Patent application number | Description | Published |
20100146933 | NACELLE REAR ASSEMBLY FOR TURBOJET ENGINE - The invention relates to a nacelle rear assembly for a turbojet engine, that comprises: a hood, an inner structure in the shape of a sheath in which at least the rear portion ( | 06-17-2010 |
20100327110 | GUIDING SYSTEM FOR AIRCRAFT NACELLE MAINTENANCE - The invention relates to a nacelle ( | 12-30-2010 |
20110139540 | NOISE REDUCTION DEVICE FOR TURBOJET NACELLE WITH MOBILE CHEVRONS, AND ASSOCIATED NACELLE - The invention relates to a turbojet nacelle ( | 06-16-2011 |
20110174919 | STRUT DESIGNED TO SUPPORT AN AIRCRAFT TURBOJET ENGINE, AND NACELLE COMPRISING SUCH A STRUT - This strut ( | 07-21-2011 |
20110284660 | THRUST REVERSER FOR A TURBOFAN ENGINE NACELLE - The invention relates to a thrust reverser for a turbofan engine nacelle including a stationary portion ( | 11-24-2011 |
20110284686 | SUSPENSION ASSEMBLY FOR AN AIRCRAFT TURBOJET ENGINE - The invention relates to a suspension assembly for an aircraft turbojet engine ( | 11-24-2011 |
20120001026 | DE-ICING DEVICE, IN PARTICULAR FOR AN AIRCRAFT NACELLE - The invention relates to a de-icing device ( | 01-05-2012 |
20120193448 | REVERSE THRUST DEVICE - The invention relates to a jet engine nacelle reverse thrust device ( | 08-02-2012 |
20120217320 | THRUST INVERTER - The present invention relates to a thrust inverter for a turbojet engine nacelle ( | 08-30-2012 |
20120217372 | ASSEMBLY FOR HOLDING THE INTERFACE OF STATIONARY OUTER STRUCTURE OF A NACELLE AND HOUSING OF A JET ENGINE - The invention relates to an assembly for holding the interface of a stationary outer structure ( | 08-30-2012 |
20120228403 | ASSEMBLY FOR AN AIRCRAFT TURBOJET ENGINE COMPRISING A THRUST REVERSAL COWL - The invention relates to an assembly for a turbojet engine which includes a pylon ( | 09-13-2012 |
20120247571 | JET ENGINE NACELLE REAR ASSEMBLY - The present invention relates to a nacelle rear assembly ( | 10-04-2012 |
20130009005 | REVERSE THRUST DEVICE - The invention relates to a reverse thrust device including a stationary upstream structure including a front frame ( | 01-10-2013 |
20130228635 | TURBOJET ENGINE NACELLE - A bypass turbojet engine nacelle equipped with a thrust reverser device is provided that includes a cowl with translational mobility and a diversion means supported by a front frame upstream of the cowl. A variable-geometry jet pipe nozzle is mounted at a downstream end of the cowl and is translatable in a direction substantially parallel to a longitudinal axis of the nacelle towards at least one position that causes a variation in its cross-section. At least part of the front frame, the diversion means, and the jet pipe nozzle form an assembly having translational mobility in a direction substantially parallel to a longitudinal axis of the nacelle in a downstream direction of the nacelle towards a position that causes a variation in the cross-section of the jet pipe nozzle, the cowl being in the closed position during that movement of said assembly. | 09-05-2013 |
20130243589 | TURBOJET ENGINE NACELLE REINFORCING STRUCTURE - A turbojet engine nacelle includes a fixed structure, which has a fan casing of the turbojet engine and a front frame mounted downstream of the fan casing and directly or indirectly supporting cascade vanes. The front frame is able to collaborate with a thrust reverser cowling sliding between a closed position covering the flow-diverting means and an open position exposing this flow-diverting means. At least one reinforcing structure of the engine nacelle transmits load between the fan casing and the front frame. The reinforcing structure extends along the longitudinal axis of the nacelle and supports a third line of defense and/or an inhibiting device between the front frame and the thrust reverser cowling. | 09-19-2013 |
20140131515 | AIRCRAFT TURBOJET ENGINE THRUST REVERSER WITH A REDUCED NUMBER OF LATCHES - A thrust reverser with grids includes a jet engine pylon, a one piece cowl either directly or indirectly slidably mounted on the jet engine pylon between a direct jet position and a reverse jet position, and a system for locking this cowl on a beam. The system has a single tertiary lock, which is positioned on one side of the jet engine pylon being capable of locking a corresponding upper edge of the cowl. In addition, the tertiary lock includes a locker to lock the cowl, a blocker for blocking the locker, and a position detector in order to detect the position of the locker. The system further includes another detector to detect proper closing of the other upper edge of the cowl. | 05-15-2014 |
20140137541 | AIRCRAFT PROPULSION UNIT INCLUDING AT LEAST ONE TURBOJET ENGINE AND A NACELLE - The present disclosure relates to a nacelle for a dual-flow turbojet engine includes a cold airstream having a non-constant cross-section over the periphery of the nacelle, such that at least one flap is radially offset with respect to the central axis of the turbojet engine, relative to the adjacent flaps. The system for driving the radially offset flaps is suitable for ensuring that the kinematics of the flaps are offset relative to the kinematics of the flaps mounted along the remainder of the periphery of the airstream. | 05-22-2014 |
20140216846 | METHOD OF MANUFACTURING A SOUND ABSORBING PANEL - The present disclosure provides a method of manufacturing a sound absorbing panel in which a reflective wall on one of faces of a set of sound absorbing cells. In particular, a passage on a portion of a thickness (E) of the set of sound absorbing cells is formed on an opposite face of the one of the faces, while the passage forming a main channel for a communication between sound absorbing cells and for a circulation of a de-icing fluid. | 08-07-2014 |
20140245743 | DOUBLE-ACTING LINEAR ACTUATOR - The present disclosure relates to a double-acting linear actuator for moving an inner part and an outer part of a cowl relative to a fixed frame. The linear actuator includes a first tubular body housing a first drive shaft and a second tubular body housing a second drive shaft. In particular, the first and second tubular bodies are mounted in series by the second drive shaft which is mounted on the first tubular body. The second drive shaft translates the second tubular body relative to the first tubular body when a lock of the first tubular body is in a locked position, and the first drive shaft translates both the first tubular and second tubular bodies when the lock is in an unlocked position. | 09-04-2014 |
20140291066 | AIR INTAKE STRUCTURE FOR TURBOJET ENGINE NACELLE - An air intake structure for a turbojet engine nacelle includes a substantially annular main structure having an internal wall, an external wall and an air intake lip structure connecting the external and internal walls upstream. The air intake structure also includes a first acoustic attenuation structure which has a holed acoustic skin, a cellular core and a solid rear skin with which the internal wall is equipped, and a second acoustic attenuation structure having a similar architecture fitted to a part of the air intake lip substantially near a junction with the internal wall. The rear skin of the first acoustic attenuation structure is aligned with the rear skin of the second acoustic attenuation structure, both of rear skins being structural. | 10-02-2014 |
20140319243 | REVERSER HAVING MOVABLE CASCADES, AND TRANSLATABLY VARIABLE NOZZLE - The thrust reverser includes a reverser cowl of which a downstream part of the reverser cowl forms a jet nozzle, cascade vanes fixed upstream from the reverser cowl, thrust reverser flaps, and an actuator. The thrust reverser is translatable under an effect of the actuator between a folded position of the thrust reverser flaps for operation of the nacelle in a direct jet mode, and a deployed position of the thrust reverser flaps for operation of the nacelle in a reverse jet mode. In particular, the stretching of the actuator results in causing a variation in a nozzle section of the jet nozzle as long as the stretching is below a predetermined value, and exposing the cascade vanes and deploying the thrust reverser flaps so as to perform the reverse jet mode beyond the predetermined value. | 10-30-2014 |
20140369812 | TURBINE ENGINE NACELLE FITTED WITH A HEAT EXCHANGER - A nacelle of a turbine engine includes an external cowling, an internal cowling, and a heat exchanger associated with at least one circulation duct for a fluid. In particular, the circulation duct forms a recirculation loop through the heat exchanger, and the recirculation loop includes at least one circulation area extending at least partially along the external cowling in contact with a wall of the external cowling so as to allow exchange of heat by conduction with the air outside the nacelle. | 12-18-2014 |
20140369829 | FLATTENED NACELLE OF A TURBOJET ENGINE - A nacelle includes an outer structure provided with a thrust reverser and a front frame, a movable cowl, and an inner structure covering a downstream section of a turbojet engine. The outer structure and the inner structure define a flow stream of an air flow. In particular, the connection of the front frame and diversion cascade of the thrust reverser which is mounted on a reduced transverse section area of the movable cowl is centered on an axis offset relative to an axis on which the connection of the front frame and the diversion cascade mounted on the remainder of the periphery of the movable cowl is centered. | 12-18-2014 |