Patent application number | Description | Published |
20090255271 | STRUCTURAL NACELLE - The present invention relates, on the one hand, to a nacelle ( | 10-15-2009 |
20100171319 | DEVICE FOR LOCKING AN OPENING PART OF A JET ENGINE NACELLE WITH RESPECT TO A FIXED PART, AND NACELLE EQUIPPED WITH SUCH A DEVICE - This device for locking an opening part ( | 07-08-2010 |
20100218480 | ACTUATOR FOR AN AIRCRAFT NACELLE MOBILE STRUCTURE, AND NACELLE COMPRISING AT LEAST ONE SUCH ACTUATOR - This actuator for an aircraft engine nacelle mobile structure ( | 09-02-2010 |
20100287910 | NACELLE WITH SIMPLIFIED COWLING ARRANGEMENT - The invention relates to a nacelle ( | 11-18-2010 |
20100327110 | GUIDING SYSTEM FOR AIRCRAFT NACELLE MAINTENANCE - The invention relates to a nacelle ( | 12-30-2010 |
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 |
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 |
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 |
20140286764 | COMPOSITE PANEL HAVING A BUILT-IN SAMPLING SCOOP - A composite panel includes an inner skin and an outer skin and has an opening for receiving a sampling scoop, which forms a channel and the sampling opening of which is in communication with the outer skin. In particular, the outer skin is shaped such that, at the opening, same forms at least a portion of a flow surface of the sampling scoop. | 09-25-2014 |
20140341744 | CELLULAR ACOUSTIC STRUCTURE FOR A TURBOJET ENGINE AND TURBOJET ENGINE INCORPORATING AT LEAST ONE SUCH STRUCTURE - A cellular acoustic structure for a turbojet engine includes a closed wall. The closed wall includes at least two faces having acoustically transparent areas and acoustic reflective areas. The closed wall is filled with a plurality of cells, and the acoustic reflective areas are disposed within the closed wall so that an acoustic path of aerial sound vibrations travels through the acoustically transparent areas, penetrates inside the cells and reflects on the acoustic reflective areas. In particular, the acoustic path in some of the cells has a depth greater than a half of the thickness of the cellular acoustic structure. | 11-20-2014 |
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 |