Fan having a variable setting by means of differential rotation of the fan disks

A compressor rotor for a turbomachine including a shaft and at least two disks mounted on the shaft to hold a single set of vanes that are rotatably mobile about the rotational axis of the shaft, at least one first disk being mounted in a mobile manner on the shaft to be able to generate an angular gap in relation to the second disk and to trigger a rotation of the vanes about the radial axis of same, at least one of the two disks being shaped to receive at least one mechanism for attaching the vanes, the connection between the disk and the attaching mechanism enabling a rotation of the attaching mechanism about a radial axis, and connection is a ball-jointed connection that is tangentially and axially mobile.

Structure for suspending a twin prop-fan engine from a structural element of an aircraft

High-pressure turbine blades made of ceramic matrix composites

Device for shifting a propeller into reverse, comprising an actuator acting on a crank pin

A device controlling shifting of a propeller turbine engine into reverse mode, by acting on a shaft for controlling pitch of propellers. The device includes: at least one centrifugal weight arranged to drive the propellers into a flag position thereof under action of the centrifugal force; and an actuator that can rotate the control shaft to shift the pitch of the propellers from a traction mode to a reverse mode, passing through a zero pitch position. The centrifugal weight is in an unstable equilibrium position in relation to action of the centrifugal force when the control shaft shifts the pitch of the propellers through the zero pitch position. Further, an actuation mechanism exerts a torque on the control shaft when the centrifugal weight is in the unstable equilibrium position, to prevent it from staying in this position.

Mechanical transmission device for driving in rotation counter-rotating propellers of a dual-propeller turboprop

Turbomachine with axial force adjustment at a bearing

A turbomachine including a stator, a rotor mounted on a shaft, a first bearing and a second bearing downstream of the first bearing in a direction of air circulation at the inlet of the turbomachine, the first bearing forming an axial abutment linked to the stator, the second bearing including an inner ring secured to the shaft and an outer ring mounted on an arm secured to the stator, the second bearing including rolling elements in axial support on the inner ring and on the outer ring. The outer ring includes a radially extending ring portion. The turbomachine also includes an axial force application device mounted between the arm and the ring portion.

Reduction gear with epicyclic gear train having roller-bearing-mounted planet spindles

Turbine engine comprising a contrarotating propeller receiver supported by a structual casing attached to the intermediate housing

Suspension structure with variable geometry of a turboprop engine on a structural element of an aircraft

Device for lubricating an epicycloidal reduction gear

A device for assembly of a suspension member on a casing of a turbo-engine

A device for controlling the pitch of turboprop fan blades

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.

AIRCRAFT PROPULSION ASSEMBLY

The disclosure relates to an aircraft propulsion assembly including a nacelle having an intermediate housing and a front frame that is to be mounted downstream of an outer envelope of the intermediate housing. The front frame includes a deviation edge and an element forming a direct or indirect support for at least one flow deviation vanes, in particular, the deviation edge and the support-forming element are built into the outer envelope of the intermediate housing. 1. An aircraft propulsion assembly comprising at least one nacelle having a turbojet engine , said nacelle comprising a middle section provided with an intermediate housing and a downstream section comprising a thrust reverser device provided with at least one of the flow cascade vanes , and a front frame designed to be mounted downstream of an outer shroud of said intermediate housing , said front frame comprising a flow deviation edge and at least one element forming a direct or indirect support for the flow deviation vanes , characterized in that the flow deviation edge and the element supporting the flow cascade vanes are integrated into the outer shroud of the intermediate housing.2. The assembly according to claim 1 , characterized in that the outer shroud of the intermediate housing claim 1 , a torsion box of the front frame or the deviation edge provided with radial ribs are formed in a single piece.3. The assembly according to claim 1 , characterized in that the entire front frame is integrated into the outer shroud of the intermediate housing claim 1 , with or without being in a single piece.4. The assembly according to claim 1 , characterized in that the deviation edge and said support-forming element for the front frame and the outer shroud of the intermediate housing form a single structural element.5. The assembly according to claim 1 , characterized in that it also comprises a turbojet engine housed in the nacelle claim 1 , the turbojet engine comprising a fan surrounded by a housing ...

FASTENER DEVICE FOR FASTENING A FREE TURBINE STATOR WITH DUAL CENTERING

The invention relates to the field of free turbines mounted on a gas turbine engine. It provides a fastener device for fastening a free turbine stator on a gas generator casing that shares a common axis with the turbine stator, the fastener device comprising a flange carrying a plurality of assembly parts providing a first releasable connection between the turbine stator and the gas generator casing, the flange providing first centering of the turbine stator on the casing. The fastener device further comprises a second releasable connection between the turbine stator and the gas generator casing that is axially offset from the flange towards the gas generator and that provides second centering of the turbine stator on the casing.

Fastener device for fastening a free turbine stator with dual centering

The invention relates to the field of free turbines mounted on a gas turbine engine. It provides a fastener device for fastening a free turbine stator on a gas generator casing that shares a common axis with the turbine stator, the fastener device comprising a flange carrying a plurality of assembly parts providing a first releasable connection between the turbine stator and the gas generator casing, the flange providing first centering of the turbine stator on the casing. The fastener device further comprises a second releasable connection between the turbine stator and the gas generator casing that is axially offset from the flange towards the gas generator and that provides second centering of the turbine stator on the casing.

SYSTEM OF COUNTER-ROTATING PROPELLERS WITH A FEATHERING DEVICE FOR PROPELLER BLADES

A system of counter-rotating propellers for an aircraft turbine engine including a first and a second propeller, each including a stalling control system for the blades, a rotating actuating mechanism for sliding an element to move the angle of attack of the blades, and a disengaging mechanism for rigidly fixing in rotation the rotating actuating mechanism. The system is designed so that when the disengaging mechanism is engaged, a relative rotation speed is created between the elements and the associated rotating actuating mechanism thereof, bringing the blades into a neutral position thereof for feathering.

Turboprop having a propeller made up of variable-pitch blades

A turboprop having a set of variable-pitch rotary blades constrained to rotate with a rotary support. In order to vary its pitch, each blade of said set is coupled to a specific hydraulic actuator carried by the rotary support.

ISOSTATIC SUSPENSION OF A TURBOJET BY REAR DOUBLE SUPPORT

The invention relates to a bypass turbojet comprising an exhaust housing having a central hub () and connecting means () that can transmit the forces generated by the turbojet to the structure of the aircraft that it propels, said connection means being two arms extending radially from the central hub in order to cross the cold flow of said turbojet and being characterised in that they are secured to said central hub and positioned in a diametrically opposed manner in relation to each other. An additional connection means () extends between the hub () and the area () for securing the exhaust housing to the structure () of the aircraft in order to transmit the exceptional dimensioning loads, said connection means being on standby during normal use, without any transmission of force between said hub and said area. 18. Exhaust casing of a bypass turbojet engine for an aircraft , which casing is equipped with a support means which is intended to be attached to the structure of the aircraft , said exhaust casing , which is cylindrical , comprising a central hub supported by said support means by connection meanscharacterised in that said connection means are arms which are rigidly connected to said central hub and extend therefrom, passing through a secondary air flow of the bypass turbojet engine, said arms being designed to transmit to said support means the stresses generated in the region of said central hub by the turbojet engine in normal use without transmitting them to a cold-flow channel, in which said secondary air flow of the turbojet engine is guided.2. Equipped exhaust casing according to claim 1 , wherein the connection arms are radial arms claim 1 , of which there are two claim 1 , which are positioned diametrically opposite one another.3. Equipped exhaust casing according to claim 1 , wherein the outer end of each arm is designed to be attached to the support means by a connection of the sliding pivot type or annular linear type.4. Equipped exhaust casing ...

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.

Turboprop including a set of adjustable-pitch blades

A turboprop including a rotary casing fitted with adjustable-pitch blades enabling thrust to be managed. Each blade is coupled, for the purpose of adjusting its pitch, to a control member of an annular actuator carried by the rotary casing.

DEVICE FOR LUBRICATING AN EPICYCLOIDAL REDUCTION GEAR

A reduction gear includes a sun pinion and planet pinions driven by the sun pinion and rolling on a fixed ring gear. The device includes an oil tank, an oil supply duct and oil routing ducts. The device also includes an oil ejection device at the end of the fixed supply duct, the orientation of which includes a radial component directed away from a common axis of rotation, and a cylindrical device for recovering the oil that can move in rotation about the common axis of rotation. The oil ejection device is linked by at least one duct to a lubrication device for the gear formed by the cooperation of the teeth of at least one planet pinion with an adjacent pinion. This device feeds the ducts which supply the oil to the parts to be lubricated, by virtue of the action of the centrifugal field. 1. A reduction gear with epicycloidal gear train equipped with an oil feed device , said reduction gear comprising a sun pinion that can move in rotation about a common axis of rotation , planet pinions borne by a planet carrier , the planet pinions being driven by said sun pinion and being able to move in rotation about planet axes , said planet pinions rolling on a fixed ring gear , said device comprising an oil tank , at least one fixed oil supply duct and oil routing ducts , said routing ducts also being able to move in rotation about the common axis of rotation , said device also comprising an oil ejection device at an end of the fixed supply duct , the orientation of which includes a radial component directed away from the common axis of rotation , and a cylindrical recovery device for recovering the oil that can move in rotation about said common axis of rotation and positioned facing said ejection device ,wherein said oil ejection device is linked by at least one duct to a lubrication device for a gear formed by the cooperation of the teeth of at least one planet pinion with an adjacent pinion.2. The reduction gear with epicycloidal gear train according to claim 1 , ...

Aircraft comprising two contra-rotating fans to the rear of the fuselage, with spacing of the blades of the downstream fan

The invention relates to an aircraft comprising a fuselage (1), which is propelled by a turbine engine with two coaxial fans, namely an upstream fan (7) and a downstream fan (8), driven by two contra-rotating rotors (5, 6) of a power turbine (3). The two fans (7, 8) and the turbine (3) are integrated into a nacelle (14) which projects downstream from the fuselage (1) and through which air flows. According to the invention, at least one of the fans (7, 8) of the aircraft and, in particular, the downstream fan (8) comprises variable-spacing blades, and at least one stator-forming variable-spacing blade ring (25) in the aircraft is placed upstream of the upstream fan (7). The variable-spacing stator blades (25) and the variable-spacing blades of the downstream fan (8) are mutually configured to direct the air flow in a first mode in which the air flows through the nacelle (14) from upstream to downstream and in a second mode in which the air is pushed back upstream through the nacelle (14) ...

Turbine engine comprising a contrarotating propeller receiver supported by a structural casing attached to the intermediate housing

An open rotor type aircraft turbine engine including a contrarotating propeller receiver and a dual-body gas generator having a low-pressure compressor and a high-pressure compressor separated by an intermediate housing, in which the gas generator is arranged upstream from the receiver is provided. The turbine engine includes a structural casing for supporting the receiver, surrounding the gas generator and having a downstream end attached to the receiver and an upstream end attached to the intermediate housing; and a connection device between the structural supporting casing and the gas generator, arranged between the upstream and downstream ends of the casing.

AIRCRAFT PROPULSION ASSEMBLY

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.

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.

Bypass engine with contrarotating turbine wheels including a reversing module

A bypass aeronautical engine including a fan, an LP compressor, an HP compressor, a combustion chamber, an HP turbine, and at least one LP turbine stage is disclosed. The LP turbine stage includes a first movable bladed wheel carried by a first turbine shaft and a second movable bladed wheel turning in the opposite direction to the first wheel. The fan is driven by the second wheel via a second turbine shaft and by the first shaft via a module for reversing its direction of rotation. The reversing module includes two bevel pinions carried respectively by the first and second LP turbine shafts, and a reversing pinion.

Thrust reverser device for compact jet pipe

A bypass turbojet engine nacelle that forms a fan casing includes a first, upstream, streamlining element and a second streamlining element that forms a jet pipe. The second element can move translationally between a position ensuring aerodynamic continuity of the nacelle and a downstream position uncovering flow reversal openings. A thrust reverser device is housed in the nacelle and includes flow reverser flaps and cascades of vanes providing radial guidance for the flow. The cascades of vanes providing radial guidance for the flow can move in translation along the axis of the nacelle between a retracted position into the first steamlining element and an active flow-guidance position, the second streamlining element being secured to the cascades of vanes, the reverser flaps being mounted to rotate about axes that are transverse with respect to the axis of the nacelle and secured to the cascades of vanes.

Turboprop with a variable-pitch propeller

A turboprop having at least one propeller formed by a set of variable pitch blades. Each blade is swivel-mounted on a rotary support and carries a gearwheel meshing with an actuator annulus rotating on the rotary support and coupled to a control annulus via an epicyclic mechanism.

DEVICE FOR SHIFTING A PROPELLER INTO REVERSE, COMPRISING AN ACTUATOR ACTING ON A CRANK PIN

A device controlling shifting of a propeller turbine engine into reverse mode, by acting on a shaft for controlling pitch of propellers. The device includes: at least one centrifugal weight arranged to drive the propellers into a flag position thereof under action of the centrifugal force; and an actuator that can rotate the control shaft to shift the pitch of the propellers from a traction mode to a reverse mode, passing through a zero pitch position. The centrifugal weight is in an unstable equilibrium position in relation to action of the centrifugal force when the control shaft shifts the pitch of the propellers through the zero pitch position. Further, an actuation mechanism exerts a torque on the control shaft when the centrifugal weight is in the unstable equilibrium position, to prevent it from staying in this position. 114-. (canceled)15. A device for controlling a shift into reverse of a propeller-type turbomachine , through action on a pitch control spindle that controls a pitch of propellers , the device comprising:at least one bob weight mounted on and so as to project in cantilevered manner beyond the control spindle and configured to drive the propellers toward their feathered position under action of centrifugal force generated by rotation of the turbomachine;an actuator configured to cause the control spindle to turn to shift the pitch of the propellers from a traction mode to a reverse mode, passing via a zero-pitch position; andan actuating means that applies a torque to the control spindle when the control spindle turns to shift the pitch of the blades via a zero-pitch position, so as to prevent the control spindle from remaining in that position.16. The device as claimed in claim 15 , wherein the bob weight is in a position of unstable equilibrium with respect to the action of the centrifugal force when the control spindle causes the pitch of the propellers to pass via the zero-pitch position.17. The device as claimed in claim 15 , wherein the ...

TURBINE ENGINE COMPRISING A CONTRAROTATING PROPELLER RECEIVER SUPPORTED BY A STRUCTURAL CASING ATTACHED TO THE INTERMEDIATE HOUSING

The present invention relates to an open rotor type aircraft turbine engine ( 1 ), comprising a contrarotating propeller receiver ( 30 ) and a dual-body gas generator ( 14 ) comprising a low-pressure compressor ( 16 ) and a high-pressure compressor ( 18 ) separated by an intermediate housing ( 27 ), said gas generator being arranged upstream from said receiver. According to the invention, the turbine engine further comprises a structural casing ( 50 ) for supporting the receiver ( 30 ), surrounding the gas generator ( 14 ) and having a downstream end ( 50 a ) attached to said receiver and an upstream end ( 50 b ) attached to said intermediate housing ( 27 ). Furthermore, it comprises additional connection means ( 60 ) between said structural supporting casing and the gas generator, arranged between the upstream and downstream ends ( 50 b , 50 a ) of the casing.

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.

SEALING DEVICE HAVING A SLEEVE FOR THE PASSAGE OF A CONNECTING ROD OF A SYSTEM FOR CONTROLLING THE ORIENTATION OF THE BLOWER BLADES OF A TURBOPROP ENGINE THROUGH A PARTITION

A sealing device for passing a connecting rod of a system for controlling a pitch of fan blades of a turboprop through a partition. The device includes a tube for fastening to the partition that is to be sealed, and a frustoconical sheath through which the connecting rod is to pass, the sheath configured to slide axially inside the tube and including, at its wider end, a sealing mechanism co-operating with the tube, and, at its narrower end, a leaktight fastener fastening to a corresponding end of the connecting rod. 15-. (canceled)6. A sealing device for passing a connecting rod of a system for controlling pitch of fan blades of a turboprop through a partition , comprising:a tube for fastening to the partition that is to be sealed; anda frustoconical sheath through which the connecting rod is to pass,the sheath configured to slide axially inside the tube and including, at its wider end, sealing means co-operating with the tube, and, at its narrower end, leaktight fastener means for fastening to a corresponding end of the connecting rod.7. A device according to claim 6 , wherein the wider end of the sheath further includes a gasket at its periphery co-operating with an inside of the tube to provide sealing between the sheath and the tube.8. A device according to claim 6 , wherein the narrower end of the sheath is closed and pivotally mounted about a pivot pin of the corresponding end of the connecting rod to fasten the sheath to the connecting rod in a sealed manner.9. A system for controlling pitch of fan blades of a turboprop comprising:at least one set of adjustable-pitch fan blades, the set being constrained to rotate with a rotary ring mechanically connected to a rotary casing, each blade of the set being coupled for adjusting its pitch to a blade root support pivotally mounted on the rotary ring by a bevel gearing including a first toothed wheel secured to the blade root support and centered on an axis that is radial relative to the rotary ring, and a second ...

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.

Reduction gear with epicyclic gear train having roller-bearing-mounted planet spindles

A reduction gear with epicyclic gear train including an annulus gear, and at least one planet gear rolling on the annulus gear and able to rotate about a planet spindle borne by a planet carrier is provided. The planet spindle is mounted such that it can itself rotate about its axis relative to the planet carrier. The reduction gear is suitable for mounting in a high bypass ratio jet engine for driving the fan thereof.

Suspension rods for the bypass flow duct of a turbojet with eccentric ball joints

A device for assembly of a connecting rod on the casing of a turbo-engine including: a clevis fixed to the casing and including at least two coaxially bored lugs; a shaft traversing the bores of the lugs to which the suspension member is fixed, in a manner which is mobile in radial rotation, via a ball joint surrounding the shaft; and a connecting device which holds the shaft in place in the lugs of the clevis and is capable of being driven in rotation about the axis of the bores, is disclosed. The ball joint and the connecting device are configured such that the rotation of the connecting device about the axis of the bore of the lugs causes an offset of the axis of rotation of the connecting rod in a direction perpendicular to the axis of the bores.

DEVICE FOR CONTROLLING THE PITCH OF FAN BLADES OF A TURBOPROP

The invention relates to a device for controlling the pitch of fan blades of a turboprop. The device includes at least at least one set of adjustable pitch fan blades secured to rotate with a rotary ring centered on a longitudinal axis and mechanically connected to a turbine rotor. Each blade of the set is coupled for pitch-adjustment purposes with a synchronization ring centered on the longitudinal axis, the synchronization ring being suitable for pivoting about the longitudinal axis relative to the rotary ring under drive from actuators carried by the rotary ring and each having a respective axis extending in a direction that is substantially tangential to the synchronization ring.

SIMPLIFIED SYSTEM FOR CONTROLLING PROPELLER BLADE PITCH IN AN AIRCRAFT TURBOSHAFT ENGINE

A system for controlling pitch of a propeller blade of a turboshank engine, including two automatic locking members making it possible, depending on their controlled position, to lock rotation of a blade root in both directions of rotation, or to allow the rotation of the blade root support in either of the two directions.

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.

Aircraft propulsion system and aircraft powered by such a propulsion system built into the rear of an aircraft fuselage

The invention relates to an aircraft propulsion system (100) intended for being built into the rear of an aircraft fuselage, the propulsion system comprising at least two gas generators (102a, 102b) supplying a power turbine (104) having two counter-rotating turbine rotors (104a, 104b) for driving two fans (112a, 12b), and separate air inlets (106a, 106b) for supplying each gas generator, characterised in that it comprises an electrical drive device (140) configured to rotate at least one of the turbine rotors, at least one electrical generator (142a, 142b) configured to transform part of the energy of the flow from the gas generators into electrical power and an electric motor (146) supplied by said electrical generator and capable of rotating at least one of the turbine rotors, said electrical generator being installed on one of said gas generators, and in that said turbine rotor is capable of being rotated simultaneously by a flow from said gas generators and by the electrical drive ...

System of counter-rotating propellers with a feathering device for propeller blades

A system of counter-rotating propellers for an aircraft turbine engine including a first and a second propeller, each including a stalling control system for the blades, a rotating actuating mechanism for sliding an element to move the angle of attack of the blades, and a disengaging mechanism for rigidly fixing in rotation the rotating actuating mechanism. The system is designed so that when the disengaging mechanism is engaged, a relative rotation speed is created between the elements and the associated rotating actuating mechanism thereof, bringing the blades into a neutral position thereof for feathering.

Simplified system for controlling propeller blade pitch in an aircraft turboshaft engine

A system for controlling pitch of a propeller blade of a turboshank engine, including two automatic locking members making it possible, depending on their controlled position, to lock rotation of a blade root in both directions of rotation, or to allow the rotation of the blade root support in either of the two directions.

Device for recovering lubricating oil from an epicyclic reduction gear

An epicyclic reduction gear, including a planetary gear movable in rotation about an axis of rotation, planet pinions driven by the planetary gear and movable in rotation about axes of planet gears carried by a planet carrier, the planet pinions rolling on a fixed ring gear and the planet carrier being axially positioned laterally relative to the ring gear, the gear formed by the planet pinions and the ring gear being formed to axially eject lubricating oil thereof after use. The planet carrier includes a radial extension positioned facing the gear and forming a mechanism for guiding the oil to a radial end thereof to be ejected from there by centrifugation.

SIMPLIFIED SYSTEM FOR CONTROLLING PROPELLER BLADE PITCH IN AN AIRCRAFT TURBOSHAFT ENGINE

A system for controlling propeller blade pitch in a turboshaft engine, including: a first track connected to a propeller blade, of which the rotation provides for the setting of the incidence of this blade; a second track; a member actuating the first track, arranged between the first and second tracks, and having a recessed angular portion; and at least one locking member provided between the first and second tracks, housed in the recessed angular portion and in the notch. The locking member can occupy a normal over-center position rendering the first and second tracks integral in rotation, and a release position authorizing the displacement in rotation of a unit including the first track, the locking member, and the actuating member.

High-pressure turbine blades made of ceramic matrix composites

A turbine blade for a turbojet engine, made of a ceramic matrix composite material and including a vane that extends above a platform and a root that extends below the platform is provided. The pressure face and the suction face of the vane is formed by sheets of a composite material, the sheets meeting at the leading edge and trailing edge of the vane. The pressure face and suction face are formed by the same sheet bent back on itself, in a radial direction, at the leading edge or trailing edge.

A DEVICE FOR FEEDING FLUID TO A HYDRAULIC ACTUATOR FOR CONTROLLING THE PITCH OF THE FAN BLADES OF A TWO-PROPELLER TURBOPROP

A device for feeding fluid to a hydraulic actuator for controlling a pitch of fan blades of a two-propeller turboprop, the device including: a fluid manifold secured to a rotor of the turboprop and including a cylindrical portion including at least two fluid-circulation grooves, each presenting an outlet orifice; a fluid-admission support secured to a stationary portion of the turboprop and including a cylindrical portion including at least two distinct fluid passages opening to fluid-admission tubes and each leading radially into one of the fluid-circulation grooves of the manifold; and a tub constrained to rotate with the fluid manifold and including a cylindrical portion including at least two fluid-flow channels, each fed with fluid by a respective one of the outlet orifices of the fluid dispenser, each fluid-flow channel leading to a respective chamber of a control actuator. 110-. (canceled)11. A device for feeding fluid to a hydraulic actuator for controlling a pitch of fan blades of a two-propeller turboprop , the device comprising:a fluid manifold constrained to rotate with a rotor of the turboprop and including a cylindrical portion provided on an outside surface including at least two annular fluid-circulation grooves that are longitudinally spaced apart, each fluid-circulation groove presenting at least one outlet orifice opening out radially to an inside of the cylindrical portion of the fluid manifold;a fluid-admission support secured to a stationary portion of the turboprop and including a cylindrical portion arranged around the cylindrical portion of the fluid manifold, being coaxial therewith and including at least two distinct fluid passages opening out to respective fluid-admission tubes and each leading radially to an inside of the cylindrical portion of the support in a respective one of the fluid-circulation grooves of the manifold; anda tub constrained to rotate with the fluid manifold and including a central portion arranged inside the ...

Device for feeding fluid to a hydraulic actuator for controlling the pitch of the fan blades of a two-propeller turboprop

A device for feeding fluid to a hydraulic actuator for controlling a pitch of fan blades of a two-propeller turboprop, the device including: a fluid manifold secured to a rotor of the turboprop and including a cylindrical portion including at least two fluid-circulation grooves, each presenting an outlet orifice; a fluid-admission support secured to a stationary portion of the turboprop and including a cylindrical portion including at least two distinct fluid passages opening to fluid-admission tubes and each leading radially into one of the fluid-circulation grooves of the manifold; and a tub constrained to rotate with the fluid manifold and including a cylindrical portion including at least two fluid-flow channels, each fed with fluid by a respective one of the outlet orifices of the fluid dispenser, each fluid-flow channel leading to a respective chamber of a control actuator.

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.

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. 110-. (canceled)11. A device for controlling pitch of fan blades of a turboprop including at least one set of adjustable-pitch fan blades , the set being secured to rotate with a rotary ring centered on a 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 , the device comprising:an actuator centered on the longitudinal axis, secured to rotate with the turbine rotor and mechanically connected to the synchronization ring by a plurality of connection arms each comprising an axial link connected to the actuator rod, a radial link connected to the synchronization ring, and at least one bellcrank connecting the axial link to the radial link such that actuating the actuator causes the synchronization ring to move in turning about the longitudinal axis.12. A device according to claim 11 , wherein each connection arm further includes another bellcrank secured to the rotary ring and connected firstly to the radial link and secondly to a tangential link fastened to the synchronization ring such that movement of the radial link in a direction that is substantially radial causes the synchronization ring to move in turning about the longitudinal axis.13. A device ...

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 () of trunconical shape designed to allow passage of the connecting rod () and having, at its wider end, means () of attachment to the partition () to be sealed and, at its narrower end, an O-ring through which the connecting rod is free to slide. 12424262828222236384042404648303012323250505454626458a,ba,ba,ba,ba,ba,ba,b. A system for controlling the orientation of the fan blades of a turboprop comprising at least one set () of fan blades () with adjustable orientation , said set being integral in rotation with a rotating ring () connected mechanically with a rotating housing () , each blade of the set being coupled , for control of its orientation , to a blade root support () pivotably mounted on the rotating ring by means of a bevel gearset () made up of a first bevel gear () integral with the blade root support and centered on an axis () radial to the rotating ring and a second bevel gear () integral with the rotating ring , centered on an axis () tangential to said rotating ring , and bearing a counterweight () eccentric with respect to its axis of rotation , the system also comprising a cylinder () centered on the axis of rotation () of the rotating ring , rotating integrally with the rotating housing , and the rod () whereof is connected to each counterweight through radial connecting rods () and bellcranks () , the system also comprising , for each radial connecting rod , a bellows of trunconical shape through which passes the radial connecting rod and having , at its wider end , means ( , ) of attachment to a partition () to be sealed and , at its narrower end , an O-ring through which the radial connecting rod is free to slide.26258. A system according to claim 1 , wherein the wider end of the bellows includes an attachment clip () attached to the partition () to be sealed.3. A system ...

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.

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.

Sealing device having a sleeve for the passage of a connecting rod of a system for controlling the orientation of the blower blades of a turboprop engine through a partition

A sealing device for passing a connecting rod of a system for controlling a pitch of fan blades of a turboprop through a partition. The device includes a tube for fastening to the partition that is to be sealed, and a frustoconical sheath through which the connecting rod is to pass, the sheath configured to slide axially inside the tube and including, at its wider end, a sealing mechanism co-operating with the tube, and, at its narrower end, a leaktight fastener fastening to a corresponding end of the connecting rod.

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.

Device for lubricating an epicycloidal reduction gear

A reduction gear includes a sun pinion and planet pinions driven by the sun pinion and rolling on a fixed ring gear. The device includes an oil tank, an oil supply duct and oil routing ducts. The device also includes an oil ejection device at the end of the fixed supply duct, the orientation of which includes a radial component directed away from a common axis of rotation, and a cylindrical device for recovering the oil that can move in rotation about the common axis of rotation. The oil ejection device is linked by at least one duct to a lubrication device for the gear formed by the cooperation of the teeth of at least one planet pinion with an adjacent pinion. This device feeds the ducts which supply the oil to the parts to be lubricated, by virtue of the action of the centrifugal field.

Feathering device for the fan blades of a turboprop engine

A feathering device for the fan blades of a turboprop engine that includes at least one set of fan blades with adjustable orientation is provided. The assembly is attached in rotation to a rotating cowling connected to a turbine rotor. Each blade is coupled, for the adjustment of its orientation, to a control ring that is movable between two extreme positions, one of which corresponds to feathering of the blades. Mechanical parts are able to extend elastically as a result of a rise in their temperature, these mechanical parts being positioned facing the control ring so as to be able to exert a thrust force on the ring in order to put it in a position to feather the blades when they expand. A device to cause a rise in the temperature of the mechanical parts so as to expand them is also provided.

Mechanical transmission device for driving in rotation counter-rotating propellers of a dual-propeller turboprop

A mechanical transmission device to driving in rotation counter-rotating propellers of a dual-propeller turboprop, including: an epicyclic gear train having a sun gear carried on a sun gear shaft centered on a longitudinal axis and which is connected upstream to a turbine rotor of the turboprop driven in rotation; at least one planet gear meshing with the sun gear; a planet gear carrier carrying the planet gear free to rotate and which is carried by a planet carrier shaft connected downstream to a first set of propellers to drive it in rotation; and a ring gear meshing with the planet gear and which is carried on a ring gear shaft connected downstream to a second set of propellers to drive it in rotation, is disclosed.

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.

COUNTERWEIGHT-BASED DEVICE FOR CONTROLLING THE ORIENTATION OF FAN BLADES OF A TURBOPROP ENGINE

A device for controlling orientation of fan blades of a turboprop including at least one set of fan blades having adjustable orientation attached in rotation to a rotating ring mechanically connected to a turbine rotor. Each blade of the set is coupled to a blade root support pivotably mounted on the rotating ring by a conical gear train including a first gear wheel attached to the blade root support and a second gear wheel attached to the rotating ring and bearing a counterweight that is eccentric with respect to its axis of rotation. A cylinder attached in rotation to the turbine rotor and a rod of which is connected to each counterweight through a connecting arm makes it possible to impart synchronous angular displacement to all the counterweights about the axis of rotation of their respective gear wheel. 18-. (canceled)9. A control device for orientation of fan blades of a turboprop , comprising:at least one set of fan blades having adjustable orientation, the set being attached in rotation to a rotating ring mechanically linked to a rotor of a turbine, each blade of the set being coupled, for control of its orientation, to a blade root support mounted pivotably on the rotating ring by a conical gear train including a first gear wheel attached to the blade root support and centered on an axis radial to the rotating ring and of a second gear wheel attached to the rotating ring, centered on an axis tangential to the rotating ring, and bearing a counterweight that is eccentric with respect to its axis of rotation; anda cylinder centered on the axis of rotation of the rotating ring, attached in rotation to the turbine rotor and a rod of which is connected to each counterweight through connecting arms so as to impart synchronous angular motion to the set of counterweights about the axis of rotation of their respective gear wheel, each connecting arm including a radial link having one end connected to the corresponding counterweight and the other end connected to an ...

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.

Isostatic suspension of a turbojet by rear double support

The invention relates to a bypass turbojet comprising an exhaust housing having a central hub (13) and connecting means (11) that can transmit the forces generated by the turbojet to the structure of the aircraft that it propels, said connection means being two arms extending radially from the central hub in order to cross the cold flow of said turbojet and being characterized in that they are secured to said central hub and positioned in a diametrically opposed manner in relation to each other. An additional connection means (14) extends between the hub (13) and the area (9) for securing the exhaust housing to the structure (12) of the aircraft in order to transmit the exceptional dimensioning loads, said connection means being on standby during normal use, without any transmission of force between said hub and said area.

Pylon for mounting an engine on the structure of an aircraft

A system for pylon attachment for mounting an engine on a structure of an aircraft, or to wings of the aircraft, is provided. The system includes a first attachment mechanism that can be secured to the pylon and a second attachment mechanism that can be secured to the structure of the aircraft. A connection mechanism connects the first and second attachment mechanism. The connection mechanism allows movement of the first attachment mechanism in relation to the second attachment mechanism between first and second positions.

THRUST REVERSER DEVICE FOR COMPACT JET PIPE

A bypass turbojet engine nacelle that forms a fan casing includes a first, upstream, streamlining element and a second streamlining element that forms a jet pipe. The second element can move translationally between a position ensuring aerodynamic continuity of the nacelle and a downstream position uncovering flow reversal openings. A thrust reverser device is housed in the nacelle and includes flow reverser flaps and cascades of vanes providing radial guidance for the flow. The cascades of vanes providing radial guidance for the flow can move in translation along the axis of the nacelle between a retracted position into the first steamlining element and an active flow-guidance position, the second streamlining element being secured to the cascades of vanes, the reverser flaps being mounted to rotate about axes that are transverse with respect to the axis of the nacelle and secured to the cascades of vanes. 19-. (canceled)10. A nacelle for a bypass turbojet engine , forming an envelope of a fan , comprising:a first streamlining element, upstream, and a second streamlining element forming a pipe, the second element being movable in translation between a position in which it ensures aerodynamic continuity of the nacelle and a downstream position uncovering flow reversal openings;a thrust reverser device accommodated in the nacelle and comprising bypass flow reverser flaps and cascades for radial guidance of flow,wherein the cascades for radial guidance of flow are movable in translation along a length of the axis of the nacelle between a position in which they are retracted into the first streamlining element and an active flow guidance position, the second streamlining element being integral with the cascades, andreverser flaps fitted to be movable in rotation around axes that are transverse relative to the axis of the nacelle and integral with the cascades.11. A nacelle according to claim 10 , wherein the first streamlining element comprises rails for guiding the ...

Aircraft comprising a turbine engine incorporated into the rear fuselage with variable supply

The invention concerns an aircraft propelled by a turbine engine having contrarotating fans (7, 8), the turbine engine being incorporated at the rear of a fuselage (1) of the aircraft, in the extension of same and comprising at least two gas generators (2a, 2b) that supply, via a shared central stream (4), a power turbine (3), the turbine (3) comprising two contrarotating rotors (5, 6) for driving two fans (7,8) disposed downstream from the gas generators (2a, 2b), said aircraft comprising means (15) arranged for separating the gas flow in the power turbine (3) into at least two concentric streams (16, 17) and a device comprising first means for distributing the gas flow (21-24) between said streams (16, 17) from the central stream (4), the first distribution means being configured to be able to open or close the supply of at least one so-called sealable stream (16) of the streams (16, 17) of the power turbine (3).

Device for controlling the pitch of turboprop fan blades

The invention provides a device for controlling the pitch of the fan blades of a turboprop, the device comprising: at least one set of adjustable pitch fan blades, the set being constrained to rotate with a rotary ring mechanically linked to a rotor; a synchronizing ring coupled to each blade of the set in order to adjust its pitch; an actuator centered on the longitudinal axis of the turboprop and constrained to rotate with the rotor; and control links, each connected firstly to the actuator rod and secondly to an inside end of a cylindrical shaft via a crank capable of imparting turning movement to the shaft about its axis of revolution, an outside end of the shaft being coupled to a blade in order to adjust its pitch.

Counterweight-based device for controlling the orientation of fan blades of a turboprop engine

A device for controlling orientation of fan blades of a turboprop including at least one set of fan blades having adjustable orientation attached in rotation to a rotating ring mechanically connected to a turbine rotor. Each blade of the set is coupled to a blade root support pivotably mounted on the rotating ring by a conical gear train including a first gear wheel attached to the blade root support and a second gear wheel attached to the rotating ring and bearing a counterweight that is eccentric with respect to its axis of rotation. A cylinder attached in rotation to the turbine rotor and a rod of which is connected to each counterweight through a connecting arm makes it possible to impart synchronous angular displacement to all the counterweights about the axis of rotation of their respective gear wheel.

Suspension structure with variable geometry of a turboprop engine on a structural element of an aircraft

A variable geometry suspension structure for suspending a turboprop from a structural element of an aircraft, the structure including a rear cradle for fastening to a structural element of an aircraft and a front cradle for supporting a front portion of the turboprop, the front cradle being connected to the rear cradle, firstly via a pivot connection configured to enable the front cradle to tilt vertically relative to the rear cradle, and secondly by a return spring configured to prevent the front cradle from tilting while thrust from the turboprop is below a predetermined threshold.

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. 1) Method for manufacturing a rotor blade of a gas turbine engine comprising a body made of composite material and a connecting yoke designed to be attached to a fastener of a rotor disc of the said turbine engine , the said method comprising the following steps:a step of installing fibres around a metal tube and a step of injecting thermosetting resin in order to form a casing of composite material around the metal tube, the tube comprising at least two sections having a high density of fibres and at least one section having a low density of fibres arranged between the two sections having a high density of fibres; anda step of machining the section having a low density of fibres so as to form a connecting yoke for the blade comprising two sections having a high density of fibres, forming a reinforcement of the connecting yoke, encased in composite material.2) Method according to claim 1 , in which claim 1 , the body of the blade made of composite material consisting of a fibre-reinforced thermosetting resin claim 1 , the method comprises a step of placing the fibres of the blade body around the metal tube in order to form the casing made of composite material around the metal tube.3) Method according to claim 1 , comprising a step of weaving fibres around the metal tube claim 1 , the weave comprising warp threads placed along the cord of the said blade and weft threads placed along the height of the blade. The field of the invention is that of gas turbine engines for aircraft. The invention relates more particularly to a device for fastening fan blades made of composite ...

DATA COMMUNICATION CABLE

The subject of the invention is a data communications cable, characterized in that it comprises: 1. Data communications cable , comprising:a plurality of groups of four pairs of isolated conductors, the four pairs of isolated conductors being assembled in a helical fashion following a group assembly pitch, each pair being twisted in a helical fashion and surrounded by an electrical shield, the plurality of groups being assembled in a helical fashion following a final assembly pitch,an external sheath surrounding the plurality of groups, whereinthe final assembly pitch is variable along the cable.2. Cable according to claim 1 , wherein the cable does not comprise any other sheath apart from the external sheath.3. Cable according to claim 1 , wherein the group assembly pitch is variable along the cable.4. Cable according to claim 3 , wherein the final assembly pitch and/or the group assembly pitch varies between two limiting values of the same sign.5. Cable according to claim 3 , wherein the final assembly pitch and/or the group assembly pitch varies according to a periodic function.6. Cable according to claim 3 , wherein the final assembly pitch and/or the group assembly pitch in a random fashion.7. Cable according to claim 1 , wherein said cable comprises three claim 1 , four or six groups.8. Cable according to claim 1 , wherein each group comprises one electrical shield per pair of isolated conductors.9. Cable according to claim 1 , wherein each group comprises a single electrical shield in the form of a cross.10. Cable according to claim 9 , wherein the cross separates the pairs of conductors from one another and surrounds each pair of conductors. The present invention relates to data communications cables comprising a plurality of groups of four pairs of individually isolated conductors allowing the transmission of data at a high rate.An electrical cable generally comprises one or more sets of twisted conducting wires. A set is conventionally made up of two ...

SUSPENSION RODS FOR THE BYPASS FLOW DUCT OF A TURBOJET WITH ECCENTRIC BALL JOINTS

Device for assembly of a connecting rod () on the casing of a turbo-engine comprising, in addition to said suspension member, a clevis () fixed to the casing and comprising at least two coaxially bored lugs, and a shaft () traversing the bores of said lugs to which said suspension member is fixed, in a manner which is mobile in radial rotation, via a ball joint () surrounding the shaft, said shaft being held in place in the lugs of said clevis by connecting means () capable of being driven in rotation about the axis of said bores, characterized in that said ball joint and said connecting means are configured such that the rotation of said connecting means about the axis of the bore of the lugs causes an offset of the axis of rotation of the connecting rod () in a direction perpendicular to said axis of the bores. 1. A device for assembly of a suspension member on the casing of a turbo-engine comprising , in addition to said suspension member , a clevis fixed to the casing and comprising at least two coaxially bored lugs , and a shaft traversing the bores of said lugs to which said suspension member is fixed , in a manner which is mobile in radial rotation , via a fixing means surrounding the shaft , said shaft being held in place in the lugs of said clevis via connecting means capable of being driven in rotation about the axis of said bores , characterized in that said fixing means is a ball joint fixed at one of the ends of said suspension member , and bored along an axis which is offset relative to the axis of symmetry of its spherical part , the axis of rotation of said connecting means being merged with the axis of said lugs such that the rotation of said connecting means about the axis of the bore of the lugs causes an offset of the axis of rotation of the suspension member in a direction perpendicular to said axis of the bores.2. The device as claimed in claim 1 , in which the ball joint comprises at least one cutout on a radial face facing said connecting ...

TURBOPROP PROVIDED WITH A BLADE-POSITIONING DEVICE

A turboprop provided with a blade-positioning device including a stationary nacelle, a rotary nacelle including a plurality of blade roots, a turbine, the stationary and rotary nacelles and the turbine being coaxial along a longitudinal axis, a blade positioning device including for each blade a device configured to transform movement suitable for transforming a translation movement into a rotation movement, each one of the device for transforming movement being secured to the rotary nacelle and being suitable for pivoting a blade. The positioning device is placed between the inner surface of the stationary nacelle and the outer surface of the turbine, the positioning device including a member including a body secured to the stationary nacelle and a rod for sliding along an axis substantially parallel to the longitudinal axis. 1. A turboprop provided with at least one blade positioning device , comprising:a stationary nacelle,at least one rotary nacelle comprising a plurality of blade roots,a turbine, said stationary and rotary nacelles and said turbine being coaxial along a longitudinal axis,said blade positioning device comprising for each blade a movement transformation device constructed and arranged to transform a translation movement into a rotation movement, each movement transformation device being secured to said rotary nacelle and being adapted to pivot a blade,wherein said positioning device is placed between an inner surface of said stationary nacelle and an outer surface of said turbine, said positioning device comprising a member including a body secured to said stationary nacelle and a rod configured to slide along an axis substantially parallel to said longitudinal axis.2. The turboprop according to claim 1 , wherein said positioning device comprises an interface located between said member and said movement transformation device claim 1 , said interface being constructed and arranged to:transmit a translation movement of said rod to said movement ...

DEVICE FOR CONTROLLING THE PITCH OF TURBOPROP FAN BLADES

The invention provides a device for controlling the pitch of the fan blades of a turboprop, the device comprising: at least one set of adjustable pitch fan blades, the set being constrained to rotate with a rotary ring mechanically linked to a rotor; a synchronizing ring coupled to each blade of the set in order to adjust its pitch; an actuator centered on the longitudinal axis of the turboprop and constrained to rotate with the rotor; and control links, each connected firstly to the actuator rod and secondly to an inside end of a cylindrical shaft via a crank capable of imparting turning movement to the shaft about its axis of revolution, an outside end of the shaft being coupled to a blade in order to adjust its pitch. 1. A device for controlling the pitch of the fan blades of a turboprop , the device comprising:at least one set of adjustable pitch fan blades, said set being constrained to rotate with a rotary ring centered on a longitudinal axis of the turboprop and mechanically linked to a rotor;a synchronizing ring centered on the longitudinal axis of the turboprop and coupled to each blade of the set in order to adjust its pitch; andan actuator centered on the longitudinal axis of the turboprop and constrained to rotate with the rotor;wherein the control device further comprises control links, each connected firstly to the actuator rod and secondly to an inside end of a cylindrical shaft via a crank capable of imparting turning movement to the shaft about its axis of revolution, an outside end of the shaft being coupled to a blade in order to adjust its pitch.2. A device according to claim 1 , wherein each blade is associated with a counterweight pivotally mounted on the synchronizing ring and connected by a system of counterweight links to a rotary casing so as to be capable of imparting a turning movement to the synchronizing ring about the longitudinal axis of the turboprop.3. A device according to claim 2 , wherein an angular position of the counterweight ...

MECHANICAL TRANSMISSION DEVICE FOR DRIVING IN ROTATION COUNTER-ROTATING PROPELLERS OF A DUAL-PROPELLER TURBOPROP

A mechanical transmission device to driving in rotation counter-rotating propellers of a dual-propeller turboprop, including: an epicyclic gear train having a sun gear carried on a sun gear shaft centered on a longitudinal axis and which is connected upstream to a turbine rotor of the turboprop driven in rotation; at least one planet gear meshing with the sun gear; a planet gear carrier carrying the planet gear free to rotate and which is carried by a planet carrier shaft connected downstream to a first set of propellers to drive it in rotation; and a ring gear meshing with the planet gear and which is carried on a ring gear shaft connected downstream to a second set of propellers to drive it in rotation, is disclosed. 1. A mechanical transmission device for driving in rotation counter-rotating propellers of a dual-propeller turboprop , including an epicyclic gear train comprising:a sun gear carried by a sun gear shaft which is centered on the longitudinal axis of the turboprop and which is designed to be connected upstream to a rotor of a turbine of the turboprop to be driven in rotation;at least one planet gear meshing with the sun gear;a planet carrier carrying, free to rotate, the planet gear and which is carried by a planet carrier shaft designed to be connected downstream to a first set of propellers to drive the first set of propellers in rotation; anda ring gear meshing with the satellite and which is carried on a ring gear shaft designed to be connected downstream to a second set of propellers to drive the second set of propellers in rotation;wherein the sun gear shaft includes an upstream end provided with an upstream web extending radially outward, and a downstream end opposite the upstream end and provided with a downstream web formed downstream of the epicyclic gear train and extending radially outward.2. The device according to claim 1 , wherein the ratio of the diameter of the upstream and downstream webs of the sun gear shaft and the diameter of the ...

AIRFLOW-STRAIGHTENING STRUCTURE FOR THE NACELLE OF AN AIRCRAFT ENGINE

An airflow-straightening structure for an aircraft engine is provided that includes a hoop inside which there are arranged a plurality of flow-straightening vanes bearing a hub of a fan. Also includes is a clevis for connecting to a suspension strut, the clevis being fixed to said hoop. The structure has at least two elements chosen from the group of the hoop, the plurality of vanes, the hub and the clevis, which are formed in one piece, that is to say without any assembly operation. Additionally, at least one of the elements chosen from the group is at least partially formed of a composite material. 2. The structure according to claim 1 , characterized in that all of said elements are made in a single piece and from a composite material.3. The structure according to claim 1 , characterized in that said hoop incorporates the case of said fan.4. The structure according to claim 1 , characterized in that said hoop incorporates an air intake shroud.5. The structure according to claim 1 , characterized in that said hoop incorporates a thrust reverser cascade edge.6. A nacelle for an aircraft engine claim 1 , characterized in that it comprises an airflow-straightening structure according to . This application is a continuation of International Application No. PCT/FR2011/051379 filed on Jun. 16, 2011, which claims the benefit of FR 10/54852, filed on Jun. 18, 2010. The disclosures of the above applications are incorporated herein by reference.The present disclosure relates to an airflow-straightening structure for an aircraft engine.The statements in this section merely provide background information related to the present disclosure and may not constitute prior art.As is known in itself, and shown in the appended , a nacelle having axis A for a dual-flow (turbojet) engine traditionally comprises an outer structure having an upstream portion forming an air intake, an intermediate portion whereof the inner skin forms a case for the fan of the engine, and a downstream ...

AIRCRAFT TURBOJET ENGINE FAN CASING

An aircraft turbojet engine fan casing in the form of a box section is provided by the present disclosure. The box section includes a radially interior wall of which is able to form an internal skin of a cold air flow duct of a nacelle in which said turbojet engine is intended to be mounted, and a radially exterior wall of which is able to form an external skin of said nacelle, the box forming a module forming an entire thickness of the nacelle, and placed between an upstream portion of the nacelle, forming the air intake, and a downstream casing portion, on which a cascade edge of a thrust reverser can be fixed. 1. An aircraft turbojet engine fan casing in the form of a box section , a radially interior wall of which is able to form an internal skin of a cold air flow duct of a nacelle in which said turbojet engine is intended to be mounted , and a radially exterior wall of which is able to form an external skin of said nacelle , the box forming a module forming an entire thickness of the nacelle , and placed between an upstream portion of the nacelle , forming the air intake , and a downstream casing portion , on which a cascade edge of a thrust reverser can be fixed.2. The fan casing according to claim 1 , characterized in that it comprises a ribbing placed between said inner and outer walls.3. The casing according to claim 1 , characterized in that at least one of said walls is formed from a composite material.4. The casing according to claim 1 , characterized in that it comprises an intermediate fan blade retaining layer between said inner and outer skins.5. The casing according to claim 4 , characterized in that said intermediate layer can be made from aramid fibers.6. An aircraft turbojet engine claim 1 , characterized in that it comprises a fan casing as set forth in .7. An aircraft propulsion assembly claim 6 , characterized in that it comprises a nacelle whereof the intermediate portion is formed by a turbojet engine fan casing according to .8. The ...

TURBOJET ENGINE NACELLE

A nacelle for a turbojet engine is provided that includes an air intake upstream from the turbojet engine, a middle section intended to surround a fan of the turbojet engine and its case, and a downstream section. The middle section is made from at least one aerostructure capable of ensuring external aerodynamic continuity of the nacelle, and the aerostructure is rigidly bound, so as to be able to be taken apart, to at least one surrounding fixed structure. 1. A nacelle for a turbojet engine , comprising:an air intake upstream from the turbojet engine;a middle section intended to surround a fan of the turbojet engine and its case; anda downstream section,the middle section being made from at least one aerostructure capable of ensuring external aerodynamic continuity of the nacelle, characterized in that said aerostructure is rigidly bound, so as to be able to be taken apart, to at least one surrounding fixed structure.2. The nacelle according to claim 1 , characterized in that the aerostructure comprises at least one hatch allowing access to the inside of the nacelle located in proximity to at least one of an upper twelve o'clock claim 1 , a lower so-six o'clock claim 1 , and a middle area.3. The nacelle according to claim 1 , characterized in that it comprises two aerostructures claim 1 , notably substantially hemicylindrical claim 1 , positioned on either side of a substantially longitudinal axis of the nacelle.4. The nacelle according to any of claim 1 , characterized in that the aerostructure is rigidly connected claim 1 , so as to be able to be taken apart claim 1 , to a pylon or an interface for connecting the nacelle to a pylon.5. The nacelle according to claim 1 , characterized in that the aerostructure is rigidly bound claim 1 , so as to be able to be taken apart claim 1 , to a lower longitudinal beam.6. The nacelle according to claim 1 , characterized in that the aerostructure is bound to another aerostructure claim 1 , notably in the lower portion.7. The ...

REDUCTION GEAR WITH EPICYCLIC GEAR TRAIN HAVING ROLLER-BEARING-MOUNTED PLANET SPINDLES

A reduction gear with epicyclic gear train comprising an annulus gear (), at least one planet gear () rolling on said annulus gear and able to rotate about a planet spindle () borne by a planet carrier (), wherein said planet spindle is mounted such that it can itself rotate about its axis relative to said planet carrier. The invention is suited to a reduction gear mounted in a high bypass ratio jet engine for driving the fan thereof. 1. A reduction gear with epicyclic gear train comprising an annulus gear , at least one planet gear rolling on said annulus gear and able to rotate about a planet spindle borne by a planet carrier , said planet spindle being mounted such that it can itself rotate about its axis relative to said planet carrier ,wherein there are two modes of operation: a first mode in which said planet spindle is rigidly attached to the planet carrier and a second mode in which said planet spindle can rotate freely relative to the planet carrier.2. The reduction gear as claimed in claim 1 , in which the planet gear rotates about its planet spindle by means of a journal bearing and the planet spindle is mounted on the planet carrier via the intermediary of a rolling bearing.3. The reduction gear as claimed in claim 1 , in which switching from one mode to the other is performed as a function of the temperature of the lubrication oil of said reduction gear.4. The reduction gear as claimed in claim 3 , in which switching from one mode to the other is actuated by an actuation means positioned so as to be in contact with said lubrication oil and comprising a shape memory material.5. The reduction gear as claimed in claim 4 , in which said actuation means is a flange plate in the shape of a circular annulus claim 4 , the central bore of which is attached to said spindle and the outer end of which moves in the axial direction as a function of the temperature of the lubrication oil.6. The reduction gear as claimed in claim 5 , in which said flange plate ...

HIGH-PRESSURE TURBINE BLADES MADE OF CERAMIC MATRIX COMPOSITES

Turbine blade for a turbojet engine, made of a ceramic matrix composite material and comprising a vane that extends above a platform and a root that extends below said platform, the pressure face and suction face of said vane being formed by sheets of a composite material, said sheets meeting at the leading edge and trailing edge of said vane, characterised in that the pressure face and suction face are formed by the same sheet bent back on itself, in a radial direction, at the leading edge or trailing edge. 1. Turbine blade for a turbojet engine , made of a ceramic matrix composite material and comprising a vane that extends above a platform and a root that extends below said platform , the pressure face and suction face of said vane being formed by sheets of a composite material , said sheets meeting at the leading edge and trailing edge of said vane ,characterised in that the pressure face and the suction face are formed by the same sheet bent back on itself, in a radial direction, at the leading edge or trailing edge.2. Blade according to claim 1 , wherein the two portions of the sheet are contiguous and fixed to one another over the entire length of the vane.3. Blade according to claim 1 , wherein the two portions of the sheet are separate claim 1 , forming a cavity for ventilation air to circulate.4. Blade according to claim 1 , wherein the two portions of the sheet are joined at the trailing edge claim 1 , respectively at the leading edge claim 1 , by soldering.5. Blade according to claim 1 , wherein the two portions of the sheet are joined at the trailing edge claim 1 , respectively at the leading edge claim 1 , by embedment in the same ceramic matrix.6. Blade according to claim 1 , wherein said sheet is bent back at the leading edge and joined to itself at the trailing edge.7. Blade according to claim 1 , wherein the platform and/or the root are formed by an extension of the sheet composing the vane claim 1 , the two portions of the sheet being contiguous ...

TURBOMACHINE WITH AXIAL FORCE ADJUSTMENT AT A BEARING

A turbomachine including a stator, a rotor mounted on a shaft, a first bearing and a second bearing downstream of the first bearing in a direction of air circulation at the inlet of the turbomachine, the first bearing forming an axial abutment linked to the stator, the second bearing including an inner ring secured to the shaft and an outer ring mounted on an arm secured to the stator, the second bearing including rolling elements in axial support on the inner ring and on the outer ring. The outer ring includes a radially extending ring portion. The turbomachine also includes an axial force application device mounted between the arm and the ring portion. 1. A turbomachine including a stator and a rotor mounted on a shaft , the rotor including vanes in a flow path , the rotation of the shaft and the rotor with respect to the stator being ensured by a set of bearings including a first bearing and a second bearing downstream of the first bearing in a direction of air circulation at an inlet of the turbomachine , said first bearing forming an axial abutment linked to the stator on which said shaft exerts , under the effect of the rotation of the vanes , an axial force in a given direction during the main operating phases of the turbomachine ,the second bearing comprising an inner ring secured to the shaft and an outer ring mounted on an arm secured to the stator,the turbomachine comprising rolling elements in axial support on the inner ring and on the outer ring,wherein the outer ring comprises a radially extending ring portion, and in that the turbomachine comprises an axial force application device mounted between the arm and the ring portion.2. The turbomachine according to claim 1 , wherein the force application device comprises a piston and further comprises a pressurized oil supply system at the piston claim 1 , so as to exert an axial force on the outer ring by oil supply.3. The turbomachine according to claim 2 , wherein the first bearing comprises a damping ...

AIRCRAFT PROPULSION SYSTEM AND AIRCRAFT POWERED BY SUCH A PROPULSION SYSTEM BUILT INTO THE REAR OF AN AIRCRAFT FUSELAGE

The invention relates to an aircraft propulsion system () intended for being built into the rear of an aircraft fuselage, the propulsion system comprising at least two gas generators () supplying a power turbine () having two counter-rotating turbine rotors () for driving two fans (), and separate air inlets () for supplying each gas generator, characterised in that it comprises an electrical drive device () configured to rotate at least one of the turbine rotors, at least one electrical generator () configured to transform part of the energy of the flow from the gas generators into electrical power and an electric motor () supplied by said electrical generator and capable of rotating at least one of the turbine rotors, said electrical generator being installed on one of said gas generators, and in that said turbine rotor is capable of being rotated simultaneously by a flow from said gas generators and by the electrical drive device. 1. An aircraft propulsion system intended for being integrated into the rear of an aircraft fuselage , the propulsion system comprising , from upstream to downstream in the direction of a gas flow in the propulsion system , at least two gas generators supplying a power turbine having two counter-rotating turbine rotors for driving two fans disposed downstream of the gas generators , and separate air inlets for supplying each gas generator , characterised in that it comprises an electrical drive device configured to rotate at least one of the turbine rotors and comprising at least one electrical generator configured to transform part of the energy of the flow coming from the gas generators into electrical power and an electric motor supplied by said electrical generator and capable of rotating at least one of the turbine rotors , said electrical generator being installed on one of said gas generators , and in that said turbine rotor is capable of being rotated simultaneously by a flow coming from said gas generators and by the electrical ...

A STRUCTURE FOR SUSPENDING A TURBOPROP HAVING TWO UNDUCTED PROPELLERS ON A STRUCTURAL ELEMENT OF AN AIRPLANE

The invention provides a suspension structure for suspending a turboprop () having two unducted propellers on a structural element of an aircraft, the suspension structure comprising a cradle () for fastening to a structural element of the aircraft and having two lateral beams () connected to a main beam () extending parallel to a longitudinal axis () of the turboprop so as to form a V-shaped cradle structure, the cradle being fastened to the turboprop via two angle members () connecting each free end of the lateral beams of the cradle to the turboprop, via an axial link () connecting one end of the main beam of the cradle of the turboprop, and via at least one transverse link () situated in a plane extending transversely relative to the longitudinal axis of the turboprop and connecting the cradle to the turboprop. 1. A suspension structure for suspending a turboprop having two unducted propellers on a structural element of an aircraft , the suspension structure comprising a cradle for fastening to a structural element of the aircraft and having two lateral structures , each of substantially triangular shape , both of which are connected to a main beam extending parallel to a longitudinal axis of the turboprop so as to form a V-shaped cradle structure , the cradle being fastened to the turboprop via two fastener members , each connected to a free end of the lateral structures of the cradle to the turboprop , and via at least one transverse link situated in a plane extending transversely relative to the longitudinal axis of the turboprop and connecting the cradle to the turboprop.2. A structure according to claim 1 , further comprising an axial link suitable for connecting one end of the main beam of the cradle to the turboprop.3. A structure according to claim 1 , including flexible pads mounted on an outside surface of the main beam of the cradle in order to attenuate the vibration generated by the turboprop and transmitted to the aircraft.4. A structure according ...

FAN HAVING A VARIABLE SETTING BY MEANS OF DIFFERENTIAL ROTATION OF THE FAN DISKS

A compressor rotor for a turbomachine including a shaft and at least two disks mounted on the shaft to hold a single set of vanes that are rotatably mobile about the rotational axis of the shaft, at least one first disk being mounted in a mobile manner on the shaft to be able to generate an angular gap in relation to the second disk and to trigger a rotation of the vanes about the radial axis of same, at least one of the two disks being shaped to receive at least one mechanism for attaching the vanes, the connection between the disk and the attaching mechanism enabling a rotation of the attaching mechanism about a radial axis, and connection is a ball-jointed connection that is tangentially and axially mobile. 110-. (canceled)11. A compressor rotor for a turbine engine comprising:a shaft and at least two discs which are mounted on the shaft to ensure retention of a same set of movable vanes during rotation about a rotation axis of the shaft;at least a first disc being mounted in a movable manner on the shaft to be able to generate angular spacing with respect to the second disc;at least one of the two discs being formed to receive at least one fixing means for each vane;a connection between the disc and the fixing means allowing rotation of the fixing means about an axis;wherein the connection is a ball-and-socket joint which is tangentially and axially movable.12. A rotor according to claim 11 , wherein the two discs are formed to receive the fixing means in a form of a ball-and-socket joint which is tangentially and axially movable.13. A rotor according to claim 11 , wherein the disc comprises a cap claim 11 , through which a hole provided with the ball-and-socket joint extends claim 11 , the fixing means for the vanes being an axle which extends through the hole.14. A rotor according to claim 11 , wherein the second disc is fixed in terms of rotation in relation to the shaft claim 11 , the first disc being fixed to an actuation means which comprises a fixed ...

SYSTEM FOR SUPPLYING PRESSURISED AIR INSTALLED IN AN AIRCRAFT TURBINE ENGINE INCLUDING SEALING MEANS

A system for supplying pressurised air installed in an aircraft turbine engine, configured to supply pressurisation air to a portion of the aircraft for using compressed air from pressurisation air collected from a portion for collecting compressed air, characterised in that it comprises a collection port formed on a casing of the compressed air collection portion, a collection member coupled to the collection port, a through port of the collection member formed on a casing of a compartment of the turbine engine, said casing being subjected to small movements relative to the casing of the compressed air portion, the collection member crossing the through port with a freedom of movement relative to the latter during said small movements, a high-pressure space crossed by the collection member, located between the casing of the compressed air collection portion and the casing of the compartment. 1. A system for supplying pressurised air for an aircraft turbine engine , configured to supply pressurisation air to a portion of the aircraft for using compressed air from pressurisation air collected from a portion for collecting compressed air of the aircraft turbine engine , comprising:a port for collecting pressurisation air formed on a casing of the compressed air collection portion of the aircraft turbine engine,a collection member coupled to the collection port to enable the collection and conveyance of the collected pressurisation air towards the portion for using compressed air,a through port of the collection member formed on a casing of a compartment of the turbine engine, said casing being subject to small movements relative to the casing of the portion for collecting compressed air, the collection member crossing the through port with a freedom of movement relative to the latter during said small movements,a high-pressure space crossed by the collection member, located between the casing of the portion for collecting compressed air and the casing of the ...

Aircraft comprising a turbine engine incorporated into the rear fuselage with variable supply

The invention concerns an aircraft propelled by a turbine engine having contrarotating fans ( 7, 8 ), the turbine engine being incorporated at the rear of a fuselage ( 1 ) of the aircraft, in the extension of same and comprising at least two gas generators ( 2 a, 2 b ) that supply, via a shared central stream ( 4 ), a power turbine ( 3 ), the turbine ( 3 ) comprising two contrarotating rotors ( 5, 6 ) for driving two fans ( 7,8 ) disposed downstream from the gas generators ( 2 a, 2 b ), said aircraft comprising means ( 15 ) arranged for separating the gas flow in the power turbine ( 3 ) into at least two concentric streams ( 16, 17 ) and a device comprising first means for distributing the gas flow ( 21 - 24 ) between said streams ( 16, 17 ) from the central stream ( 4 ), the first distribution means being configured to be able to open or close the supply of at least one so-called sealable stream ( 16 ) of the streams ( 16, 17 ) of the power turbine ( 3 ).

AIRCRAFT COMPRISING TWO CONTRA-ROTATING FANS TO THE REAR OF THE FUSELAGE, WITH SPACING OF THE BLADES OF THE DOWNSTREAM FAN

The invention relates to an aircraft comprising a fuselage (), which is propelled by a turbine engine with two coaxial fans, namely an upstream fan () and a downstream fan (), driven by two contra-rotating rotors () of a power turbine (). The two fans () and the turbine () are integrated into a nacelle () which projects downstream from the fuselage () and through which air flows. According to the invention, at least one of the fans () of the aircraft and, in particular, the downstream fan () comprises variable-spacing blades, and at least one stator-forming variable-spacing blade ring () in the aircraft is placed upstream of the upstream fan (). The variable-spacing stator blades () and the variable-spacing blades of the downstream fan () are mutually configured to direct the air flow in a first mode in which the air flows through the nacelle () from upstream to downstream and in a second mode in which the air is pushed back upstream through the nacelle (). 1. Aircraft comprising a fuselage and being propelled by a turbine engine with two coaxial fans , respectively upstream and downstream , driven by two contra-rotating rotors of a power turbine , the two fans and the turbine being integrated in a nacelle downstream of the fuselage , in the extension thereof , and in which an air flow circulates , which aircraft is characterised in that at least one of the fans , and in particular the downstream fan , comprises variable-pitch vanes and wherein at least one ring of variable-pitch vanes forming a stator is placed upstream of the upstream fan , the variable-pitch stator vanes and the variable-pitch vanes of the downstream fan being mutually configured to orient the air flow in a first mode where the air circulates in the nacelle in the upstream to downstream direction and in a second mode where the air is pushed back upstream through the nacelle.2. Aircraft according to claim 1 , wherein a mechanism for rotating a pitch rod for the vanes of the downstream fan is ...

Aircraft comprising a turbine engine incorporated into the rear fuselage comprising a system for blocking the fans

An aircraft comprising a fuselage and propelled by a turbine engine having two coaxial and contrarotating fans, the turbine engine comprising a power turbine having two contrarotating rotors, one of which drives a fan upstream from the turbine, the other a fan downstream from the turbine, each fan comprising a ring of blades, and the assembly of the fans and the power turbine being incorporated at the rear of the fuselage, in the extension of same. The aircraft comprises, for at least one of the fans, a device for blocking the rotation of the fan and a device configured to modify the pitch of the blades of the fan in such a way as to make it operate as a flow straightener with respect to the other fan.

PYLON FOR MOUNTING AN ENGINE ON THE STRUCTURE OF AN AIRCRAFT

A system for pylon attachment for mounting an engine on a structure of an aircraft, or to wings of the aircraft, including a first attachment mechanism that can be secured to the pylon and a second attachment mechanism that can be secured to the structure of the aircraft. A connection mechanism connects the first and second attachment mechanism, the connection mechanism configured to allow movement of the first attachment mechanism in relation to the second attachment mechanism between first and second positions. 17-. (canceled)8. An assembly of a propulsion engine of an aircraft and a system for attaching a strut for mounting the engine on a structure of an aircraft , on its wing , the attachment system comprising:a first attachment means, fixed to the strut;a second attachment means configured to be fixed to the structure of the aircraft; anda connection means connecting the first attachment means to the second attachment means, the connection means configured to allow movement of the first attachment means relative to the second attachment means between a first position and a second position when the engine is subjected to a force resulting from thrust exerted by weight of the engine.9. An assembly according to claim 8 , wherein the first position corresponds to a stopped or cruising-flight position and the second position corresponds to a climbing position of the aircraft.10. An assembly according to claim 8 , wherein the connection means forms a deformable trapezoidal structure with two vertices of the trapezium fixed with respect to the first attachment means and two other vertices of the trapezium fixed with respect to the second attachment means.11. An assembly according to claim 8 , wherein the connection means comprises a movement damper claim 8 , or a movement damper associated with a member for returning to the first position.12. An assembly according to claim 8 , further comprising an actuator controlling change from the first position to the second ...

SELF-CLAMPING FASTENER FOR CMC TURBINE BLADE

The invention relates to a turbine blade having an airfoil () extending above a platform () and a root () extending below said platform, the root of said blade having the form of a radially extending arm (), being produced from composite material and having at least one cylindrical face (), the direction of the generatrices of which is oriented in the direction of said platform so as to allow a clamping piece () to slide towards the latter on said cylindrical face under the action of centrifugal force, characterized in that said arm has, at its lower end, a protuberance () forming a radial bearing point for engagement with an element for retaining the blade on a turbine disc (), and in that the root () is located entirely on the side of said protuberance with respect to said face. 1. Turbine blade comprising a vane extending above a platform and a root extending below said platform , the root of said blade having the form of a radially extending arm , being produced from composite material and having at least a first plane or cylindrical face , oriented axially , the direction of the generatrices of which is oriented towards said platform , so as to allow a clamping piece to slide on said plane or cylindrical face under the action of the centrifugal force that is exerted on said blade during operation on a turbine engine ,characterised in that said arm has at its lower end a protuberance forming the end of the root, and providing a radial bearing point for cooperation with an element for retaining the blade on a turbine disc and in that the root is located entirely on the side of said protuberance relative to said first face.2. Turbine blade according to wherein said first face is oriented at an angle less than or equal to 30° with the radial direction.3. Turbine blade according to wherein said arm comprises a second plane or cylindrical face claim 2 , the direction of the generatrices of which is oriented towards said platform claim 2 , oriented radially claim 2 , ...

AIRCRAFT PROPELLED BY A TURBOJET ENGINE WITH CONTRAROTATING FANS

An aircraft propelled by a turbojet having contrarotating fans, the turbojet being incorporated at the rear of a fuselage of the aircraft and in line therewith and including two gas generators that feed a working turbine having two contrarotating turbine rotors for driving two fans arranged downstream from the gas generators, and distinct air intakes for feeding each gas generator, the air intakes being connected to the fuselage of the aircraft so as to take in at least a portion of the boundary layer formed around the fuselage of the aircraft. 1. An aircraft propelled by a turbojet having contrarotating fans , the turbojet being incorporated at the rear of a fuselage of the aircraft and in line therewith and comprising two gas generators that feed a working turbine having two contrarotating turbine rotors for driving two fans arranged downstream from the gas generators , and distinct air intakes for feeding each gas generator , said air intakes being connected to the fuselage of the aircraft so as to take in at least a portion of the boundary layer formed around the fuselage of the aircraft.2. An aircraft according to claim 1 , wherein the fans present an outside diameter that is substantially identical to the maximum diameter of the fuselage of the aircraft.3. An aircraft according to claim 1 , wherein the gas generators are arranged in primary flow passages forming a V-shape between them.4. An aircraft according to claim 3 , wherein each of the primary flow passages lies at an angle in the range 80° to 120° relative to a longitudinal axis of the fuselage of the aircraft.5. An aircraft according to claim 1 , wherein the working turbine and the fans are centered on a longitudinal axis of the fuselage of the aircraft.6. An aircraft according to claim 1 , wherein the fans are ducted by a nacelle fastened to a vertical empennage of the aircraft. The present invention relates to the general field of aircraft, and in particular to civil airplanes, which aircraft are ...

DEVICE FOR RECOVERING LUBRICATING OIL FROM AN EPICYCLIC REDUCTION GEAR

An epicyclic reduction gear, including a planetary gear movable in rotation about an axis of rotation, planet pinions driven by the planetary gear and movable in rotation about axes of planet gears carried by a planet carrier, the planet pinions rolling on a fixed ring gear and the planet carrier being axially positioned laterally relative to the ring gear, the gear formed by the planet pinions and the ring gear being formed to axially eject lubricating oil thereof after use. The planet carrier includes a radial extension positioned facing the gear and forming a mechanism for guiding the oil to a radial end thereof to be ejected from there by centrifugation. 19-. (canceled)10. A reduction gear having an epicyclic train , comprising:a planet pinion which can be moved in rotation about a rotation axis;satellite type planet pinions which are driven by the planet pinion and which can be moved in rotation about planet shafts which are carried by a planet carrier,the satellite type planet pinions travelling on a fixed ring gear and the planet carrier being axially positioned laterally relative to the ring gear, the gear pair formed by the pinions of the planets and the ring gear being shaped to axially eject lubrication oil thereof after use,wherein the planet carrier comprises a surface portion which is positioned opposite the gear pair and which forms a means for guiding and redirecting the oil, from an axial direction thereof to a radial direction, for ejection by centrifuging at an end thereof, and at least one fixed oil collection gutter that extends radially beyond the planet carrier and is positioned axially opposite the radial extension.11. The reduction gear according to claim 10 , wherein the radial extension is in a form of a partial torus.12. The reduction gear according to claim 11 , wherein the radial extension carries rotating blades which are arranged in a regular manner on a circumference of the planet carrier claim 11 , extending inside the torus.13. The ...

SUSPENSION STRUCTURE WITH VARIABLE GEOMETRY OF A TURBOPROP ENGINE ON A STRUCTURAL ELEMENT OF AN AIRCRAFT

A variable geometry suspension structure for suspending a turboprop from a structural element of an aircraft, the structure including a rear cradle for fastening to a structural element of an aircraft and a front cradle for supporting a front portion of the turboprop, the front cradle being connected to the rear cradle, firstly via a pivot connection configured to enable the front cradle to tilt vertically relative to the rear cradle, and secondly by a return spring configured to prevent the front cradle from tilting while thrust from the turboprop is below a predetermined threshold. 112-. (canceled)13. A variable geometry suspension structure for suspending a turboprop from a structural element of an aircraft , the structure comprising:a rear cradle for fastening to a structural element of an aircraft; anda front cradle for supporting a front portion of the turboprop,the front cradle being connected to the rear cradle, firstly via a pivot connection configured to enable the front cradle to tilt vertically relative to the rear cradle, and secondly by a return spring configured to prevent the front cradle from tilting while thrust from the turboprop is below a predetermined threshold.14. A structure according to claim 13 , further comprising means for preventing any lateral movement of the front cradle relative to the rear cradle.15. A structure according to claim 14 , wherein the rear cradle includes at least one rod including a wheel configured to slide in an axial slot formed in the front cradle to prevent any lateral movement of the front cradle relative to the rear cradle.16. A structure according to claim 15 , wherein the slot is closed at its axial ends to limit angular amplitude of the tilting of the front cradle.17. A structure according to claim 15 , wherein the rod includes two branches forming a rearwardly-open V-shape claim 15 , the wheel being positioned at an intersection between the branches of the rod.18. A structure according to claim 15 , wherein ...

DEVICE FOR LUBRICATING AN EPICYCLOIDAL REDUCER.

Dispositif d'alimentation en huile d'un ensemble de pignons (11, 12, 13) engrenant les uns sur les autres en étant mobiles en rotation autour d'un axe de rotation commun (4), ledit dispositif comprenant un réservoir d'huile (31), au moins une canalisation fixe d'amenée de l'huile (32) au niveau dudit ensemble et des canalisations d'acheminement de l'huile au niveau des engrenages tournants, lesdites canalisations d'acheminement étant également mobiles en rotation autour de l'axe de rotation commun (4) de façon à suivre le mouvement desdits engrenages, caractérisé en ce qu'il comporte un moyen d'éjection de l'huile (33) à l'extrémité de la canalisation fixe d'amenée (32) dont l'orientation comporte une composante radiale dirigée en éloignement de l'axe de rotation commun (4), et un moyen cylindrique (35) de récupération de l'huile mobile en rotation autour dudit axe de rotation commun (4) et positionné en regard dudit moyen d'éjection. Ce moyen alimente des canalisations qui amènent l'huile vers les parties à lubrifier, grâce à l'action du champ centrifuge.

Device for lubricating rolling bearing of double helix turbopropeller of airplane, has flow channel opening to downstream level of downstream roller bearing, and lubricating oil jet opening longitudinally at upstream end of channel

The device has an inner shaft and an outer shaft comprising cylindrical portions (36a, 38a) extending toward a downstream by truncated portions (36b, 38b), which are widened toward the downstream. A downstream rolling bearing (40) is arranged between the inner and outer shafts. A sleeve (58) is equipped within the outer shaft. An annular space is formed around the inner shaft, where the space forms a lubricating oil flow channel (60). The channel opens to a downstream level of the downstream rolling bearing. A lubricating oil jet (56) opens longitudinally at an upstream end of the channel.

Device for recovering lubricating oil from an epicyclic reduction gear

Réducteur à train épicycloïdal, comportant un pignon planétaire (11) mobile en rotation autour d'un axe de rotation, des pignons satellites (12) entraînés par ledit pignon planétaire et mobiles en rotation autour d'axes de satellites (16) portés par un porte satellite (13), lesdits pignons satellites roulant sur une couronne (14) fixe et ledit porte-satellites étant positionné axialement latéralement par rapport à ladite couronne, l'engrenage formé par les pignons des satellites (12) et la couronne (14) étant conformé pour éjecter axialement son huile de lubrification après usage, caractérisé en ce que le porte-satellites (13) comporte une extension radiale positionnée en vis-à-vis dudit engrenage et formant moyen de guidage de ladite huile vers son extrémité radiale pour y être éjectée par centrifugation.

Structure for suspending a twin prop-fan engine from a structural element of an aircraft

The invention relates to a structure for suspending a twin prop-fan engine (10) from a structural element of an aircraft, comprising a cradle (18) intended to be fixed to a structural element of the aircraft and having two lateral beams (22) connected to a main beam (20) running parallel to a longitudinal axis (14) of the prop-fan engine so as to form a V-shaped cradle structure, the cradle being fixed to the prop-fan engine by two brackets (24) connecting each free end of the lateral beams of the cradle to the prop-fan engine, by an axial link rod (28) connecting one end of the main beam of the cradle to the prop-fan engine, and by at least one transverse link rod (30) situated in a plane that is transverse to the longitudinal axis of the prop-fan engine and connecting the cradle to the prop-fan engine.

AIRCRAFT COMPRISING A TURBOMACHINE INTEGRATED WITH REAR FUSELAGE COMPRISING A SYSTEM FOR BLOCKING BLOWERS

AIRCRAFT TURBOKIN ENGINE BLOWER HOUSING

Device for recovering lubricating oil from an epicyclic reduction gear

An epicyclic reduction gear, comprising a planetary gear (11) movable in rotation about an axis of rotation, planet pinions (12) driven by said planetary gear and movable in rotation about axes of planet gears (16) carried by a planet carrier (13), said planet pinions rolling on a fixed ring gear (14) and said planet carrier being axially positioned laterally relative to said ring gear, the gear formed by the planet pinions (12) and the ring gear (14) being formed to axially eject the lubricating oil thereof after use, characterised in that the planet carrier (13) comprises a radial extension positioned facing said gear and forming a means for guiding said oil to the radial end thereof to be ejected from there by centrifugation.

ROTOR BLADE OF A COMPOSITE MATERIAL GAS TURBOMOTOR COMPRISING A CONNECTING HAT, A METHOD OF 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.

Blower element for double-flow turbofan engine, has external ring forming monoblock single piece and directly connected to guide vanes located in downstream of revolving paddles, and stiffener including fixing point of secondary equipments

The element has a blower (2) provided with a casing (7). An external ring (8) of an intermediate casing forms a monoblock single piece (13) made of composite material with the casing of the blower. The external ring is directly connected to outlet guide vanes (5) located in downstream of revolving paddles (4) of the blower. A radial stiffener (14) is arranged on external perimeter of the single piece. The stiffener comprises a fixing point (17) of secondary equipments (16). A deviation edge of a thrust reverser is integrated in the single piece. An independent claim is also included for a method for manufacturing a blower element of a turbojet.

VARIABLE TIMING BLOWER BY DIFFERENTIAL ROTATION OF BLOWER DISKS

Rotor de compresseur pour turbomachine comportant un arbre (12) et au moins deux disques (10a, 10b) montés sur ledit arbre pour assurer le maintien d'un même jeu d'aubes (2) mobiles en rotation autour de l'axe de rotation dudit arbre, caractérisé en ce qu'au moins un premier disque (10a) est monté de façon mobile sur ledit arbre de façon à pouvoir générer un écart angulaire avec ledit second disque(10b) et donner lieu à une rotation des aubes 2 autour de leur axe radial. Turbomachine compressor rotor comprising a shaft (12) and at least two disks (10a, 10b) mounted on said shaft to maintain a same set of blades (2) rotatable about the axis of rotation said shaft, characterized in that at least a first disk (10a) is movably mounted on said shaft so as to be able to generate an angular gap with said second disk (10b) and to cause the blades 2 to rotate about their radial axis.

DEVICE FOR DRIVING A PAIRE OF CONTRAROTIVE PROPELLERS BY AN EPYCYCLOIDAL TRAIN

DEVICE FOR RECOVERING THE LUBRICATING OIL OF AN EPICYCLOIDAL REDUCER.

TURBOMACHINE COMPRISING A CONTRAROTATIVE PROPELLER RECEIVER SUPPORTED BY A STRUCTURAL ENVELOPE FIXED TO THE INTERMEDIATE CASING

La présente invention se rapporte à une turbomachine (1) d'aéronef, du type « open rotor », comprenant un récepteur (30) à hélices contrarotatives ainsi qu'un générateur de gaz double corps (14) comportant un compresseur basse pression (16) ainsi qu'un compresseur haute pression (18) séparés par carter intermédiaire (27), le générateur de gaz étant agencé en amont du récepteur. Selon l'invention, la turbomachine comprend en outre une enveloppe structurale (50) de support du récepteur (30), entourant le générateur de gaz (14) et présentant une extrémité aval (50a) fixée au récepteur ainsi qu'une extrémité amont (50b) fixée au carter intermédiaire (27). De plus, elle comprend des moyens additionnels de liaison (60) entre l'enveloppe structurale de support et le générateur de gaz, agencés entre les extrémités amont et aval (50b, 50a) de l'enveloppe. The present invention relates to an aircraft turbine engine (1), of the "open rotor" type, comprising a receiver (30) with counter-rotating propellers and a double-body gas generator (14) comprising a low-pressure compressor (16). ) and a high pressure compressor (18) separated by intermediate casing (27), the gas generator being arranged upstream of the receiver. According to the invention, the turbomachine further comprises a structural envelope (50) for supporting the receiver (30), surrounding the gas generator (14) and having a downstream end (50a) fixed to the receiver as well as an upstream end ( 50b) fixed to the intermediate casing (27). In addition, it comprises additional connecting means (60) between the structural support envelope and the gas generator, arranged between the upstream and downstream ends (50b, 50a) of the envelope.

SIMPLIFIED BLADE SETTING CONTROL SYSTEM OF A PROPELLER OF A TURBOMOTEUR FOR AN AIRCRAFT

DEVICE FOR DRIVING A PAIRE OF CONTRAROTIVE PROPELLERS BY AN EPYCYCLOIDAL TRAIN

Une turbine (18) d'entraînement d'une roue planétaire (16) et d'un train épicycloïdal (17) comprenant encore un porte-satellites (14) et une couronne (10) de mise en rotation de deux hélices est reliée à la roue planétaire par un manchon souple (22) entourant un arbre de support de turbine (19) plutôt que par l'arbre de support lui-même de façon à réaliser un montage souple avec une position de butée contre l'arbre (19) de manière à soulager le train épicycloïdal (17) d'efforts internes parasites sans tolérer un montage lâche ou une rupture du manchon grâce à l'état de butée après la disparition du jeu (27). A turbine (18) driving a sun wheel (16) and an epicyclic gear (17) further comprising a planet carrier (14) and a ring (10) for rotating two propellers is connected to the sun wheel by a flexible sleeve (22) surrounding a turbine support shaft (19) rather than by the support shaft itself so as to provide a flexible mounting with a stop position against the shaft (19) in such a way as to relieve the planetary gear train (17) from parasitic internal forces without tolerating a loose assembly or a rupture of the sleeve by virtue of the state of abutment after the disappearance of the clearance (27).

AIRCRAFT TURBOMACHINE WITH MECHANICAL REDUCER AND CONTRAROTATIVE TURBINE

Turbomachine (10) d'aéronef à réducteur mécanique (42) et à turbine contrarotative (22), comportant une soufflante (12) entraînée en rotation par un arbre de soufflante (39), un réducteur mécanique (42) à train épicycloïdal, un générateur de gaz comportant une turbine contrarotative (22) dont un premier arbre (36) de turbine est accouplé à un arbre d'entrée (36a) du réducteur ainsi qu'à un tourillon (90), et dont un second arbre (38) de turbine est accouplé à l'arbre de soufflante, caractérisée en ce que le guidage de l'arbre d'entrée du réducteur est assuré par un premier palier à billes (60), le guidage du tourillon est assuré par un deuxième palier à rouleaux (48), et le guidage du premier arbre (36) est assuré notamment par un troisième palier à rouleaux (52) intercalé axialement entre lesdits premier et second paliers. Turbomachine (10) of an aircraft with mechanical reduction gear (42) and with counter-rotating turbine (22), comprising a fan (12) driven in rotation by a fan shaft (39), a mechanical reduction gear (42) with planetary gear, a gas generator comprising a counter-rotating turbine (22), a first turbine shaft (36) of which is coupled to an input shaft (36a) of the reduction gear and to a journal (90), and of which a second shaft (38) of the turbine is coupled to the fan shaft, characterized in that the guiding of the reduction gear input shaft is ensured by a first ball bearing (60), the guiding of the journal is ensured by a second roller bearing (48), and the guiding of the first shaft (36) is ensured in particular by a third roller bearing (52) interposed axially between said first and second bearings.

DEVICE FOR LUBRICATING A DOUBLE PROPELLER TURBOPROPULSOR INTERROBE BEARING BEARING

Nacelle for gas turbine engine that is utilized for aircraft, has transverse partition arranged to be fixed with upstream support, and reinforcement element connecting transverse partition to downstream support

La présente invention porte sur une nacelle de moteur à turbine à gaz comportant une manche d'entrée d'air (16) annulaire avec une paroi intérieure (16i) et une paroi extérieure (16 e) en aval d'un bord d'attaque (16a), les deux parois étant reliées par une cloison transversale (14), la nacelle étant agencée pour équiper un moteur comportant un carter (13) de compresseur formé d'une pluralité d'éléments de carter reliés par des brides (13a, 13b,) dont au moins une bride amont (13a) et une bride (13b) située en aval de la bride amont. La nacelle est caractérisée par le fait que la cloison transversale (14) est fixée à la bride amont (13a) et qu'elle comprend un élément de renfort (11) reliant la cloison transversale (14) à ladite bride aval (13b).

DOUBLE FLOW MOTOR WITH CONTRAROTATIVE TURBINE WHEELS

DOUBLE FLOW MOTOR WITH CONTRAROTATIVE TURBINE WHEELS

Moteur aéronautique double flux comportant une soufflante (1), un compresseur BP (3) et un compresseur HP (4), une chambre de combustion (5), un étage de turbine HP et au moins un étage de turbine BP, ledit étage BP comprenant une première roue aubagée (9a, 10a) et une seconde roue aubagée mobile (9b, 10b, 11b), ladite soufflante étant entrainée par ladite seconde roue par l'intermédiaire d'un second arbre de turbine (2b), caractérisé en ce que ladite première roue de turbine (9a, 10a) est une roue mobile, portée par un premier arbre de turbine (2a) et tournant en sens inverse de la seconde roue (9b, 10b) et en ce que ledit premier arbre (2a) entraine la soufflante (1) par l'intermédiaire d'un module d'inversion de son sens de rotation. A dual-flow aeronautical engine comprising a blower (1), a BP compressor (3) and an HP compressor (4), a combustion chamber (5), an HP turbine stage and at least one LP turbine stage, said LP stage comprising a first bladed wheel (9a, 10a) and a second movable bladed wheel (9b, 10b, 11b), said blower being driven by said second wheel through a second turbine shaft (2b), characterized in that said first turbine wheel (9a, 10a) is a moving wheel, carried by a first turbine shaft (2a) and rotating in opposite direction to the second wheel (9b, 10b) and in that said first shaft (2a) drives the blower (1) via a reversing module of its direction of rotation.

PROPULSIVE AIRCRAFT SYSTEM AND AIRCRAFT PROPULSED BY SUCH AN INTEGRATED PROPULSIVE SYSTEM AT THE BACK OF AN AIRCRAFT FUSELAGE

L'invention concerne un système propulsif (100) d'aéronef destiné à être intégré à l'arrière d'un fuselage de l'aéronef, le système propulsif comprenant, d'amont en aval dans le sens d'un écoulement de gaz dans le système propulsif, au moins deux générateurs de gaz (102a, 102b) alimentant une turbine de puissance (104) ayant deux rotors de turbine (104a, 104b) contra rotatifs pour entraîner deux soufflantes (112a, 112b) disposées en aval des générateurs de gaz, et des entrées d'air (106a, 106b) distinctes pour alimenter chaque générateur de gaz, caractérisé en ce qu'il comprend un dispositif d'entrainement électrique (140) configuré pour entrainer en rotation au moins un des rotors de turbine, et en ce que ledit rotor de turbine est apte à être entrainé en rotation simultanément par un flux provenant desdits générateurs de gaz et par le dispositif d'entrainement électrique. The invention relates to an aircraft propulsion system (100) for integration into the rear of an aircraft fuselage, the propulsion system comprising, from upstream to downstream in the direction of a flow of gas in the propulsion system, at least two gas generators (102a, 102b) supplying a power turbine (104) having two counter-rotating turbine rotors (104a, 104b) to drive two blowers (112a, 112b) arranged downstream of the generators of gas, and separate air inlets (106a, 106b) for supplying each gas generator, characterized in that it comprises an electrical drive device (140) configured to drive at least one of the turbine rotors in rotation, and in that said turbine rotor is able to be driven in rotation simultaneously by a flow coming from said gas generators and by the electric drive device.

VARIABLE GEOMETRY SUSPENSION STRUCTURE OF A TURBOPROPULSER ON A STRUCTURAL ELEMENT OF AN AIRCRAFT

L'invention concerne une structure de suspension (100) à géométrie variable d'un turbopropulseur (4) sur un élément structurel d'un aéronef, comprenant un arceau arrière (102) destiné à être fixé sur un élément structurel d'un aéronef et un arceau avant (104) destiné à supporter une partie avant du turbopropulseur, l'arceau avant étant relié à l'arceau arrière, d'une part par une liaison pivot (116) apte à permettre un basculement vertical de l'arceau avant par rapport à l'arceau arrière, et d'autre part par un ressort de rappel (120) apte à empêcher le basculement de l'arceau avant en deçà d'une poussée de seuil prédéterminée du turbopropulseur. A variable geometry suspension structure (100) of a turboprop (4) on a structural member of an aircraft, comprising a rear bow (102) for attachment to a structural member of an aircraft and a front bow (104) for supporting a front part of the turboprop, the front bow being connected to the rear bow, on the one hand by a pivot connection (116) adapted to allow a vertical tilting of the front bow by relative to the rear arch, and secondly by a return spring (120) adapted to prevent the tilting of the front bow within a predetermined threshold thrust of the turboprop.

EPICYCLOIDAL TRAIN REDUCER WITH BEARING-BASED SATELLITE AXES

Réducteur à train épicycloïdal comprenant une couronne planétaire (14), au moins un pignon satellite (21) roulant sur ladite couronne et mobile en rotation autour d'un axe de satellite (16) porté par un porte-satellites (13), caractérisé en ce que ledit axe de satellite est monté de façon à pouvoir être lui-même mobile en rotation autour de son axe par rapport audit porte-satellites. L'invention est adaptée à un réducteur monté dans un turboréacteur à fort taux de dilution pour l'entraînement de sa soufflante. An epicyclic gear unit comprising a planetary ring gear (14), at least one planet pinion (21) rolling on said ring gear and rotatable about a satellite axis (16) carried by a planet carrier (13), characterized in that said satellite axis is mounted so that it can itself be rotatable about its axis with respect to said planet carrier. The invention is adapted to a gearbox mounted in a turbojet engine with a high dilution ratio for driving its fan.

GAS TURBINE ENGINE NACELLE

VARIABLE TIMING BLOWER BY DIFFERENTIAL ROTATION OF BLOWER DISKS

BELLOW SEALING DEVICE FOR THE CROSSING BY A CONNECTING ROD OF A CONTROL SYSTEM FOR ORIENTATION OF BLOWER BLADES OF A TURBOPROPULSOR

L'invention concerne un dispositif d'étanchéité pour la traversée de cloison par une biellette d'un système de commande de l'orientation des pales de soufflante d'un turbopropulseur. Le dispositif comprend un soufflet (60) de forme tronconique destiné à être traversé par la biellette (50a) et ayant, au niveau de son extrémité la plus large, des moyens de fixation (62, 64) sur la cloison (58) à étancher et, au niveau de son extrémité la plus étroite, un joint torique au travers duquel la biellette est apte à coulisser. The invention relates to a sealing device for the passage of the partition by a connecting rod of a control system of the orientation of the fan blades of a turboprop. The device comprises a frustoconical bellows (60) intended to be traversed by the connecting rod (50a) and having, at its widest end, fastening means (62, 64) on the partition (58) to be sealed. and, at its narrowest end, an O-ring through which the link is slidable.

DISTRIBUTOR FOR TURBOMOTEUR

AIRCRAFT TURBOMACHINE WITH MECHANICAL REDUCER AND CONTRAROTATING TURBINE

Turbomachine (10) d'aéronef à réducteur mécanique (42) et à turbine contrarotative (22), comportant une soufflante (12) entraînée en rotation par un arbre de soufflante (39), un réducteur mécanique (42) à train épicycloïdal, un générateur de gaz comportant une turbine contrarotative (22) dont un premier arbre (36) de turbine est accouplé à un arbre d'entrée (36a) du réducteur ainsi qu'à un tourillon (90), et dont un second arbre (38) de turbine est accouplé à l'arbre de soufflante, caractérisée en ce que le guidage de l'arbre d'entrée du réducteur est assuré par un premier palier à billes (60), le guidage du tourillon est assuré par un deuxième palier à rouleaux (48), et le guidage du premier arbre (36) est assuré notamment par un troisième palier à rouleaux (52) intercalé axialement entre lesdits premier et second paliers. Aircraft turbomachine (10) with mechanical reduction gear (42) and contra-rotating turbine (22), comprising a fan (12) driven in rotation by a fan shaft (39), a mechanical reduction gear (42) with epicyclic train, a gas generator comprising a counter-rotating turbine (22), a first turbine shaft (36) of which is coupled to an input shaft (36a) of the reducer and to a journal (90), and of which a second shaft (38) turbine is coupled to the fan shaft, characterized in that the guide of the input shaft of the reduction gear is provided by a first ball bearing (60), the guide of the journal is provided by a second roller bearing (48), and the guiding of the first shaft (36) is provided in particular by a third roller bearing (52) interposed axially between said first and second bearings.

VARIABLE GEOMETRY SUSPENSION STRUCTURE OF A TURBOPROPULSER ON A STRUCTURAL ELEMENT OF AN AIRCRAFT

PROPELLANT AIRCRAFT ASSEMBLY

PRESSURIZED AIR SUPPLY SYSTEM INSTALLED IN AN AIRCRAFT TURBOMACHINE HAVING SEALING MEANS

L'objet principal de l'invention est un système (1) d'alimentation en air sous pression installé dans une turbomachine d'aéronef, configuré pour alimenter en air de pressurisation une partie d'utilisation d'air comprimé à partir d'air de pressurisation prélevé depuis une partie de prélèvement d'air comprimé (12), caractérisé en ce qu'il comporte un organe de prélèvement (32) raccordé à un port de prélèvement (30), pourvu d'un port de passage (38), une chambre pressurisée (33) traversée par l'organe de prélèvement (32), le système (1) comportant en outre des moyens d'étanchéité (2) pour former une séparation sensiblement étanche entre la chambre pressurisée (33) et un espace libre (40) communicant avec un compartiment (ZC) de turbomachine et ménagé autour de l'organe de prélèvement (32), afin de se prémunir de l'introduction d'air sous pression de la chambre pressurisée (33) à l'intérieur de l'organe de prélèvement (32) en cas de rupture de dernier. The main object of the invention is a system (1) for supplying pressurized air installed in an aircraft turbine engine, configured to supply pressurizing air with a portion of compressed air using air pressurizing device taken from a compressed air sampling portion (12), characterized in that it comprises a sampling member (32) connected to a sampling port (30) provided with a passage port (38) , a pressurized chamber (33) traversed by the sampling member (32), the system (1) further comprising sealing means (2) for forming a substantially sealed separation between the pressurized chamber (33) and a space free wheel (40) communicating with a turbomachine compartment (ZC) and arranged around the sampling member (32), in order to guard against the introduction of pressurized air from the pressurized chamber (33) inside. of the sampling member (32) in case of breakage of last r.

DEVICE ADAPTED TO BE PROVIDED WITH PROPELLER BLADES

AIRCRAFT COMPRISING TWO CONTRAROTATIVE BLOWERS AT THE REAR OF A FUSELAGE WITH BLOCKING OF THE BLOWERS OF THE AVAL BLOWER

L'invention concerne un aéronef comportant un fuselage (1) et propulsé par une turbomachine à deux soufflantes coaxiales, respectivement amont (7) et aval (8), entrainées par deux rotors (5, 6) contrarotatifs d'une turbine de puissance (3), les deux soufflantes (7, 8) et la turbine (3) étant intégrées dans une nacelle (14) à l'aval du fuselage (1), dans le prolongement de celui-ci, aéronef caractérisé en ce qu'au moins une des soufflantes (7, 8), et en particulier la soufflante aval (8), comporte des aubes à calage variable. The invention relates to an aircraft comprising a fuselage (1) and propelled by a turbomachine with two coaxial blowers, respectively upstream (7) and downstream (8), driven by two rotors (5, 6) counter-rotating a power turbine ( 3), the two blowers (7, 8) and the turbine (3) being integrated into a nacelle (14) downstream of the fuselage (1), in the extension thereof, an aircraft characterized in that at least one of the blowers (7, 8), and in particular the downstream blower (8), comprises variable-pitch vanes.

TORSION MEASURING DEVICE FOR A ROTATING SHAFT

Mesure de torsion d'un arbre tournant par faisceau laser et filtres polarisants. Le dispositif de mesure comprend un générateur de faisceau laser (27), deux filtres polarisants (29, 31) solidaires de l'arbre (25) et distants l'un de l'autre et un récepteur de rayonnement laser (33) recevant le faisceau laser ayant traversé ces deux filtres. Torsional measurement of a rotating shaft by laser beam and polarizing filters. The measuring device comprises a laser beam generator (27), two polarizing filters (29, 31) integral with the shaft (25) and spaced from each other and a laser radiation receiver (33) receiving the laser beam having passed through these two filters.

SYSTEM FOR CONTRAROTATIVE PROPELLERS HAVING A DEVICE FOR FLAPPING PROPELLER BLADES

FLUID SUPPLY DEVICE FOR A HYDRAULIC CYLINDER FOR CONTROLLING THE ORIENTATION OF BLOWER BLADES OF A DOUBLE PROPELLER TURBOPROPULSER

The invention relates to a device (100) for supplying fluid to a hydraulic jack for controlling the orientation of the fan blades of a twin fan turboprop, comprising a fluid distributor (120) secured to a rotor of the turboprop and comprising a cylindrical part (121) which is equipped with at least two fluid circulation grooves (123) each having an outlet orifice (125), a fluid inlet support (110) secured to a fixed part of the turboprop and comprising a cylindrical part (111) equipped with at least two separate fluid passages (113) opening onto fluid inlet tubes (44) and each emerging radially into one of the fluid circulation grooves of the distributor, and a well (130) that rotates as one with the fluid distributor and comprises a cylindrical part (131) equipped with at least two fluid flow ducts (132) each supplied with fluid by one of the outlet orifices of the fluid distributor, each fluid flow duct emerging into one chamber of a control jack.

AIRCRAFT COMPRISING A TURBOMACHINE INTEGRATED WITH REAR FUSELAGE WITH VARIABLE POWER SUPPLY

L'invention concerne un aéronef propulsé par une turbomachine à soufflantes contrarotatives (7, 8), la turbomachine étant intégrée à l'arrière d'un fuselage (1) de l'aéronef, dans le prolongement de celui-ci et comprenant au moins deux générateurs de gaz (2a, 2b) qui alimentent, par une veine centrale (4) commune, une turbine de puissance (3), la turbine (3) comportant deux rotors contrarotatifs (5, 6) pour entraîner deux soufflantes (7,8) disposées en aval des générateurs de gaz (2a, 2b), aéronef caractérisé en ce qu'il comporte des moyens (15) agencés pour séparer le flux de gaz dans la turbine de puissance (3) en au moins deux veines concentriques (16, 17) et un dispositif de distribution du flux de gaz (21-24) entre ces veines (16, 17) à partir de la veine centrale (4), ledit dispositif de distribution étant configuré pour pourvoir ouvrir ou fermer l'alimentation d'au moins une veine (16), dite occultable, parmi les veines (16, 17) de la turbine de puissance (3).

PYLONE FOR MOUNTING AN ENGINE TO THE STRUCTURE OF AN AIRCRAFT

PLANE PROPELLED BY A TURBOREACTOR WITH CONTRAROTATIVE BLOWERS

PRESSURIZED AIR SUPPLY SYSTEM INSTALLED IN AN AIRCRAFT TURBOMACHINE HAVING SEALING MEANS

L'objet principal de l'invention est un système (1) d'alimentation en air sous pression installé dans une turbomachine d'aéronef, configuré pour alimenter en air de pressurisation une partie d'utilisation d'air comprimé à partir d'air de pressurisation prélevé depuis une partie de prélèvement d'air comprimé (12), caractérisé en ce qu'il comporte un organe de prélèvement (32) raccordé à un port de prélèvement (30), pourvu d'un port de passage (38), une chambre pressurisée (33) traversée par l'organe de prélèvement (32), le système (1) comportant en outre des moyens d'étanchéité (2) pour former une séparation sensiblement étanche entre la chambre pressurisée (33) et un espace libre (40) communicant avec un compartiment (ZC) de turbomachine et ménagé autour de l'organe de prélèvement (32), afin de se prémunir de l'introduction d'air sous pression de la chambre pressurisée (33) à l'intérieur de l'organe de prélèvement (32) en cas de rupture de dernier. The main object of the invention is a pressurized air supply system (1) installed in an aircraft turbine engine, configured to supply pressurization air to a compressed air utilization part from air pressurization pump taken from a compressed air tapping part (12), characterized in that it comprises a tapping member (32) connected to a tapping port (30), provided with a passage port (38) , a pressurized chamber (33) through which the sampling member (32) passes, the system (1) further comprising sealing means (2) to form a substantially sealed separation between the pressurized chamber (33) and a space free (40) communicating with a turbomachine compartment (ZC) and arranged around the sampling member (32), in order to guard against the introduction of pressurized air from the pressurized chamber (33) inside of the sampling member (32) in the event of the latter breaking.

MECHANICAL TRANSMISSION DEVICE FOR THE ROTATION DRIVE OF THE CONTRAROTATIVE PROPELLERS OF A DOUBLE PROPELLER TURBOPROPULSOR.

Dispositif de transmission mécanique pour l'entraînement en rotation des hélices contra rotatives d'un turbopropulseur à double hélice, comprenant : un train épicycloïdal (102) ayant un planétaire (104) porté par un arbre planétaire (106) qui est centré sur un axe longitudinal (12) du turbopropulseur et qui est destiné à être relié vers l'amont à un rotor (30) d'une turbine du turbopropulseur pour être entraîné en rotation ; au moins un satellite (108) engrenant avec le planétaire ; un porte-satellite (112) portant de manière rotative le satellite et qui est porté par un arbre de porte-satellite (114) destiné à être relié vers l'aval à un premier ensemble d'hélices pour l'entraîner en rotation ; et une couronne (116) engrenant le satellite et qui est portée par un arbre de couronne (118) destiné à être relié vers l'aval à un second ensemble d'hélices pour l'entraîner en rotation ; l'arbre planétaire comprenant une extrémité amont (106a) munie d'une bride amont (120) s'étendant radialement vers l'extérieur, et une extrémité aval (106b) opposée à l'extrémité amont et munie d'une bride aval (122) formée en aval du train épicycloïdal et s'étendant radialement vers l'extérieur. A mechanical transmission device for rotating the contra-rotating propellers of a twin-propeller turboprop, comprising: an epicyclic gear train (102) having a sun gear (104) carried by a planet shaft (106) which is centered on an axis longitudinal section (12) of the turboprop engine and which is intended to be connected upstream to a rotor (30) of a turboprop turbine to be rotated; at least one satellite (108) meshing with the sun gear; a planet carrier (112) rotatably carrying the satellite and carried by a planet carrier shaft (114) to be downstream connected to a first set of propellers to drive it in rotation; and a ring gear (116) meshing with the satellite and carried by a ring gear (118) to be connected downstream to a ...

DEVICE FOR LUBRICATING AN EPICYCLOIDAL REDUCER COMPATIBLE WITH A MODULAR ASSEMBLY.

OXYGENATION BIOREACTOR AND SEPARATE BACTERIAL BED.

Turbomachine e.g. jet engine, for aircraft, has connection unit with air flow annular channel centered on longitudinal axle, where channel is traversed by oblique torque arms connecting internal units with streamline annual cases

The turbomachine has a connection unit with an air flow annular channel (76) centered on a longitudinal axle (40). The channel is externally determined by internal surfaces (54, 68) of streamline annual cases (52, 66) of open rotor type upstream and downstream contra-rotating propellers (26, 28), and is internally determined by internal units (42, 44) of the propellers. The channel is traversed by oblique torque arms (50, 64) connecting the internal units with the cases.

DECOUPLING DEVICE FOR TURBOMACHINE COMPRISING AN INTERMEDIATE PIECE

L'objet principal de l'invention est un dispositif de découplage (10) entre une structure fixe (5) d'une turbomachine (1) et une première pièce (6 ; 6a) formant support d'un palier (4) d'un arbre d'entraînement (3) d'un rotor (2) de la turbomachine (1), le dispositif de découplage (10) comportant une pluralité de vis fusibles (11) pour la fixation de la première pièce support de palier (6 ; 6a) avec la structure fixe (5) de la turbomachine (1), caractérisé en ce qu'il comporte en outre au moins une pièce intermédiaire (16) située entre la première pièce support de palier (6 ; 6a) et la structure fixe (5) de la turbomachine (1), au niveau des vis fusibles (11), pour permettre le découplage. The main object of the invention is a decoupling device (10) between a fixed structure (5) of a turbomachine (1) and a first piece (6; 6a) forming a support of a bearing (4) of a drive shaft (3) of a rotor (2) of the turbomachine (1), the decoupling device (10) having a plurality of fusible screws (11) for fixing the first bearing support part (6) 6a) with the fixed structure (5) of the turbomachine (1), characterized in that it further comprises at least one intermediate piece (16) located between the first bearing support piece (6; 6a) and the structure fixed (5) of the turbomachine (1), at the level of the fusible screws (11), to allow decoupling.

System including counter-rotating propellers driven by an epicyclic train ensuring a balanced couple distribution between the two propellers

La présente invention se rapporte à un système d'hélices contrarotatives (30) pour turbomachine d'aéronef, comprenant : une turbine libre de puissance (32) comprenant un premier rotor (32a); une première et une seconde hélices (7, 9); et un dispositif de transmission mécanique (13) comprenant un train épicycloïdal (15) muni d'un planétaire (17) entraîné par le rotor (32a), au moins un satellite (21), un porte-satellite(s) (25) entraînant la première hélice (7), ainsi qu'une couronne (31) entraînant ladite seconde hélice (9). Selon l'invention, la turbine libre (32) comprend également un second rotor (32b) contrarotatif vis-à-vis du premier rotor (32a), et entraînant en rotation la couronne (31). The present invention relates to a counter-rotating propeller system (30) for an aircraft turbomachine, comprising: a power free turbine (32) comprising a first rotor (32a); a first and second propellers (7, 9); and a device mechanical transmission (13) comprising an epicyclic gear train (15) provided with a sun gear (17) driven by the rotor (32a), at least a satellite (21), a carrier (s) (25) driving the first propeller (7), as well as a crown (31) driving said second helix (9). According to the invention, the free turbine (32) also comprises a second rotor (32b) counter-rotating with respect to the first rotor (32a), and rotating the crown (31).

improved contra-rotating turbine housing architecture

Architecture améliorée de carter tournant de turbine contrarotative Turbine contrarotative (C) de turbomachine (10) s’étendant autour d’un axe de rotation (X) et comprenant un rotor interne ayant un tambour interne (50a) sur lequel est fixé une pluralité de roues mobiles internes (22) comprenant chacune des aubes mobiles internes et étant supportées en rotation par un premier arbre (26),un rotor externe ayant un tambour externe (50b) sur lequel est fixé une pluralité de roues mobiles externes (20) comprenant chacune des aubes mobiles internes et étant supportées en rotation par un deuxième arbre (24) coaxial au premier arbre (26), le rotor externe comprenant une roue mobile aval (60) ayant une pluralité d’aubes mobiles avals (61) s’étendant chacune entre une virole externe (62), fixée au tambour externe en aval de celui-ci, et une virole interne (63) fixée au deuxième arbre (24),au moins une des extrémités radiales des aubes mobiles avals (61) étant fixée à la virole interne (63) ou à la virole externe (62) au moyen d’une liaison articulée (70). Figure pour l’abrégé : Fig. 3. Improved architecture of rotating housing counter-rotating turbine Counter-rotating turbine (C) of a turbomachine (10) extending around an axis of rotation (X) and comprising an internal rotor having an internal drum (50a) to which are fixed a plurality of internal moving wheels (22) each comprising internal movable vanes and being rotatably supported by a first shaft (26), an outer rotor having an outer drum (50b) to which are fixed a plurality of outer movable wheels (20) each comprising inner movable vanes and being supported in rotation by a second shaft (24) coaxial with the first shaft (26), the outer rotor comprising a downstream movable wheel (60) having a plurality of downstream movable vanes (61) each extending between an outer shell (62), fixed to the outer drum downstream thereof, and an inner ring (63) fixed to the second shaft (24), at least one of the radial ends of the ...

High pressure turbine blade for rotor of double flow type turbojet in aeronautical field, has foot mounted on rotor disk, where foot of blade is provided as lengthened band that is rolled up around two cylindrical supports

L'invention concerne une aube (20) de turbomachine en matériau composite, comprenant un pied (22) destiné à être monté sur un disque de rotor (10), le pied de l'aube se présentant sous la forme d'une bande sensiblement allongée qui est enroulée autour d'au moins deux supports cylindriques (30).

TORSION MEASURING DEVICE FOR A ROTATING SHAFT

DEVICE FOR SEALING A HOUSING FOR THE CROSSING CROSS BY A CONNECTING ROD OF A CONTROL SYSTEM FOR ORIENTATION OF BLOWER BLADES OF A TURBOPROPULSOR

Contrarotating propeller system for turbine engine, has internal gear meshed with satellite of mechanical transmission device, where internal gear is fixed with respect to stator and has internal teeth

The system has downstream and upstream propellers (6, 8) that rotate around a longitudinal axis (4) with respect to a stator (2). A mechanical transmission device (12) has a planetary gearing (14) equipped with a planet gear (16) centered on the longitudinal axis, where the gear is driven by a turbine of a turbine engine. The device (12) has a satellite (40) associated to a satellite (20) of the gearing (14), and an internal gear (42) has internal teeth, where the internal gear is meshed with the satellite (40). The internal gear (42) is fixed with respect to the stator. An independent claim is also included for a method for piloting a contrarotating propeller system.

SUSPENSION LINKS OF THE COLD FLOW CHANNEL OF A TURBOJUSTER WITH EXCENTRIC BALLS

DEVICE WITH CONTRAROTATIVE PROPELLERS HAVING A MEANS FOR CHANGING THE STEPS OF THE PROPELLERS

Improved architecture of a contra-rotating turbine engine

Architecture améliorée de turbomachine à turbine contrarotative Turbine contrarotative (C) de turbomachine (10) s’étendant autour d’un axe de rotation (X) et comprenant un rotor interne (22) tournant autour de l’axe de rotation (X), et comprenant au moins une aube mobile interne (220) supportée en rotation par un premier arbre (26), un rotor externe (20) tournant autour de l’axe de rotation (X) dans un sens opposé au rotor interne (22), et comprenant au moins une aube mobile externe (200) supportée en rotation par un deuxième arbre (24) coaxial au premier arbre (26), les premier et deuxième arbres (24, 26) s’étendant axialement de l’amont vers l’aval de la turbine (C), dans lequel le premier arbre (26) est guidé en rotation par un premier palier (62) disposé entre le premier arbre et un carter amont (60) de la turbine, et le deuxième arbre (24) est guidé en rotation par un deuxième palier (72) disposé entre le deuxième arbre (24) et ledit carter amont (60) de la turbine. Figure pour l’abrégé : Fig. 2.

TURBOPROPULSEUR COMPRISING AN ADJUSTABLE ORIENTATION BLADE ASSEMBLY

DEVICE FOR SEALING A HOUSING FOR THE CROSSING CROSS BY A CONNECTING ROD OF A CONTROL SYSTEM FOR ORIENTATION OF BLOWER BLADES OF A TURBOPROPULSOR

L'invention concerne un dispositif d'étanchéité pour la traversée de cloison par une biellette d'un système de commande de l'orientation des pales de soufflante d'un turbopropulseur. Le dispositif comprend un tube (60) destiné à être fixé sur la cloison (58) à étancher, et un fourreau (62) de forme tronconique destiné à être traversé par la biellette (50a), le fourreau pouvant coulisser axialement à l'intérieur du tube et ayant, au niveau de son extrémité la plus large, des moyens d'étanchéité avec le tube et, au niveau de son extrémité la plus étroite, des moyens de fixation étanche à une extrémité correspondante de la biellette. The invention relates to a sealing device for the passage of the partition by a connecting rod of a control system of the orientation of the fan blades of a turboprop. The device comprises a tube (60) intended to be fixed on the partition (58) to be sealed, and a sleeve (62) of frustoconical shape intended to be traversed by the rod (50a), the sleeve being able to slide axially inside. of the tube and having, at its widest end, sealing means with the tube and, at its narrowest end, means for sealing at a corresponding end of the rod.

TURBOMACHINE TURBINE AUB COOLING AIR CIRCULATION SYSTEM

L'objet principal de l'invention est un système (1) de circulation d'air de refroidissement (A1-A4) d'aubes (24a) de turbine (24) d'une turbomachine (10), caractérisé en ce qu'il comporte un conduit amont (2) de circulation d'air de refroidissement (A1) pour le prélèvement d'air de refroidissement (A1) depuis un compresseur (22) de la turbomachine (10), un conduit aval (3) de circulation d'air de refroidissement (A3) pour l'acheminement d'air de refroidissement (A4) vers les aubes (24a) de turbine (24), et un échangeur thermique (4) positionné entre le conduit amont (2) et le conduit aval (3) pour refroidir l'air de refroidissement (A1) prélevé depuis le compresseur (22) avant son acheminement vers les aubes (24a) de turbine (24) par l'intermédiaire du conduit aval (3). The main object of the invention is a system (1) for circulating cooling air (A1-A4) of turbine blades (24a) (24) of a turbomachine (10), characterized in that it comprises an upstream duct (2) for cooling air circulation (A1) for the extraction of cooling air (A1) from a compressor (22) of the turbomachine (10), a downstream duct (3) for circulation cooling air (A3) for conveying cooling air (A4) to the turbine blades (24a) (24), and a heat exchanger (4) positioned between the upstream duct (2) and the duct downstream (3) for cooling the cooling air (A1) taken from the compressor (22) before it is conveyed to the turbine blades (24a) (24) via the downstream duct (3).

Retainer for open rotor turbo engine of aircraft, has support structure comprising support unit that is carried by antifriction bearing inter-turbine, where two ends of support unit is mounted on turbine

La présente invention se rapporte à un récepteur (30) de turbomachine d'aéronef (1) à doublet d'hélices contrarotatives non carénées, comprenant : - un ensemble tournant (32a) muni d'une première hélice (32), d'une première turbine libre de puissance (34) entraînant la première hélice, et d'un premier dispositif structural tournant (33) prolongeant axialement la première turbine et supportant la première hélice, - une structure de support (60) du premier ensemble tournant (32a), comprenant des premiers moyens de support (62) portant le premier dispositif structural tournant (33), lui-même portant le carter extérieur (58) du doublet de turbines à l'une des deux extrémités axiales de la turbine (34), et des seconds moyens de support (84) portés par un palier de roulement inter-turbine (72) et montés sur la turbine (34) à l'autre des ses deux extrémités.

EPICYCLOIDAL TRAIN REDUCER WITH BEARING-BASED SATELLITE AXES

SUSPENSION LINKS OF THE COLD FLOW CHANNEL OF A TURBOJUSTER WITH EXCENTRIC BALLS

Dispositif d'assemblage d'une bielle (3) sur le carter d'une turbomachine comprenant, outre ledit organe de suspension, une chape (4) solidaire du carter et comportant au moins deux oreilles alésées coaxialement, et un axe (9) traversant les alésages desdites oreilles auquel est attaché, de façon mobile en rotation radiale, ledit organe de suspension par l'intermédiaire d'une rotule (10) entourant l'axe, ledit axe étant maintenu en place dans les oreilles de ladite chape par des moyens de liaison (11, 12, 14) aptes à être entraînés en rotation autour de l'axe desdits alésages, caractérisé en ce que ladite rotule et lesdits moyens de liaison sont conformés pour que la rotation desdits moyens de liaison autour de l'axe d'alésage des oreilles entraîne un décalage de l'axe de rotation de la bielle (3) dans une direction perpendiculaire audit axe des alésages. Device for assembling a connecting rod (3) on the casing of a turbomachine comprising, in addition to said suspension member, a yoke (4) secured to the casing and comprising at least two coaxially bored lugs, and a traversing shaft (9) the bores of said lugs to which is attached, in a mobile manner in radial rotation, said suspension member via a ball joint (10) surrounding the axis, said axis being held in place in the ears of said yoke by means link (11, 12, 14) adapted to be rotated about the axis of said bores, characterized in that said ball and said connecting means are shaped so that the rotation of said connecting means about the axis of Boring of the ears causes a shift of the axis of rotation of the connecting rod (3) in a direction perpendicular to said axis of the bores.

PROPULSIVE SYSTEM FOR AIRCRAFT

DEVICE FOR MEASURING THE TORQUE OF A TURBOMACHINE SHAFT AND TURBOMACHINE INCLUDING SUCH A DEVICE

L’invention concerne un dispositif de mesure du couple de torsion d’un arbre rotatif (10) de turbomachine, comprenant : un émetteur (12) émettant un faisceau laser (F), un miroir (14) renvoyant le faisceau laser, des obturateurs (16, 18) présentant chacun des secteurs obturateurs et des lumières, les obturateurs étant agencés de sorte à ce qu’au moins une lumière de chaque obturateur est traversée par le faisceau laser, les obturateurs étant mobiles avec l’arbre, et les lumières des obturateurs étant mutuellement agencées de sorte que le nombre de lumières laissant passer le faisceau laser augmente proportionnellement avec la torsion de l’arbre sous l’effet du couple, un récepteur (26) recevant le faisceau laser renvoyé (F’) et émettant un signal représentatif du faisceau laser reçu, et un calculateur recevant le signal émis et comptant le nombre de lumières laissant passer le faisceau laser sur la base du signal. Figure pour l'abrégé : Figure 1

PRODUCT AND PROCESS FOR THE MODIFIER TREATMENT OF THE SURFACE CONDITION AND / OR TINT OF TEXTILE ARTICLES

A particulate product for treating, in an aqueous medium, textile articles at least partially formed of optionally coloured cellulose materials, to modify their surface state and/or their shade is described. The particulate product comprises a foamed perlite forming an adsorption substrate, and one or more cellulolytic enzymes adsorbed by said substrate. The textile articles of interest are, for example, fabrics, knits, some non-woven fabrics, trousers, skirts and other textile products.

AIR FLOW RECTIFYING STRUCTURE FOR AN AIRCRAFT ENGINE NACELLE