| Patent application number | Description | Published |
|---|
| 20080202847 | Method For Attenuating the Noise of a Turbofan - The invention concerns a turbofan, characterized in that edge of the outlet ( | 08-28-2008 |
| 20080206044 | NOISE REDUCTION ASSEMBLY FOR AIRCRAFT TURBOJET - A noise reduction assembly located at a junction plane between an air intake structure and a fan casing of an aircraft turbojet has improved acoustic properties since the alternation of acoustic and non-acoustic zones is displaced or eliminated. In particular, the inner wall of the air intake structure includes a projecting part that extends towards the aft direction beyond the junction plane, in other words the flange of the fan casing. The projecting part may be sufficiently long so that its inner skin is continuous as far as the limit between the acoustic zone and the non-acoustic zone of the nacelle. | 08-28-2008 |
| 20080230651 | Turbofan Provided With a Pre-Cooler - The invention concerns a turbofan provided with a pre-cooler. The invention is characterized in that to evacuate the heated cool air stream ( | 09-25-2008 |
| 20080271431 | Turbojet Engine with Attenuated Jet Noise - According to the invention, a plurality of hatches ( | 11-06-2008 |
| 20090000305 | Dual Flow Turbine Engine Equipped with a Precooler - The invention concerns a precooler ( | 01-01-2009 |
| 20090007567 | Dual Flow Turbine Engine Equipped with a Precooler - The invention concerns a precooler ( | 01-08-2009 |
| 20090020647 | SYSTEM FOR DEICING AN AIR INLET COWL FOR A TURBINE ENGINE - According to the invention, a scaled articulation device ( | 01-22-2009 |
| 20090111370 | VENTILATING AIR INTAKE ARRANGEMENT WITH MOBILE CLOSING DEVICE - The invention concerns a ventilating air intake arrangement with mobile sealing device. The arrangement comprises at least one air passage channel ( | 04-30-2009 |
| 20090197031 | AIRCRAFT CONDUIT - The object of the invention is a pipe that is integrated into the aircraft piping, characterized in that it is produced from a composite material that comprises a fiber-reinforced geopolymer resin matrix. | 08-06-2009 |
| 20090253361 | VENTILATING AIR INTAKE ARRANGEMENT - The invention concerns an arrangement comprising at least one air passage channel ( | 10-08-2009 |
| 20090255589 | TURBINE ENGINE FOR AIRCRAFT - According to the invention, the internal wall of the air intake ( | 10-15-2009 |
| 20090290978 | TURBINE ENGINE FOR AIRCRAFT - According to the invention, the internal wall (5.1) of the air intake (2) and the housing (12.1) for the fan (3) are pieces of composite fibre/resin material, overlap-jointed at the ends thereof (5.1R) and (12.1A). | 11-26-2009 |
| 20090314899 | STRUCTURAL ELEMENT OF AN AIRCRAFT - A rear frame of an air intake of a nacelle of an aircraft, is made in part of composite material that is based on a fiber-reinforced geopolymer resin and includes at least one part ( | 12-24-2009 |
| 20100000227 | AIR INTAKE FOR AN AIRCRAFT TURBINE ENGINE - According to the invention, the air intake ( | 01-07-2010 |
| 20100087132 | Air Intake Arrangement for a Vehicle, in Particular an Aircraft - The arrangement of the invention includes mobile means for blocking an air passage channel (10) which are controlled by an aerodynamic surface (20) provided in said air passage channel (10) and capable of generating a lift force (P) under the action of the external air flow (F) flowing through said air passage channel (10). | 04-08-2010 |
| 20100089690 | METHOD FOR MAKING AN ACOUSTIC TREATMENT COATING AND COATING THUS OBTAINED - A process for the producing a coating for acoustic treatment relative to a leading edge such as an air intake of an aircraft nacelle, the coating including a reflective layer, an alveolar structure, and an acoustically resistive layer, includes: | 04-15-2010 |
| 20100116587 | ACOUSTIC PANEL - The invention relates to a panel for an acoustic treatment at the surface of an aircraft, that comprises from the outside to the inside an acoustically resistive porous layer, at least one cellular structure and a reflective or non-permissive layer, wherein the acoustically resistive porous layer includes, at the outer surface that may contact the aerodynamic flows of a sheet or foil, open areas ( | 05-13-2010 |
| 20100176250 | FAIRING FOR A PYLON VIA WHICH A TURBINE ENGINE IS SUSPENDED FROM A WING OF AN AIRCRAFT - Fairing for a pylon via which a turbine engine is suspended from a wing of an aircraft. According to the invention, the forward attachment ( | 07-15-2010 |
| 20100181420 | COATING FOR ACOUSTIC TREATMENT THAT INTEGRATES THE FUNCTION OF HOT-AIR TREATMENT OF FROST - The invention relates to a coating for acoustic treatment at the surface of an aircraft, in particular at the leading edge such as the air intake of an aircraft nacelle, said coating including an acoustically resistive layer ( | 07-22-2010 |
| 20100199629 | SYSTEME D'ANTI GIVRAGE ET DE DEGIVRAGE DE NACELLE DE MOTEUR D'AERONEF A TAPIS RESISTIF - A deicing and anti-icing system for an aircraft engine pod, including an air intake provided with a lip followed by an air intake tubular part, equipped with a first sound attenuating panel, including deicing means having at least one array of resistive heating elements embedded in an insulating material, the deicing means being in the form of a mat incorporating the resistive element in the thickness of the air intake lip. | 08-12-2010 |
| 20100200699 | SYSTEM FOR DEFROSTING THE LEADING EDGE SHEATH OF AN AIR INLET HOOD FOR A TURBOENGINE - The system for defrosting the leading edge sheath of an air intake hood for a turboengine comprises a hot pressure air supply duct ( | 08-12-2010 |
| 20100252685 | AIRCRAFT NACELLE INCLUDING AN OPTIMISED ICE TREATMENT SYSTEM - An aircraft nacelle includes a pipe, a peripheral wall, a lip connecting the pipe and peripheral wall and delimiting an air intake. A frost treatment system treats a zone extending along a longitudinal section of a point A at the peripheral wall at a point B at the pipe and includes a front frame delimiting with the lip a pipe circulating deicing hot air. An acoustic pipe coating includes a reflective layer, at least one alveolar structure, and at least one acoustically resistive structure. The front frame includes a junction zone with the lip and/or the pipe offset toward the nacelle front relative to B. Pipes inside the lip and the pipe convey hot air from the pipe to circularly arranged discharges corresponding to B. The pipes extend beyond the junction between the front frame and the lip and/or the pipe and are delimited by at least one isolating partition. | 10-07-2010 |
| 20100276548 | ACOUSTIC PROCESSING STRUCTURE PARTICULARLY ADAPTED TO THE AIR INLET OF AN AIRCRAFT NACELLE - An acoustic treatment structure related to a leading edge onto which an aerodynamic stream flows, in particular at an air intake of an aircraft nacelle, includes—from the outside to the inside—at least one acoustically resistive substructure ( | 11-04-2010 |
| 20100281880 | AIRCRAFT PROPULSION ASSEMBLY COMPRISING HOT AIR BLEED SYSTEMS - An aircraft propulsion unit includes a nacelle ( | 11-11-2010 |
| 20100294882 | AIRCRAFT LEADING EDGE - An aircraft leading edge, such as, for example, an air intake ( | 11-25-2010 |
| 20100301161 | ACOUSTIC COATING FOR AN AIRCRAFT INCORPORATING A FROST TREATMENT SYSTEM BY JOULE EFFECT - The invention relates to acoustic lining for an aircraft, which can cover a leading edge, such as an air inlet in the nacelle of a propulsion unit, said lining comprising: (i) from the inside outwards, a reflective layer ( | 12-02-2010 |
| 20100314082 | AIRCRAFT NACELLE INCLUDING HOT AIR DISCHARGE MEANS - The invention relates to an aircraft nacelle that comprises a discharge means ( | 12-16-2010 |
| 20110114787 | ACOUSTIC TREATMENT PANEL WITH INTEGRAL CONNECTING REINFORCEMENT - An acoustic treatment panel includes, from the inside to the outside, a reflective layer ( | 05-19-2011 |
| 20110114796 | DEVICE FOR SHROUDING AN AIRCRAFT NACELLE - An aircraft nacelle includes an air intake ( | 05-19-2011 |
| 20110116916 | DEVICE FOR SHROUDING AN AIRCRAFT NACELLE - An aircraft nacelle includes an air intake followed at the upper part by a part that is integral with the mast, called a cap, and at least one door with a curved profile that includes a stiffening device arranged at the edge upstream from the door and which includes:
| 05-19-2011 |
| 20110139927 | PANEL FOR AN AIR INTAKE OF AN AIRCRAFT NACELLE THAT ENSURES OPTIMIZED ACOUSTIC TREATMENT AND FROST TREATMENT - An acoustic treatment panel includes an acoustically resistive layer that defines a surface of an aircraft that is in contact with an aerodynamic stream, a reflective layer ( | 06-16-2011 |
| 20110139940 | WAVE ATTENUATION PANEL INSERTED BETWEEN THE MOTOR AND AIR INLET OF AN AIRCRAFT NACELLE - An aircraft nacelle includes an air intake for channeling air flow in the direction of a power plant. The air intake includes an inside pipe that forms an aerodynamic surface in contact with the air flow and is extended toward the rear by an aerodynamic surface of a pipe of the power plant. The nacelle includes a wave attenuation panel which limits or prevents the propagation of at least one wave produced during the pumping of the power plant and includes a layer that is in contact with the air flow that can allow passage of the at least one wave, at least one alveolar structure, and a reflective or impermeable layer, wherein the wave attenuation panel is inserted between the air intake and the power plant, and the layer that is in contact with the air flow ensures the continuity of the aerodynamic surfaces that are arranged downstream and upstream and the wave attenuation panel includes inserts that can be inserted between the air intake and the power plant so as not to crush the wave attenuation panel. | 06-16-2011 |
