Airbus Operations (s.a.s.)

Airbus Operations Gmbh

Nicolas Molin

Jean-François Piet

Bastien Caruelle

Stéphane Perrin Decroux

Constantin Sandu

Cedric Leconte

Guillaume Clairet

Pascal Souchotte

Emmanuel Jondeau

Jean-Michel Perrin

Isabelle Boullet

Alois Sengissen

Jean-Francois Piet

An aircraft turbomachine comprising a fan conduit with a wall, a flow of air passing through the turbomachine via the fan conduit. An air passage comprising an air opening is arranged in the wall, the air passage configured to receive a portion of the flow of the air through the fan conduit. A deflector is fixed to the wall upstream of the air opening, the deflector comprising at least one cross-section extending in the fan conduit to capture the flow of air. The at least one cross-section is porous. The deflector protects the air passage structure and is easy to produce and to fix to the wall of the fan conduit when it is screwed or riveted directly thereto. The deflector, as a result of its location in the fan conduit, is easy to access and thus allows rapid maintenance operations without having to disassemble the air passage.

Aircraft turbomachine comprising a deflector

A masking method includes: a step of choosing a generating element which is part of the skin of an aircraft, a first step of measuring a fundamental frequency of a sound signal emitted by the generating element, a step of selecting a masking element which is part of the skin, a second step of measuring a fundamental frequency of another sound signal emitted by the masking element, a step of modification of the structure of the masking element in such a way as to shift the fundamental frequency of the sound signal emitted by the masking element to a frequency lower than the fundamental frequency of the sound signal emitted by the generating element. Such a masking method thus makes it possible to mask the sound signal emitted by the generating element by the sound signal emitted by the masking element.

Method for masking a sound signal generated by an element of the skin of an aircraft

An aircraft includes at least one net for reducing aerodynamic noise from a structural element of the aircraft. The flexible net associated with the structural element is retractable and capable of occupying at least one position located between the following two end positions: a deployed position, in which the net is placed in a turbulence area, and a retracted position, in which the net is at least partially outside the turbulence area. The net may be automatically moved between positions based on an aircraft parameter such as speed or altitude.

Aircraft with at least one net for reducing aerodynamic noise from a structural element of the aircraft

Disclosed is an landing gear that includes at least One constituent element having an upstream air side and downstream air side relative to airflow across the aircraft landing gear in the down position. The landing gear also includes at least one noise reducing unit including at least one individual net having geometric meshes. The net is positioned at the downstream air side of the constituent element and is arranged at the downstream air side so as to reduce noise generating turbulence generated by airflow across the constituent element in its down position.

Aircraft landing gear provided with at least one noise reducing means

According to the invention, at least part of the edge of the hole is loosely surrounded with a mesh structure so as to create a space between the latter and said edge part.

Method for reducing the noise generated by a hole under a high energy gas flow

Growing community of inventors

Nailloux, France

Nicolas Molin