Patent application number | Description | Published |
20090084893 | PYLON FOR SUSPENDING AN ENGINE BENEATH AN AIRCRAFT WING | 04-02-2009 |
20090184198 | CONNECTING A PROPULSION SYSTEM TO A STRUCTURAL ELEMENT OF AN AIRCRAFT - An aircraft propulsion system ( | 07-23-2009 |
20090189014 | ATTACHMENT OF A MULTIFLOW TURBOJET ENGINE TO AN AIRCRAFT - The invention relates to the suspension of a multi-flow turbojet engine provided with an intermediate casing and an exhaust casing from a pylon that can be attached to the structure of an aircraft, comprising forward means of attachment between the hub of the intermediate casing and said pylon and a rear means of attachment between the exhaust casing and the pylon. This suspension is one which also comprises a means of connection rigidly connecting the intermediate casing to the pylon, and is one wherein the rear means of attachment comprises a means such as an actuator for compensating for the variations in diameter of the exhaust casing so as to keep the axis of the exhaust casing coaxial with the axis of the intermediate casing through the various phases of flight of the aircraft. | 07-30-2009 |
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 |
20110168837 | AIRCRAFT PROPULSION SYSTEM - An aircraft propulsion system including a bypass turbojet engine surrounded by a nacelle together with a mechanism attaching the engine to a pylon of an aircraft. The nacelle includes an inner structure forming a body of revolution including a rigid framework formed by an upstream annular frame fastened to an intermediate casing of the engine, a downstream annular frame supporting the exhaust casing of the engine, and longitudinal arms connecting the frames together, the annular downstream frame being fastened to the pylon by a flexible or hinged suspension mechanism. | 07-14-2011 |
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 |
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 |
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 |
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 |
20120288358 | CONTRA-ROTATING PROPELLER SYSTEM FOR AN AIRCRAFT TURBINE ENGINE - A contra-rotating propeller system for an aircraft turbine engine, including a free power turbine including a first rotor and a second rotor contra-rotating relative to the first rotor, a first contra-rotating propeller and a second contra-rotating propeller to be rotated about a longitudinal axis of the propeller system relative to a stator of the system, and a mechanical transmission device. The mechanical transmission system is provided between the first propeller and the second propeller. | 11-15-2012 |
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 |
20130032681 | BRACKET AND METHOD AND TOOLING FOR ITS PRODUCTION - A fitting including at least one composite material bracket with two flat segments forming an angle less than 180° on an inside of the bracket and an angle greater than 180° on an outside of the bracket, together with a stiffener extending on the inside of the bracket between the two flat segments is disclosed. The bracket presents a slot crossing a straight line between the two flat segments, the slot extending into the two flat segments. The stiffener is folded in register with the slot and includes tabs fastened to each of the two flat segments. | 02-07-2013 |
20130087635 | AIR INLET DUCT FOR A TURBOJET NACELLE - An air inlet duct and method for producing such for a turbojet nacelle, the air inlet duct including an upstream annular lip and a downstream outer annular structure. The upstream annular lip and the downstream outer annular structure are formed as a one-piece part made from composite material and the upstream lip is covered with a metal layer formed by electro-deposition or plastic forming. A turbofan engine can include such an air inlet duct. | 04-11-2013 |
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 |
20130133977 | ACOUSTIC PANEL FOR A TURBOJET ENGINE NACELLE, WITH IN-BUILT FASTENERS - An acoustic panel is provided that includes at least one cellular core arranged between at least an internal skin and an external skin, wherein the external skin incorporates at least one fastener able to collaborate in a disconnectable fashion with a complementary fastener associated with a structure to which it is to be attached. | 05-30-2013 |
20130186056 | GAS TURBINE ENGINE COMPRISING MEANS FOR AXIALLY RETAINING A FAN OF THE ENGINE - A gas turbine engine including: a casing in which is mounted at least one shaft for driving a fan solidly connected to a driving drum including blades to compress an airflow moving from upstream to downstream in the engine; and an axial retention mechanism, on standby, solidly connected to the casing and arranged to come into contact with the driving drum such as to prevent axial movement of the drum in event of breakage of the driving shaft. | 07-25-2013 |
20130202425 | Turbojet engine case, notably intermediate case - The present invention relates to an annular case ( | 08-08-2013 |
20130202449 | AXISYMMETRIC PART FOR AN AVIATION TURBINE ENGINE ROTOR - A link part for a turbine engine, in particular such as a turbojet, the link part being mounted between a fan cone and a fan disk supporting fan blades, the link part having an annular wall pierced by a plurality of orifices, each for receiving a fastener member and terminated by a substantially perpendicular rim having an outer surface that provides an aerodynamic extension of the fan between an outer surface of the fan cone and an outer surface of a fan blade platform, the annular wall being made of a first material that is composite and is provided on an inner surface of the rim with a ring made of a second material that is different from the first and that is suitable for radially retaining the fan blade platform. | 08-08-2013 |
20130227963 | ASSEMBLY FOR ATTACHING THE HANGERS FROM WHICH AN AIRCRAFT PROPULSION UNIT IS SUSPENDED - An assembly is designed to attach hangers from which an aircraft propulsion unit is suspended. The propulsion unit is intended to be suspended from a structural element of the aircraft. The propulsion unit includes a turbojet engine having a longitudinal axis and the attachment assembly having a clevis mount for attaching the hangers to a casing of the propulsion unit. The clevis mount is fixed to the casing by means designed to form a connection between the clevis mount and the casing at the external periphery of the casing. | 09-05-2013 |
20130258583 | COMPOSITE MATERIAL FADEC BOX SUPPORT - A device for protecting a computer of an aircraft turbine engine, the device comprising a box containing the computer and a cover covering the box, the box being supported by tabs forming integral portions of the box and maintaining a flow of air between the bottom of the box and a portion of the casing of the engine on which they are to come into secure contact via resilient studs, the box being made of a composite material. | 10-03-2013 |
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 |
20130280031 | THRUST REVERSER - A thrust reverser for the nacelle of a turboreactor includes at least one fixed front frame that can be mounted downstream of a fan casing of the turboreactor and directly or indirectly supports at least one flow deviation vanes, in which at least part of the flow deviation vanes can be detached from the front frame and moved in translation independently therefrom when a maintenance operation is being carried out on the reverser. | 10-24-2013 |
20130327058 | DEVICE FOR SUSPENDING A TURBOJET ENGINE - A turbojet is suspended by attachments including hinged links. An attachment includes a support including three branches with passages through which a pin passes, the pin being oriented generally parallel to a direction that is tangential to a casing and being hinged to a central branch of the support by a ball joint. | 12-12-2013 |
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 |
20150021455 | TURBINE ENGINE SUPPORT PART OF HYBRID STRUCTURE - A turbine engine support part including a main structure made of composite material and a reinforcing secondary structure made of metal and integrated in the main structure, the secondary structure presenting a geometrical shape and dimensions configured to impart mechanical strength to the support part in event of the main structure being destroyed. | 01-22-2015 |