Patent application number | Description | Published |
20130069281 | DEVICE FOR MANUFACTURING A COMPOSITE PART BY RESIN INJECTION MOULDING - A device for manufacturing a part in composite material by resin transfer moulding and method is provided according to the present disclosure. The device includes a manufacturing mould in which at least one preform is intended to be arranged of the part intended to be impregnated with resin during a resin transfer process. The mould is subdivided into a die and at least one movable structural element intended to be indexed on the die to form an assembly, the assembly forming a cavity corresponding to a shape of the part to be manufactured. The mould is associated with at least one positioning frame having a low coefficient of thermal expansion in at least one dimension, the positioning frame being designed to allow the indexing and holding in position of the at least one movable structural element, corresponding to at least one singularity, on the die. | 03-21-2013 |
20130079434 | PROCESS FOR MANUFACTURING A PART MADE OF A COMPOSITE HAVING A HOLLOW CORE - A method for manufacturing a part in composite material with a hollow core is provided that includes applying at least one adhesive layer on an open surface of the hollow core. The adhesive layer is a blocking polymerizable adhesive layer having, after polymerization, sealing properties relatively to a resin and capable of preventing its diffusion towards an inside of the hollow core. Subsequently, the blocking adhesive layer is polymerized so as to achieve sealing of the hollow core. Additionally, various parts manufactured according to the methods of the present disclosure are also provided. | 03-28-2013 |
20130121814 | TURBOJET ENGINE NACELLE - A nacelle for a turbojet engine is provided that includes an air intake upstream from the turbojet engine, a middle section intended to surround a fan of the turbojet engine and its case, and a downstream section. The middle section is made from at least one aerostructure capable of ensuring external aerodynamic continuity of the nacelle, and the aerostructure is rigidly bound, so as to be able to be taken apart, to at least one surrounding fixed structure. | 05-16-2013 |
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 |
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 |
20130230391 | NACELLE FOR AN AIRCRAFT BYPASS TURBOJET ENGINE - The invention relates to a nacelle ( | 09-05-2013 |
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 |
20140061332 | THRUST REVERSER FOR AN AIRCRAFT JET ENGINE - An assembly includes a suspension pylon and a thrust reverser which has vanes for deflecting flow and a cowl able to move between an open position and a closed position by an actuator. The thrust reverser further includes rails able to slide in slideways. In particular, the actuator is disposed in line with a corresponding rail. The actuator may be an actuator having a rotating nut connected to an endless screw or an actuator suitable for pulling on the corresponding rail or on the corresponding slideway. | 03-06-2014 |
20140131479 | AIRCRAFT TURBOJET ENGINE THRUST REVERSER WITH A LOWER NUMBER OF ACTUATORS - This cascade-type thrust reverser with one-piece moving cowl includes rails able to slide in guideways positioned on each side of a suspension pylon. This thrust reverser includes just two actuators positioned near the rails and able to cause this cowl to slide on the guideways between its direct-jet and reverse-jet positions. It also has means capable of compensating for forces that have a tendency to misalign the rails with respect to the guideways, thus preventing them from jamming in one another. | 05-15-2014 |
20140131480 | THRUST REVERSER DEVICE WITHOUT A CONTROL ROD IN THE STREAM - A jet engine nacelle has one thrust reverser device which includes a deflection means and one cowl translatable in a direction substantially parallel to a longitudinal axis of the nacelle. The cowl can translate between a closed position and an open position. In the open position, the cowl ensures the aerodynamic continuity of the nacelle and covers the deflection means. In the open position, the cowl opens a passage into the nacelle and uncovers the deflection means. The thrust reverser device moreover includes one blocking flap pivotably mounted by one end attached to a rear portion of the deflection means, and slidingly connected to the moving cowl. The pivoting end is also translatably connected to the rear portion of the deflection means. | 05-15-2014 |
20140140830 | INNER STRUCTURE FOR AN AIRCRAFT NACELLE - An inner structure for a nacelle for an aircraft turbofan includes a plurality of active and passive movable portions. Each active movable portion can drive adjacent passive movable portions such that the inner structure has a nominal first position, a second position and a third position. In the second position, the active movable portions project beyond by the passive movable portions toward the outside of the inner structure after the active mobile portions have driven the passive mobile portions. In the third position, the active movable portions project beyond the passive movable portions toward the inside of the inner structure after the active mobile portions have driven the passive mobile portions. The present disclosure also relates to a nacelle having an outer structure and such an inner structure. | 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 |
20140234090 | REAR NACELLE ASSEMBLY FOR A TURBOJET ENGINE - A rear nacelle assembly for turbojet engine includes an inner structure surrounding a downstream portion of the turbojet engine. In particular, the inner structure is movable in rotation between an operating position in which it forms a downstream fairing and defines an annular stream of cold air with a thrust reverser cowl, and a maintenance position in which the inner structure moves away from the downstream portion. A suspension pylon is further provided to mount the thrust reverser cowl and the inner structure. The thrust reverser cowl slides between an opening position clearing air flow deviation grids and a closing position recovering the air flow deviation grids. Moreover, the thrust reverser cowl is mounted on the suspension pylon by a pivot connection sliding around a main axis, and the inner structure is mounted on the suspension pylon by a pivot connection around the main axis. | 08-21-2014 |
20150083823 | COUPLING AND UNCOUPLING MECHANISM FOR AN ONBOARD DEVICE OF A TURBOJET ENGINE NACELLE - A mechanism for coupling and uncoupling a motor inlet shaft and an outlet shaft, in particular, the inlet shaft is mounted in rotation on a front frame, and the outlet shaft is mounted in rotation on a rear frame. The outlet shaft rotates an outlet pinion, and the rear frame is slidably mounted to translate between a forward compact position and a backward deployed position. The mechanism includes a coupler, and first and second lockers to couple or uncouple the inlet and outlet shafts according to the translation of the rear frame between the forward compact position and the backward deployed position. The first locker locks in rotation the inlet shaft on the front frame, the second locker locks the outlet shaft on the rear frame. In particular, the second locker automatically locks the inlet and outlet shafts in rotation respectively, according to the displacement of the rear frame. | 03-26-2015 |