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 |
20110168839 | DEVICE FOR CONNECTING AN AIR INLET WITH AN AIRCRAFT NACELLE ACTUATOR ASSEMBLY - An aircraft nacelle includes an air intake that makes it possible to channel the air in a pipe in the direction of a pipe of a power plant that is arranged in the extension of the pipe, whereby the pipe of the air intake includes at least one panel that integrates an acoustic treatment with an acoustically resistive porous layer that is in contact with the aerodynamic stream that enters into the nacelle, at least one alveolar structure, and a reflective or impermeable layer that forms the rear surface of the panel, a flange that ensures the connection between the air intake and the power plant including at least one wing that is connected to the air intake by a number of connecting elements, characterized in that some of the connecting elements have axes that are secant with the edge of the panel that delimits the pipe of the air intake. | 07-14-2011 |
20110168852 | METHOD OF DEPOSITING A COATING FOR IMPROVING LAMINAR FLOW - A process for deposition of a coating whose purpose is to improve the laminar flows at a junction between a first panel ( | 07-14-2011 |
20110174930 | FUSE LINK DEVICE BETWEEN A MOBILE PART AND A FIXED PART OF AN AIRCRAFT NACELLE - The object of the invention is an aircraft nacelle that comprises at least one part, called a door ( | 07-21-2011 |
20110226903 | DE-ICING DEVICE COMPRISING MEANS FOR DETECTION OF A LEAKAGE IN A HOT AIR SUPPLY SYSTEM - A device for defrosting a leading edge of an aircraft, includes at least one opening ( | 09-22-2011 |
20110253843 | Air Intake Arrangement For An Aircraft - The invention relates to an arrangement ( | 10-20-2011 |
20110303302 | NACELLE COMPRISING AN AIR ENTRANCE IN A CAP - An aircraft nacelle includes an outside wall ( | 12-15-2011 |
20120090694 | AIRCRAFT NACELLE INCLUDING A REAR FRAME INCLINED TO THE REAR - An aircraft nacelle includes a lip whose surface contacts with the aerodynamic streams extends inside the nacelle by an inside wall that delimits a layer that empties at a power plant and outside of the nacelle by an outside wall, a first front frame connects the inside and outside walls, delimiting an annular pipe with the lip, and a rear frame connects the inside and outside walls at a junction zone between the inside pipe and power plant pipe, for a given cross-section of the nacelle along a plane that contains the longitudinal axis of the nacelle, a point A at the intersection between the rear frame and the inside wall, and a point B at the intersection between the rear frame and the outside wall, with B being offset toward the rear of the nacelle relative to A over more than 50% of the rear frame's periphery. | 04-19-2012 |
20120090695 | AIRCRAFT NACELLE INCLUDING AT LEAST ONE RADIAL PARTITION BETWEEN TWO CONDUCTS - An aircraft nacelle that makes it possible to channel a stream of air in a longitudinal direction and that includes at least two panels ( | 04-19-2012 |
20120091285 | AIRCRAFT NACELLE INCLUDING A CONTINUE JOINT AREA BETWEEN AN OUTER WALL AND A FRONT FRAME - An aircraft nacelle includes a lip that is extended inside the nacelle by an inside wall that delimits a pipe that empties at a power plant and outside of the nacelle by an outside wall, a first frame called a front frame that connects the inside wall and the outside wall, delimiting an annular pipe with the lip, and a second frame called a rear frame that connects the inside wall and the outside wall close to the power plant, characterized in that it includes at least one junction zone—at at least one cross-section of the nacelle along a plane that contains the longitudinal axis of the nacelle—an element that constitutes at least one part of the outside wall and at least one part of the front frame and that includes an offset whose shapes are suitable for accommodating a panel that forms the lip. | 04-19-2012 |
20120097260 | AIRCRAFT COVER INCLUDING MEANS FOR LIMITING THE SCOOP PHENOMENA OF ELECTROMAGNETIC TYPE - An aircraft nacelle includes at its outside wall a cowl that can move relative to the rest of the nacelle so as to block or unblock an opening. The cowl includes an articulation relative to the rest of the nacelle and locking/unlocking elements distant from the upstream edge of the cowl that includes elements for limiting the appearance of scooping phenomena. The limiting elements include at least one electromagnetic torque, having one element integral with the rest of the nacelle and the other element integral with the cowl, with at least one of these two elements emitting a magnetic field that generates a force of attraction on the other element, and the surfaces of the two elements of the electromagnetic torque that are flattened against one another are arranged in planes having at least one component in the radial direction. | 04-26-2012 |
20120097261 | AIRCRAFT COVER INCLUDING MEANS FOR LIMITING THE SCOOP PHENOMENA OF PNEUMATIC TYPE - An aircraft nacelle includes at its outside wall a cowl moveable relative to the nacelle so as to block or unblock an opening. The cowl includes an articulation and locking/unlocking elements distant from the upstream edge of the cowl that include elements for limiting the appearance of scooping phenomena. The limiting elements include at least one lock integral with the rest of the nacelle or respectively the cowl that can occupy a locked state in which part of the lock interferes with the cowl or respectively the rest of the nacelle and prevents a deformation that includes a radial component of the cowl, and another free state in which the part no longer interferes with the cowl or respectively the rest of the nacelle and allows the opening movement of the cowl, with the switch from one state to the next being generated by a gas pressure variation. | 04-26-2012 |
20120241249 | PANEL FOR THE ACOUSTIC TREATMENT WITH A PROGRESSIVE THICKNESS - An aircraft nacelle includes an air inlet ( | 09-27-2012 |
20120248250 | AIRCRAFT NACELLE AIR INTAKE INCORPORATING OPTIMIZED ICE-TREATMENT HOT AIR INJECTION MEANS - An aircraft nacelle air intake includes a duct extending around the circumference of the air intake and elements ( | 10-04-2012 |
20120261521 | NACELLE INCORPORATING AN ELEMENT FOR CONNECTING A LIP AND AN ACOUSTIC ATTENUATION PANEL TOGETHER - An aircraft nacelle includes a first subassembly consisting of a pipe ( | 10-18-2012 |
20120280090 | CONNECTING DEVICE PARTICULARLY ADAPTED FOR THE CONNECTION BETWEEN AN AIR INTAKE AND AN ENGINE OF AN AIRCRAFT NACELLE - A connecting device between two cylindrical parts that are connected at a junction plane, more particularly suited for connecting an air intake and a power plant of an aircraft nacelle, includes—at the parts to be connected—a large number of through holes that are perpendicular to the junction plane and that empty out at the junction plane, arranged facing one another and connecting elements housed in the through holes, each including a rod with supports at each end that make it possible to keep the parts to be connected flattened. The through holes include—for each—at least one small cross-section that is adjusted to the rod of the connecting element close to the corresponding support and a cross-section with significant play at the junction plane so that the rod only undergoes very weak shear forces at the junction plane during the relative deformation of the assembled parts. | 11-08-2012 |
20120317782 | Process for the Production of a Panel for the Acoustic Treatment Incorporating the Frost Treatment Function with Hot Air - A process for the production of an acoustic treatment panel that can be connected at a surface of an aircraft, in particular at a leading edge such as an air intake of an aircraft nacelle, whereby the panel includes an acoustically resistive layer ( | 12-20-2012 |
20120318029 | PROCESS FOR THE PRODUCTION OF AN ACOUSTIC TREATMENT PANEL THAT INTEGRATES CHANNELS JUXTAPOSED WITH AN ALVEOLAR STRUCTURE - A process for the production of an acoustic treatment panel that includes an acoustically resistive layer ( | 12-20-2012 |
20120318924 | AIR INTAKE OF AN AIRCRAFT NACELLE THAT INCORPORATES A REINFORCED LIP WITH A DEFROST SYSTEM BY JOULE-EFFECT - An air intake of an aircraft nacelle includes: | 12-20-2012 |
20130032669 | FASTENING DEVICE PARTICULARLY SUITABLE FOR THE FASTENING BETWEEN AN AIR INTAKE AND AN ENGINE OF AN AIRCRAFT NACELLE - An aircraft nacelle with a connecting device between a first conduit of an air intake and a second conduit of a motor, both conduits being arranged end-to-end, the connecting device including an annular flange connected to the air intake, an annular flange connected to the motor pressed against annular flange of the air intake, the flanges extending in a plane perpendicular to the longitudinal axis of the nacelle; bolt holes formed in annular flanges and disposed plumb to one another; and connecting elements located in bolt holes, for connecting the annular flanges, wherein at least one flange includes at least one opening interposed between a bolt hole and junction zone of the flange and/or between a bolt hole and outer edge of the flange. | 02-07-2013 |
20130033036 | FASTENING DEVICE PARTICULARLY SUITABLE FOR THE FASTENING BETWEEN AN AIR INTAKE AND AN ENGINE OF AN AIRCRAFT NACELLE - A fastening device includes an annular flange connected to an air intake, an annular flange connected to a powerplant pressed against the annular flange and fastening elements that allow the annular flanges to be linked, and for at least a first fastening element, a blade is fitted between the fastening element and the annular flange, the blade consisting of at least a central part linked to the first fastening element, radially mobile relative to the annular flange, and at least one part offset for which at least radial centripetal displacement is limited relative to the annular flange, the two parts being offset along the direction of the circumference. | 02-07-2013 |
20130034437 | FASTENING DEVICE PARTICULARLY SUITABLE FOR THE FASTENING BETWEEN AN AIR INTAKE AND AN ENGINE OF AN AIRCRAFT NACELLE - An aircraft nacelle includes a first conduit for an air inlet and a second conduit for an engine, arranged end to end and connected by an annular flange, attached to the air inlet, and an annular flange, attached to the engine. The annular flanges are connected by a plurality of passage holes in the annular flanges and arranged in line with each other. Rods are housed in the passage holes. For at least one rod, the passage hole of one of the annular flanges has a diameter greater than the diameter of the rod allowing the rod to move in case of deformation of one of the two conduits. An angle profile is inserted between the rod and a cylindrical portion adjacent to the annular flange and. is connected to the adjacent cylindrical portion through the intermediary of at least one means for absorbing eventual deformations in radial direction. | 02-07-2013 |
20130040117 | WALL REINFORCED COMPOSITE MATERIAL - A wall panel of composite material including at least two carbon fiber layers oriented parallel to the plane of the panel and embedded in a resin matrix. At least one reinforcement mesh is inserted between the two fiber layers. The mesh has at least a first series of linear elements with a section greater than or equal to 0.07 mm | 02-14-2013 |
20130098471 | Aircraft nacelle comprising a hot air supply device for a panel combining acoustic and frost treatments - The object of the invention is an aircraft nacelle comprising a lip extended by an inner conduit forming an air intake, a front frame delimiting with said lip annular channel within which hot air circulates, and a panel for acoustic treatment comprising, from outside inwardly, an acoustic resistive layer, at least one honeycomb structure and one reflective layer as well as ducts for channeling hot air, at least one conduit with opening which opens into annular channel being provided for carrying hot air up to the panel for acoustic treatment, wherein opening is used for channeling hot air in direction which forms an angle β of less than 60° with hot air flow direction into annular channel. | 04-25-2013 |
20130146393 | METHOD FOR PRODUCING AN ACOUSTIC TREATMENT PANEL - A method for producing an acoustic treatment panel, including:
| 06-13-2013 |
20130183513 | WALL MADE FROM A COMPOSITE MATERIAL REINFORCED SO AS TO LIMIT THE SPREAD OF A CRACK IN A DIRECTION - The invention relates to a wall made from a composite material comprising at least two layers of fibers ( | 07-18-2013 |
20130224000 | Panel for the acoustic treatment comprising hot air ducts and at least one annular channel - An aircraft nacelle comprising a lip extended by an inner conduit forming an air intake, a front frame delimiting with said lip an annular channel wherein hot air circulates, as well as a panel for acoustic treatment comprising, from outside inwardly, an acoustic resistive layer, at least one honeycomb structure, and a reflective layer, as well as ducts for channeling hot air with each one inlet communicating with the annular channel and one outlet communicating with the inner conduit, wherein the panel for acoustic treatment comprises, upstream from the ducts, an annular channel which extends over at least a portion of the nacelle circumference, at least one conduit providing communication between said annular channel and the upstream annular channel, and a plurality of ducts that open into said downstream annular channel, the panel for acoustic treatment being connected to the front frame in regard to the annular channel. | 08-29-2013 |
20140001284 | Panel for the acoustic treatment comprising hot air ducts and at least one stabilization chamber | 01-02-2014 |
20140144519 | AIRCRAFT NACELLE COMPRISING A REINFORCED CONNECTION BETWEEN AN AIR INTAKE AND A POWERPLANT - An aircraft nacelle comprising a first duct secured to an air intake and a second duct secured to a powerplant, the first duct comprising an exterior surface and an end portion connected to the second duct. The nacelle includes a hollow section piece in contact with the exterior surface of the first duct which extends over at least part of the circumference of that end portion of the first duct that is connected to the second duct. | 05-29-2014 |
20140147268 | AIRCRAFT NACELLE COMPRISING A DEFORMABLE CONNECTION BETWEEN AN AIR INTAKE AND A POWER PLANT - An aircraft nacelle comprising a first duct secured to an air intake and a second duct secured to a power plant. The two ducts are arranged end-to-end and connected by a connection. The connection comprises a bracket which extends between a first region for connecting to the power plant and a second region for connecting to the air intake, and which comprises a J-shaped profile in longitudinal planes, having at least one curved portion offset towards the outside of the nacelle with respect to the connecting regions. | 05-29-2014 |
20140147269 | AIRCRAFT NACELLE INCORPORATING AN IMPROVED CONNECTION BETWEEN AN AIR INTAKE AND A POWERPLANT - An aircraft nacelle comprising two ducts, a first duct secured to an air intake and a second duct secured to a powerplant. The ducts are arranged coaxially in a longitudinal direction, in contact with one another at a junction plane and joined together by a connection which comprises a plurality of through holes oriented in the longitudinal direction and connecting elements housed in the through holes. Each connecting element comprises a shank with, at each end, lands allowing the ducts to be joined together. At least one through hole of at least one of the two ducts has an oblong section with the largest dimension oriented to allow relative rotation of the two ducts about an axis in the longitudinal direction. | 05-29-2014 |
20140147270 | Aircraft Nacelle Comprising A Reinforced Connection Between An Air Intake And A Means Of Propulsion - An aircraft nacelle includes an air intake, connected to a means of propulsion, which defines a longitudinal direction, an outer wall, an inner duct including an annular flange connected, by means of connecting elements, to the means of propulsion, and a forward frame and a rear frame which connects the outer wall and the inner duct. | 05-29-2014 |