Patent application number | Description | Published |
20100252689 | AIRCRAFT NACELLE GUIDANCE SYSTEM INSTALLATION - The present invention relates to a turbojet engine nacelle ( | 10-07-2010 |
20100281849 | DOOR-TYPE THRUST REVERSER FOR A JET ENGINE - This thrust reverser comprises at least two doors ( | 11-11-2010 |
20100314501 | LOCKING SYSTEM FOR AIR INTAKE STRUCTURE FOR TURBOJET ENGINE NACELLE - The invention relates to a nacelle for a turbojet engine that includes an air intake structure ( | 12-16-2010 |
20100320316 | AIR INTAKE FOR AIRCRAFT NACELLE, AND PROPULSION ASSEMBLY INCLUDING SUCH AIR INTAKE - The invention relates to an air intake for an aircraft nacelle that comprises a shroud ( | 12-23-2010 |
20110011981 | AIR INTAKE STRUCTURE FOR AN AIRCRAFT NACELLE - The invention relates to an air intake structure capable of being mounted upstream of a central structure of a nacelle for an aircraft engine, the said air intake structure comprising: —an external wall incorporating a lip, —an upstream partition ( | 01-20-2011 |
20110014044 | LOCKING SYSTEM FOR AIR INTAKE STRUCTURE FOR TURBOJET ENGINE NACELLE - The invention relates to a nacelle for a turbojet engine that comprises an air intake structure ( | 01-20-2011 |
20110030338 | BYPASS TURBOJET ENGINE NACELLE - The invention relates to a bypass turbojet engine nacelle comprising a downstream section equipped with a thrust reverser device comprising a moving cowl ( | 02-10-2011 |
20110033286 | NACELLE FOR TURBOJET ENGINE - The present invention relates to a nacelle for a turbojet engine comprising an air intake structure able to channel an airflow towards a fan of the turbojet engine, and a middle structure comprising a casing (9) intended to surround the said fan and to which the air intake structure is attached, the latter structure having at least one peripheral interior panel (41), characterized in that the casing extends around the fan more or less as far as the fan blades (8), the air intake structure being connected to the casing by the interior panel by means of at least one structural peripheral flange (15) capable of providing containment for at least one blade should the latter break off. | 02-10-2011 |
20110068222 | PROPULSION UNIT FOR AN AIRCRAFT AND AIR INTAKE STRUCTURE FOR SUCH A UNIT - This propulsion unit for an aircraft comprises: a fan ( | 03-24-2011 |
20110085897 | CASING COMPRISING A PERIPHERAL SHROUD FOR A TURBOMACHINE ROTOR - The present invention relates to a casing ( | 04-14-2011 |
20110103935 | AIRCRAFT ENGINE NACELLE AIR INTAKE ASSEMBLY - This aircraft engine nacelle air intake assembly comprises an air intake structure comprising an air intake lip ( | 05-05-2011 |
20110108357 | ACOUSTIC PANEL FOR AN EJECTOR NOZZLE - The invention relates to an acoustic panel ( | 05-12-2011 |
20110131945 | ASSEMBLY OF COMPONENTS CONNECTED BY A DEVICE THAT MAINTAINS THE INTEGRITY OF THE SURFACE OF ONE OF THE COMPONENTS - This assembly comprises a first component ( | 06-09-2011 |
20110133025 | ACOUSTIC ATTENUATION PANEL FOR AIRCRAFT FOR ENGINE NACELLE - This acoustic attenuation panel for an aircraft engine nacelle comprises a structuring skin ( | 06-09-2011 |
20110133035 | METHOD FOR MAKING DEICING SYSTEM ON A NACELLE PANEL - The invention relates to a method for making a deicing system on a panel ( | 06-09-2011 |
20110174899 | NACELLE WITH A VARIABLE NOZZLE SECTION - The invention relates to a nacelle that comprises a fixed structure ( | 07-21-2011 |
20110174919 | STRUT DESIGNED TO SUPPORT AN AIRCRAFT TURBOJET ENGINE, AND NACELLE COMPRISING SUCH A STRUT - This strut ( | 07-21-2011 |
20110182727 | TURBOJET ENGINE NACELLE - The invention relates to a nacelle ( | 07-28-2011 |
20110192134 | AIR INTAKE STRUCTURE FOR A TURBINE ENGINE NACELLE - The invention relates to an air intake structure ( | 08-11-2011 |
20110214405 | NACELLE AIR INTAKE STRUCTURE - The invention relates to a nacelle comprising an air intake structure ( | 09-08-2011 |
20110219783 | TURBOJET ENGINE NACELLE WITH TRANSLATABLE UPSTREAM COWL - Turbojet engine nacelle ( | 09-15-2011 |
20110220218 | TURBOJET ENGINE NACELLE - The invention relates to a nacelle ( | 09-15-2011 |
20110240137 | OVERPRESSURE HATCH INTENDED TO BE MOUNTED ON A WALL OF A TURBOJET ENGINE NACELLE - The invention relates to an overpressure hatch ( | 10-06-2011 |
20110254196 | METHOD FOR MAKING AN ACOUSTIC ATTENTUATION PANEL, IN PARTICULAR FOR AERONAUTICS - The invention relates to a method for making an acoustic attenuation panel, comprising using at least one foam block ( | 10-20-2011 |
20110284095 | TURBOJET ENGINE NACELLE - The invention relates to a turbojet engine nacelle ( | 11-24-2011 |
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 |
20110308257 | ATTACHMENT STRUCTURE FOR A TURBOJET ENGINE - The present invention relates to an attachment structure ( | 12-22-2011 |
20120006000 | BENT CONNECTING ROD FITTED WITH AT LEAST ONE SELF-ALIGNING MEANS - The invention relates to a bent connecting rod ( | 01-12-2012 |
20120067024 | THRUST REVERSER FOR A DUAL-FLOW TURBINE ENGINE NACELLE - The invention relates to a thrust reverser ( | 03-22-2012 |
20120067975 | THRUST REVERSING DEVICE - The invention relates to a thrust reversing device ( | 03-22-2012 |
20120096730 | DEVICE FOR CENTERING AN AIR INLET STRUCTURE ON A CENTRAL STRUCTURE OF A NACELLE - The invention relates to a device ( | 04-26-2012 |
20120138707 | THRUST REVERSAL DEVICE - The present invention relates to a thrust reversal device ( | 06-07-2012 |
20120160933 | STRUCTURING ASSEMBLY FOR AN EXHAUST NOZZLE - The invention relates to a structuring assembly ( | 06-28-2012 |
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 |
20130062433 | NACELLE FOR AN AIRCRAFT ENGINE WITH VARIABLE CROSS-SECTION NOZZLE - A nacelle for an aircraft engine is provided that includes a thrust reverser cowling slideably mounted between a direct jet position and a reversed jet position, an outlet jet pipe nozzle with variable cross-section positioned in a downstream extension of the reverser cowling, and means for respectively actuating the cowling and the nozzle. The nozzle is slideably mounted on the thrust reverser cowling, and the means includes at least one actuator for actuating said thrust reverser cowling, at least one driving pinion rotatably mounted on a fixed structure of said nacelle, and at least one rack for actuating the nozzle, secured to the nozzle and meshing with the driving pinion when the thrust reverser cowling is in the direct jet position, and escaping from this pinion when said reverser cowling is in the reversed jet position. | 03-14-2013 |
20130062434 | ARRANGEMENT OF THRUST REVERSER FLAP LINK RODS ON THE INTERNAL FIXED STRUCTURE OF A TURBOJET ENGINE NACELLE - An arrangement is provided that includes a thrust reverser flap link rod on an internal fixed structure of a turbojet engine nacelle. The link rod is connected to the internal fixed structure by an elastic means that is a spring. | 03-14-2013 |
20130075493 | AIRPLANE JET ENGINE THRUST REVERSER HAVING GRATINGS OR CASCADES - A cascade thrust reverser for an airplane dual flow jet engine nacelle is provided that includes a front frame holding a plurality of cascades, a cowling slidably mounted between a direct jet position and a reverse jet position. The cowl includes a substantially annular diaphragm that is placed edge-to-edge with the front frame and radially inside said cascades when said cowl is located in the direct jet position. Thrust reversal flaps are pivotably mounted onto the diaphragm, and cylinders for actuating the cowl are also provided. Upstream ends of the cylinders are mounted on a stationary portion of the nacelle, and the downstream ends of the cylinders are mounted on an upstream edge of the diaphragm. | 03-28-2013 |
20130091825 | TURBOJET ENGINE NACELLE INCLUDING A DEVICE FOR ABSORBING CIRCUMFERENTIAL STRESSES - A nacelle for a turbojet engine of an aircraft is provided that includes a fan case, an internal structure positioned upstream from the fan case, and a thrust reverser positioned downstream from the fan case. The thrust reverser includes a cowl delimiting an external line (LE) and including two removable half cowls. A device for absorbing circumferential stresses are shaped so as to lock the half cowls in the closed position when it occupies a locking configuration on the one hand and for allowing the opening of the half cowls when it occupies an unlocking configuration on the other hand. The stress absorbing device is positioned under an upstream portion of a pylon and is exclusively attached to the half cowls in order to allow the opening of the two half cowls independently of the opening/closing of an external fan cowl. | 04-18-2013 |
20130126638 | THRUST REVERSER HAVING AN AERODYNAMIC COUPLING FOR A FRONT FRAME - A thrust reversal device for a turbojet engine nacelle is provided that includes a deflection means and at least one cowl moveable relative to at least one fixed structure including at least one at least partly peripheral front frame and equipped with means for connection to a corresponding upstream portion. The front frame has a deflection edge having an upstream extension forming a deformable flap intended to become an aerodynamic interface with the corresponding upstream portion to which is attached the front frame, and in that a portion of the moveable cowl is conformed so as to, in the closing position, interface with said upstream attachment portion by forcing withdrawal of the deformable flap. | 05-23-2013 |
20130236294 | TURBOJET ENGINE NACELLE WITH VARIABLE VENTILATION OUTLET CROSS SECTION - A turbojet engine nacelle includes a rear section having an internal structure. The internal structure surrounds a rear part of an engine compartment and delimits, with an ejection jet pipe, an outlet cross section for the ventilation of the engine compartment. The engine nacelle includes a moving element associated with a corresponding controller. The moving element is able to move between a withdrawn position in which the outlet cross section for ventilation is at a maximum and an engaged position in which the moving element partially reduces the outlet cross section for ventilation by comparison with the retracted position. The controller is capable of moving the moving element between the retracted and engaged positions. | 09-12-2013 |
20130263600 | ASSEMBLY INCLUDING A REVERSE THRUST DEVICE AND SYSTEM FOR ACTUATING SAID DEVICE - A reverse thrust device and a system for actuating the reverse thrust device is provided by the present disclosure. The device includes at least one cowl that is translatably mounted in a direction substantially parallel to a longitudinal axis of a nacelle. The actuation system includes an actuation means that is capable of activating translational and rotational movement of the cowl and a panel of a nozzle. The actuation system also includes a downstream locking means for the nozzle and the cowl. The downstream locking means includes at least two reversible states, one of the states being a locked state in which the downstream locking means is suitable for locking the panel of the nozzle into a position for varying the section for outputting the nozzle with the cowl. | 10-10-2013 |
20130266423 | SELF-MOUNTED CASCADE FOR A THRUST REVERSER - The present disclosure relates to a self-mounted cascade for a thrust reverser of an airplane jet engine nacelle. The cascade includes an upstream portion and an opposite downstream portion, along with respective connection means so that two adjacent cascades are directly connected to one another only in the respective downstream portions by downstream connection means thereof. The downstream portion corresponds to an area extending from a downstream side edge over a length less than or equal to N times the length of the last cavity located along said downstream side edge, where N is less than 3. The present disclosure is of use in the field of airplane jet engine nacelles. | 10-10-2013 |
20130292489 | THRUST REVERSER HAVING A LOCKABLE VARIABLE NOZZLE SECTION - The present disclosure relates to a thrust reverser including at least one translatably movable cowl capable of alternately shifting between a closed position in which same ensures the aerodynamic continuity of the nacelle and which covers the deflecting means, and an open position in which same opens a passage in the nacelle and uncovers the deflecting means, said thrust reverser likewise including at least one variable nozzle section arranged in the extension of the movable thrust-reversing cowl and provided with at least one locking means capable of engaging with a complementary locking means of the movable reversing cowl so as to optionally mechanically link the movable nozzle section of the movable reversing cowl. | 11-07-2013 |
20140326536 | STRUCTURAL ACOUSTIC ATTENUATION PANEL - An acoustic attenuation panel includes a resistive skin having acoustic holes, a solid skin and an acoustic structure. The acoustic structure includes a sound-absorbing material and is arranged between the resistive skin and the solid skin. In particular, the solid skin is structural and forms a transverse spacer between the solid skin and the resistive skin. | 11-06-2014 |
20150044413 | METHOD FOR MANUFACTURING A COMPOSITE SANDWICH PANEL WITH HONEYCOMB CORE - The present disclosure provides a method for manufacturing a composite sandwich panel with an alveolar core. The alveolar core exhibits a plurality of cells each delimited by at least one wall formed from at least one partition. In particular, a portion of the partition is integrated to a support skin of the composite sandwich panel during a resin molding step. | 02-12-2015 |
20150059967 | METHOD FOR MANUFACTURING A COMPOSITE SKIN FORMING A NON-STRIPPABLE SHROUD - The present disclosure relates to a method for producing a composite skin forming a non-strippable rotationally-symmetrical collar. The method includes draping fabric plies over a mold, providing a separating line on the draped fabric plies, post-impregnating the draped plies with a resin, curing the resin, removing the resulting skin from the mold using a separating line, and, subsequently, splinting two edges of the skin defined by the separating line. | 03-05-2015 |