Aircelle Limited

Societe Nationale D'etude Et De Construction De Moteurs D'aviation

Hispano Suiza Aerostructures

Ateca

Eric Lecossais

Guy Bernard Vauchel

Patrick Gonidec

Laurent Georges Valleroy

Gilles Le Gouellec

Osmin Regis Delverdier

Sebastien Vieillard

Philippe Jean Vie

Michel Philippe Dehu

Fabrice Henri Emile Metezeau

Fabrice Metezeau

Pascal Gerard Rouyer

Regis Meuret

Jacques Michel Julliard

Georges Jean Riou

Sébastien Vieillard

Felix Carimali

Frederic Zoonekyndt

Thierry Ledocte

Bernard Louis Le Barazer

Henriette S Lemay

Bertrand Lebrun

Régis Meuret

Frédéric Zoonekyndt

Pascal Gérard Rouyer

Félix Carimali

The invention relates to a method for controlling an electric motor actuating a mobile hood provided in a thrust reverser for a turboreactor, said method being characterized in that it comprises steps of: determining the operating state of the electric motor; interrupting the supply of the electric motor if said motor is not in operation during a defined period of time; reactivating the electric motor after an idle period and repeating the previous steps or definitively stopping the motor if the steps have already been repeated a pre-defined number of times. The invention also relates to a method for managing the electrical supply of a motor provided in a device arranged in the vicinity of a turboreactor.

Method for controlling electric motors of a thrust reverser

The invention relates to a rear section () of an aircraft nacelle, that comprises two halves () defining: a central portion (C) for receiving a turbojet engine (), a cool-air annular passage () provided around said central portion (C), and at least one six-hour cavity () provided under said central portion (C). The rear section is characterized in that it comprises at least one duct () for the fluidic communication between said annular passage () and said six-hour cavity () for maintaining the temperature inside the six-hour cavity () within a relatively low range.

Rear section of aircraft nacelle and nacelle equipped with such rear section

This grid thrust reverser cover comprises a seal support and a seal mounted in this support by means of two fastening lugs, this seal being capable of interacting with a diversion edge of this thrust reverser. At least one of the said lugs is turned up and the said support has a section matching that defined by the said lugs.

Grid thrust reverser cover comprising a seal support and associated seal

A soundproofing panel comprises a honeycomb core sandwiched between a solid skin and a porous skin, the cells of the honeycomb being divided in the direction of its thickness into at least two resonant cavities by a least one partition which is traversed by passages interlinking the cavities. The partitions are formed by a plurality of hollow microbeads having porous walls, the microbeads being bonded to one another and to the walls of the honeycomb at their points of contact. Such a soundproofing panel combines high performance in terms of linearity as a function of the level of sound excitation, attenuation band, bulk and mechanical strength.

Soundproofing panel and method of producing said panel

A thrust reverser for a turbojet engine is disclosed in which the thrust erser baffles have one or more deflectors to direct the cold gas flow over an inner surface of the baffles to ensure that the inner surface remains out of contact with the hot gas flow. The deflectors are movably mounted on the baffles such that, when the baffles are in their forward thrust positions, the deflectors are retracted so as to be generally flush with the inner surface of the baffle so as not to interfere with the forward thrust flow of gases. The deflectors may be automatically deployed to their extended positions when the baffles are moved to their reverse thrust positions.

Thrust reverser with aerodynamically cooled baffle

Growing community of inventors

Virville, France

Eric Lecossais