Safran Aircraft Engines

Snecma

Societe Lorraine De Construction Aeronautique

Stéphane Orcel

Norman Bruno André Jodet

Jérémy Paul Francisco Gonzalez

Francis Couillard

Nicolas Jerome Jean Tantot

Mathieu Ange Poisson

Jean-Michel Boiteux

Jean-Luc Pacary

Jean-Michel Daniel Paul Boiteux

Pascal Charles Edouard Coat

Jean-François Endy Bersot

Guillaume Glemarec

The invention relates to acoustic management, on an aircraft turbomachine or on a nacelle, via a panel (). On a support () is reserved a recess (), recessed with respect to a surrounding general surface () for contact with moving air. The recess () is adapted to receive the panel, as another so-called surface for contact with moving air. The support () and/or the panel comprise removable connecting elements for, in the recess, mounting the panel removably with respect to the support, the panel being an acoustic panel () or a non-acoustic panel ().

Acoustic management, on a turbomachine or a nacelle

The invention relates to the rating (S) of a propulsion unit () comprising a main engine () providing main thrust assisted by an auxiliary engine () providing auxiliary thrust, according to the following steps: (i) determining (S) a distribution between the main thrust and the auxiliary thrust so as to obtain the takeoff thrust of the propulsion unit, the auxiliary thrust making a 5% to 65% contribution to the takeoff thrust, (ii) depending on the distribution determined for the takeoff condition, determining (S) distribution between the main thrust and the auxiliary thrust so its to obtain the top of climb thrust of the propulsion unit, the auxiliary thrust making at most 70% contribution to the top of climb thrust, and (iii) rating (S) the propulsion unit () in such a way that the main thrust of the main engine () determined fir the takeoff condition corresponds to the maximum thrust likely to be achieved by the main engine ().

Method for rating a propulsion unit comprising a main engine and an auxiliary engine

The invention relates to acoustic management, on an aircraft turbomachine () or on a nacelle (), via a panel (). On a support () is reserved a recess (), recessed with respect to a surrounding general surface () for contact with moving air. The recess () is adapted to receive the panel, as another so-called surface for contact with moving air. The support () and/or the panel comprise removable connecting elements for, in the recess (), mounting it removably with respect to the support, the panel being an acoustic panel or a non-acoustic panel.

Method for preparing a support and for acoustic management on a turbine engine or a nacelle

A turboprop includes a rotary propeller upstream from an engine and an air intake that is not coaxial to the propeller, said air intake defining a conduit for supplying air to the engine and further defining a bypass to said conduit, the bypass having an outlet oriented substantially axially towards the downstream of the engine. The turboprop further includes a nacelle surrounding the engine and the air intake, wherein the air intake is secured to a housing of the engine and is not rigidly connected to the nacelle, so as to allow, during operation, relative movements between the air intake and the nacelle. The outlet is connected by a flexible link to an intake of an air circuit carried by the nacelle.

Turboprop air intake

Growing community of inventors

Moissy-Cramayel, France

Stéphane Orcel