Airbus Operations (s.a.s.)

Airbus Operations Gmbh

Creuzet Aeronautique

Fabrice Gantie

Alain Porte

Jacques Lalane

Frédéric Chelin

Thierry Surply

Bernard Duprieu

Valerie Frustie

Dominique Haro

Patrick Oberle

Gilles Chene

David Lambert

Christophe Menier

Thomas Gilles

Jean Yves Thomy

Etienne Bertin

Jacques Barillot-Creuzet

Yann Druon

Valérie Frustie

An internal wall of an air intake and a housing of a fan form a single tubular piece made from a fiber/resin composite material. A rear end has the single tubular component connected by a flange and bolts to an external cowl of the fan duct, such that the rear end of the tubular component is uniform and the flange is attached and fixed to the rear end.

Turbine engine for aircraft

An aircraft nacelle including a pipe (), a peripheral wall (), a lip (), and a front frame () connecting the peripheral wall () and the pipe () and forming with the lip () a space () in which the hot air that is provided for frost treatment can circulate, with the pipe () including a coating () for the composite material acoustic treatment, is characterized in that the nacelle includes at least one element () made of a heat-conducting material inserted between the lip () and the pipe () ensuring the continuity of the aerodynamic surfaces of the lip () and the pipe () and the propagation of heat from the space () toward the rear of the nacelle, whereby the at least one element () includes a coating () for acoustic treatment that is made of a heat-resistant material.

Aircraft nacelle including an optimised acoustic processing system

An acoustic treatment panel that is connected to an air intake of an aircraft nacelle, includes at least one acoustically resistive structure () and a reflective layer (), between which are located&#x2014;in a direction that is essentially perpendicular to the longitudinal direction of the nacelle&#x2014;bands () of alveolar cells spaced in such a way as to allow the passage of hot air provided for a frost treatment, characterized in that it includes pipes () for hot air that are each delimited by at least one partition that extends from the acoustically resistive layer () up to the reflective layer () in such a way as to insulate the bands () of cells in the longitudinal direction.

Acoustic processing panel, more particularly adapted for an air intake in an aircraft nacelle

An aircraft leading edge, such as, for example, an air intake () of a nacelle () of a propulsion unit, includes a coating () for the acoustic treatment that includes&#x2014;from the outside to the inside&#x2014;an acoustically resistive porous layer that has a determined open surface ratio, at least one alveolar structure, and a reflective layer, whereby the coating () integrates a frost treatment system, characterized in that a frost treatment system includes at least one vibration emitter ().

Aircraft leading edge

A process for producing a panel for acoustic treatment including a resistive porous layer, an alveolar structure, a reflective layer with openings, and a drainage plate having a furrow for delimiting at least one evacuation pipe when the drainage plate is flattened against the free surface of the reflective layer, includes: shaping the reflective layer according to its final geometry, affixing a demolding film on at least one portion of the free surface of the reflective layer, positioning on the demolding film a core whose cross-section is adapted to that of the evacuation pipe so that the core covers the openings of the reflective layer, molding the drainage plate on the demolding film and the core, demolding the drainage plate and removing the core and the demolding film, and making the drainage plate integral with the free surface of the reflective layer.

Method for making a network of drainage pipes and acoustic processing panel including such a network of drainage pipes

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&#x2014;from the outside to the inside&#x2014;at least one acoustically resistive substructure (), at least one alveolar substructure including strips () of cells, arranged in a direction that is essentially perpendicular to the direction of flow of the aerodynamic stream, and at least one reflective layer (). Each strip () includes a first part that insulates the strips from one another, called a support, with a U-shaped cross-section in the longitudinal direction, whose open surface that is opposite to the bottom of the U shape is flattened against the acoustically resistive substructure (), and at least a second part, called partitioning, making it possible to partition the space that is delimited by the support and the acoustically resistive substructure () into cells.

Acoustic processing structure particularly adapted to the air inlet of an aircraft nacelle

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 (), at least one cellular structure () and an acoustically resistive structure () having a pre-determined proportion of open surface; and (ii) at least one frost treatment system in the form of at least one heating layer () comprising open zones through which acoustic waves can pass, which co-operate at least partially with the open zones in the acoustically resistive structure. The invention is characterized in that the acoustically resistive structure () includes at least one structural layer () with openings () and in that said at least one heating layer () is disposed under the structural layer ().

Acoustic coating for an aircraft incorporating a frost treatment system by joule effect

A device for improving the effectiveness of the acoustic treatment(s) in an aircraft propulsion unit that includes a pipe () into which a gas stream flows, whereby the pipe () is delimited by two approximately concentric inside walls () and outside walls (), wherein the device includes at least one partition () that extends over at least one portion of the length of the pipe () between the inside and outside walls () and in that the profile of at least one wall () of the at least one partition () is defined so as to increase the number of reflections of an acoustic beam on at least one of the inside and/or outside walls () of the pipe and/or on at least one of the walls () of the at least one partition ().

Device that makes it possible to improve the effectiveness of the acoustic treatments in a pipe of an aircraft power plant

A panel for acoustic treatment connected to a surface of an aircraft, includes&#x2014;from the outside to the inside&#x2014;an acoustically resistive porous layer, at least one alveolar structure, and a reflective or impermeable layer, whereby the acoustically resistive porous layer includes&#x2014;at the outside surface that can be in contact with the aerodynamic flows&#x2014;one sheet or piece of sheet metal including open zones () that allow sound waves to pass and filled zones () that do not allow sound waves to pass, characterized in that the sheet or piece of sheet metal of the acoustically resistive layer includes sets of microperforations (), whereby each set of microperforations forms an open zone (), the sets of microperforations being separated from one another by at least one series of bands separated by filled zones ().

Acoustic panel

A coating for acoustic treatment relative to an aircraft's surface, in particular a leading edge such as an air intake of an aircraft nacelle, includes an acoustically resistive layer, at least one alveolar structure (), and a reflective layer. The alveolar structure () includes a number of tubes that empty out, on the one hand, at a first imaginary surface (), and, on the other hand, at a second imaginary surface (). The alveolar structure () includes cut-outs or openings () made at the side walls of certain tubes that make it possible to link adjacent tubes so as to create a network of communicating tubes that isolate at least one tube or a group of non-communicating tubes, whereby at least one of the communicating tubes is connected to at least one hot gas intake ().

Growing community of inventors

Toulouse, France

Fabrice Gantie