Patent application number | Description | Published |
20090191049 | TURBOJET COMPRESSOR - The invention relates to a turbojet compressor comprising a shroud and a plurality of blades, each fixed via its root to the shroud. Level with each blade root, the shroud presents a suction-side ramp and a pressure-side ramp extending from the trailing edge of the blade to beyond its leading edge. The pressure-side and suction-side ramps join together upstream from the leading edge of the blade to form a projection presenting a profile that is twisted about the axis of the shroud so as to force the gas stream flowing in each flow passage to go round the blade root essentially on the suction-side thereof, and the suction-side ramp presents a profile that is inclined relative to the outside surface of the shroud so as to deflect the gas stream flowing in the corresponding flow passage from the suction-side surface of the blade towards the pressure-side surface of the adjacent blade. | 07-30-2009 |
20100046868 | BEARING SUPPORT JOURNAL AND ASSEMBLY OF SUCH A JOURNAL AND A SEALING SLEEVE - A bearing support journal ( | 02-25-2010 |
20110058942 | BALANCING DEVICE AND METHOD - The invention relates to a balancing device comprising a nut | 03-10-2011 |
20110097206 | ANNULAR FLANGE FOR FASTENING A ROTOR OR STATOR ELEMENT - A radial annular flange of a rotor or stator element of a turbomachine including, at an inner/outer periphery, alternating solid portions and hollow portions, the solid portions including orifices for passing fastener bolts. The flange in the bottom of at least one hollow portion has a radius relative to the axis of the turbomachine that is less/greater than the radius of a circle that is tangential to the outsides/insides of the orifices for passing bolts through the solid portions. | 04-28-2011 |
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 |
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 |
20110239661 | ROTOR FOR A GAS TURBINE ENGINE COMPRISING A ROTOR SPOOL AND A ROTOR RING - A one-piece rotor spool ( | 10-06-2011 |
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 |
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 |
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 |
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 |
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 |
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 |
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 |
20120244001 | RETAINING RING ASSEMBLY AND SUPPORTING FLANGE FOR SAID RING - A retaining ring assembly for at least one blade of a rotor disk of a turbine engine and a supporting flange for the ring. The flange and the ring are rotating parts having an axis X, the flange including an attachment edge configured to be connected to the rotor disk and a free edge configured to bear against the retaining ring; and the flange bears against the ring such that the bearing force of the flange on the ring has an axial component and a radial component relative to the axis of revolution X. | 09-27-2012 |
20130064619 | METHOD OF MACHINING SLOTS IN A TURBINE DISK OF A TURBINE ENGINE - A machining method for machining peripheral slots in a disk of a turbine of a turbine engine, such as an airplane turboprop or turbojet, the method including: machining the slots by reaming using a substantially cylindrical reamer of length greater than an axial thickness of the disk, and extending substantially parallel to the axis of the disk, outlines of the slots being machined by moving the reamer perpendicularly to its axis along the profile of each slot. | 03-14-2013 |
20130133194 | METHOD OF FABRICATING A TURBINE ENGINE DRUM - A method of fabricating a turbine engine drum including at least two rotor disks, the method including: positioning the two disks on a common axis spaced apart from each other and in a predetermined angular position relative to each other; placing a wall forming a body of revolution between the two disks coaxially about their common axis; driving the wall in rotation about its axis; and moving the disks axially towards the wall so as to put the disks into contact with ends of the wall and thus welding the disks to the wall by inertial friction welding. | 05-30-2013 |
20130209238 | SET OF ROTOR DISKS FOR A TURBINE ENGINE - A set of rotor disks for a turbine engine, or an airplane turboprop or turbojet, the set including disks rigidly connected together by bolts and shaped at their outer peripheries with slots for mounting blade roots. Each disk includes a rim extending radially and not having any axial flanges, two consecutive disks being connected together with help of an axially-extending ferrule that is fastened to the rims of the disks and that is fitted with a holder plate for holding the blade roots of the downstream disk. | 08-15-2013 |
20140023505 | DEVICE FOR THE BLIND COUPLING OF FLUIDIC, ELECTRICAL OR SIMILAR SUPPLIES, TO A RECEIVING CONTROL MECHANISM - The device ( | 01-23-2014 |
20140072405 | DEVICE FOR DE-ICING A TURBOMACHINE SEPARATOR - A turbomachine separator including a device for de-icing the turbomachine separator, and a distribution element, wherein the separator is formed by an inner ferrule and an outer ferrule, wherein the inner ferrule is fitted with a first mounting flange and a second mounting flange, the de-icing device including an internal air supply duct, able to inject air into the separator, wherein the internal supply duct is connected to an air inlet, wherein the air inlet forms a projection external to the de-icing device, allowing a flexible connection with a tube of the distribution element for conveying hot air, a first fastener constructed and arranged to be attached to the first mounting flange; and a second fastener constructed and arranged to be attached to the second mounting flange. | 03-13-2014 |
20140133989 | TURBINE ENGINE PART FORMING A COMPRESSOR STATOR OR A TURBINE NOZZLE, AND METHOD FOR FABRICATING SAME - A turbine engine part forming a compressor stator or a turbine nozzle and including an inner shroud, an outer shroud, and vanes extending substantially radially between the inner and outer shrouds and being secured thereto. The part is made of composite material and is obtained by densifying a fiber preform with a matrix. The fiber preform includes a set of yarns extending continuously along a path passing longitudinally along the preform portions of at least two consecutive vanes by passing through the inner shroud preform portion and the outer shroud preform portion, and the woven fiber reinforcement yarns extends continuously in the circumferential direction along an inner shroud segment and along an outer shroud segment between which the consecutive vanes extend. | 05-15-2014 |
20140147264 | TURBINE ENGINE STATOR WHEEL AND A TURBINE OR A COMPRESSOR INCLUDING SUCH A STATOR WHEEL - A turbine nozzle comprises a plurality of composite material vanes, each vane comprising an inner platform, an outer platform with attachment tabs on the outside, and at least one airfoil extending between the inner and outer platforms and secured thereto. The attachment tabs of the vanes are engaged on a metal assembly ring supporting all of the vanes, extending continuously along the outer platforms of adjacent vanes, and forming a distinct assembly part between the vanes and a turbine casing. | 05-29-2014 |
20140154076 | DEVICE FOR SUPPLYING AND DISTRIBUTING FLUID - The device ( | 06-05-2014 |
20140205457 | SYSTEM FOR CHANGING THE PITCH OF THE BLADES OF A PROPELLER - The system comprises a linear-displacement fluidic actuator ( | 07-24-2014 |
20140271151 | OIL TRANSFER SYSTEM ON ROTATING SHAFT - Lubrication system for a device ( | 09-18-2014 |
20140341722 | UNLOCKABLE DEVICE FOR AXIALLY ARRESTING A SEALING RING WITH WHICH AN AIRCRAFT TURBOMACHINE MODULE ROTOR WHEEL MAKES CONTACT - A device for axially arresting a sealing ring made of an abradable material in contact with a periphery of an aircraft turbomachine module rotor, the device having a first reference central axis, and including: a support including a support opening defining a circular track centered on a second axis at a distance from the axis; and an axial stop part including an extraction passage centered on a third axis at a distance from the axis, and defining a complementary circular track around its periphery, cooperating with the track to allow the part to rotate about the axis, between an axial stop position for the sealing ring, and a position to extract the ring through the extraction passage. | 11-20-2014 |
20150198221 | BALANCING DEVICE AND METHOD - A balancing device including a nut having an internal thread, and a countersunk collar is disclosed. The countersunk collar has a through-hole with a diameter greater than the diameter of the internal thread of the nut. The countersunk collar includes a balancing weight. | 07-16-2015 |
20150204339 | SYSTEM FOR HOLDING BLADES AND ASSEMBLY METHOD - The invention relates to a blower ( | 07-23-2015 |
20150219014 | DEVICE FOR THE TRANSFER OF HEAT BETWEEN A LUBRICATION PIPE AND A TURBOMACHINE BLADE PITCH ACTUATOR CONTROL HYDRAULIC PIPE - An aircraft turbomachine including a lubricant circulation pipe and a hydraulic pipe for controlling an actuator for changing a pitch of blades of a propeller of the turbomachine. The assembly, integrated to a receiver of the turbomachine, further includes a mechanism forming a thermal bridge between the lubricant circulation pipe and the hydraulic pipe. | 08-06-2015 |