEEL OF A TURBINE ENGINE, AND A BLADE HAVING A COMPENSATED TANG - A method optimizing a composite material blade profile for a rotor wheel of a turbine engine, and a blade including a tang compensated by the method. The method includes: compensating a blade airfoil by subdividing the airfoil into slices, and for each airfoil slice and a predetermined rotation speed of a disk of the wheel, calculating centrifugal force applied to the slice, calculating an aerodynamic force moment acting on a bottom section of the slice, and calculating shift values to be applied to a center of gravity of the slice to cancel the aerodynamic force moment; and compensating the blade tang by calculating centrifugal force applied to a blade portion situated beyond the airfoil neck, calculating an aerodynamic force moment acting on a bottom section of the blade tang, and calculating shift values to be applied to a center of gravity of the blade tang to cancel the aerodynamic force moment. | 09-05-2013 |
20140105732 | LABYRINTH SEAL FOR GAS TURBINE ENGINE TURBINE - A turbine for a gas turbine engine comprising at least one turbine stator and one turbine rotor, said turbine stator comprising at least one inner annular platform, said inner platform comprising a radial wall delimiting at least one cavity between the turbine stator and the turbine rotor, wherein the turbine rotor comprises at least one elongate element positioned substantially axially and defining a sealing baffle in said cavity, and in that the turbine stator comprises at least one element made of abradable material designed to engage with said elongate element of the turbine rotor so as to form a labyrinth seal. | 04-17-2014 |
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 |