Patent application number | Description | Published |
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 |
20110198155 | METHOD AND SYSTEM FOR LUBRICATING A TURBINE ENGINE - A method and a system for lubricating a turbine engine including at least three separate housings each including at least one roller bearing. The method pressurizes the housings through seals, of which two main housings are pressurized at a pressure higher than that of a remaining secondary housing, lubricates a secondary roller bearing only by injecting an oil mist from at least one of the main housings, the oil mist being supplied by a pressure difference between the main housings and the secondary housing, recovers a remainder of the lubrication oil injected into the main housings to supply the same to an oil tank, and supplies the air/oil mixture from the secondary housing to an oil separator. | 08-18-2011 |
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 |
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 |
20120251314 | CMC TURBINE NOZZLE ADAPTED TO SUPPORT A METALLIC TURBINE INTERNAL CASING BY A RADIAL CONTACT - Composite material turbine nozzle blade including an airfoil ( | 10-04-2012 |
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 |
20130011259 | MECHANISM FOR VARIABLE ADJUSTMENT OF BLADES FOR A SYSTEM OF CONTRA-ROTATING PROPELLERS, AND A SYSTEM OF CONTRA-ROTATING PROPELLERS COMPRISING AT LEAST ONE SUCH MECHANISM - A mechanism for adjusting pitch of blades of a propeller of a system of contra-rotating propellers for a turbomachine, wherein each blade moves around a radial axis. The mechanism includes a linear actuator, a structure to transform movement imparted by the linear actuator into rotation of each of the blades in a synchronized manner around their radial axis, the structure including a bracket of longitudinal axis formed of a central ring, an outer ring, and multiple radial arms rigidly connected to the central ring and to the outer ring. The central ring can be subject to actuation of the linear actuator, and the central ring and the outer ring are positioned in two separate planes, orthogonal to the longitudinal axis, such that the bracket is shaped as a truncated cone. | 01-10-2013 |
20140017086 | SYSTEM FOR CHANGING THE PITCH OF THE CONTRA-ROTATING PROPELLERS OF A TURBOSHAFT ENGINE - A system, including: a linear actuator axially arranged in a first propeller and rotatably secured thereto, a first linking mechanism connecting a rod of the linear actuator to a second propeller to change a setting of blades thereof, and including an intermediate bearing between the propellers, which is capable of transmitting translation of the rod of the linear actuator and disconnecting a rotatable link to the first propeller to make it possible to change the setting of the blades of the second propeller rotated in an opposite direction to the first propeller, and a second linking mechanism combined with blades of the first propeller to change a setting thereof. | 01-16-2014 |
20140023505 | DEVICE FOR THE BLIND COUPLING OF FLUIDIC, ELECTRICAL OR SIMILAR SUPPLIES, TO A RECEIVING CONTROL MECHANISM - The device ( | 01-23-2014 |
20140294585 | TURBO ENGINE WITH PROPELLER(S) FOR AN AIRCRAFT WITH A SYSTEM FOR CHANGING THE PITCH OF THE PROPELLER - A turbo engine includes a system for changing a pitch of blades of a propeller, the system including an annular fluid cylinder with a linear drive and a link mechanism linking the cylinder to the blades of the propeller to change an orientation of the propeller. The annular cylinder of the system can be rigidly mounted on a fixed housing supporting the propeller and internal to it, unlike the blades mounted in an external rotating hub of the propeller, and the link mechanism includes a displacement transfer bearing fixed, on one side, to the mobile part of the cylinder and cooperating, on the other side, with a mechanism linking to the blades of the rotating hub of the propeller. | 10-02-2014 |
20150047369 | FIXED TURBINE ENGINE RECEIVER PART COMPRISING AN ASSEMBLY FOR HOLDING ANCILLARY SYSTEMS IN POSITION INSIDE A FIXED HOLLOW SHAFT - The invention relates to a fixed turbine engine receiver part comprising a fixed hollow shaft for carrying ancillary systems of a turbine engine, centered on the turbine engine axis, turbine engine ancillary systems, an assembly for holding ancillary systems in position situated inside the fixed hollow shaft. The assembly for holding ancillary systems in position comprises at least one first ancillary system support ring, having an axis substantially parallel with the turbine engine axis, a first distance sleeve for holding the first ancillary system support ring in position, having an axis substantially parallel with the turbine engine axis, the first distance sleeve bearing against the first support ring, such that the first support ring comprises a plurality of mutually separated through holes, each through hole defining a passage for at least one ancillary system, each through hole being traversed by at least one of the ancillary systems of the turbine engine. | 02-19-2015 |