Patent application number | Description | Published |
20080247877 | 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. | 10-09-2008 |
20090311100 | 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. | 12-17-2009 |
20100104438 | 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. | 04-29-2010 |
20100205934 | BYPASS ENGINE WITH CONTRAROTATING TURBINE WHEELS - Bypass aeronautical engine comprising a fan ( | 08-19-2010 |
20110014046 | 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. | 01-20-2011 |
20110070086 | 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. | 03-24-2011 |
20110076143 | 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. | 03-31-2011 |
20110243735 | 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. | 10-06-2011 |
20110273724 | 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. | 11-10-2011 |
20110305575 | 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. | 12-15-2011 |
20110311361 | 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. | 12-22-2011 |
20120070289 | 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 ( | 03-22-2012 |
20120070290 | 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. | 03-22-2012 |
20120070292 | 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. | 03-22-2012 |
20120099988 | 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. | 04-26-2012 |
20120308385 | 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. | 12-06-2012 |
20130017087 | DEVICE FOR CONTROLLING THE PITCH OF TURBOPROP FAN BLADESAANM GALLET; FrancoisAACI ParisAACO FRAAGP GALLET; Francois Paris FR - 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. | 01-17-2013 |
20130045102 | 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. | 02-21-2013 |
20130098066 | 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 ( | 04-25-2013 |
20130108432 | AIRFLOW-STRAIGHTENING STRUCTURE FOR THE NACELLE OF AN AIRCRAFT ENGINE | 05-02-2013 |
20130111873 | 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. | 05-09-2013 |
20130121814 | 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. | 05-16-2013 |
20130183143 | 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. | 07-18-2013 |
20130224021 | 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. | 08-29-2013 |
20130225353 | 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. | 08-29-2013 |
20130277454 | 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. | 10-24-2013 |
20140119939 | 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. | 05-01-2014 |
20140150404 | 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. | 06-05-2014 |
20140186182 | 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. | 07-03-2014 |
20150239569 | 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. | 08-27-2015 |
20150275680 | SELF-CLAMPING FASTENER FOR CMC TURBINE BLADE - The invention relates to a turbine blade having an airfoil ( | 10-01-2015 |
20150291285 | 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. | 10-15-2015 |
Patent application number | Description | Published |
20100205934 | BYPASS ENGINE WITH CONTRAROTATING TURBINE WHEELS - Bypass aeronautical engine comprising a fan ( | 08-19-2010 |
20110176924 | DEVICE ADAPTED TO BE FITTED WITH PROPELLER BLADES - A device adapted to be fitted with propeller blades includes a first retention ring including over a periphery thereof a plurality of radial bores; and a second retention ring including over a periphery thereof a plurality of radial bores, the first and second retention rings being mounted one on top of the other in the radial direction, each bore in the first retention ring being positioned opposite a bore in the second retention ring, a bore in the first retention ring arranged opposite a bore in the second retention ring forming a bore pair adapted to receive a foot of a blade. | 07-21-2011 |
20110180171 | OBSTRUCTIVE CAP FOR A ROTATING HOLLOW TRANSMISSION SHAFT - A sealing plug for a hollow shaft used to impart a rotational speed, the hollow shaft including a first end adapted to be located in a chamber containing lubricant, and a second end adapted to be located outside the chamber. The sealing plug has a substantially cylindrical surface, a first face and a second face for insertion into the first end of the hollow shaft. The plug also includes a cavity that is open at the second face and a first radial duct opening, at one of its ends, at the cavity and, at its opposite end, at the substantially cylindrical surface of the sealing plug. The device is applied particularly in the field of turbomachines equipped with an open rotor. | 07-28-2011 |
20110236212 | FEATHERING DEVICE FOR THE FAN BLADES OF A TURBOPROP ENGINE - The invention concerns a feathering device for the fan blades of a turboprop engine that includes at least one set of fan blades ( | 09-29-2011 |
20120018079 | 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. | 01-26-2012 |
20120308385 | 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. | 12-06-2012 |
20130045102 | 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. | 02-21-2013 |