Safran Aircraft Engines

General Electric Company

Safran Nacelles

Nicolas Maurice Herve Aussedat

Pierre Caruel

Gilles Alain Charier

Bruno Albert Beutin

Nathalie Nowakowski

Kevin Morgane Lemarchand

Nicolas Joseph Sirvin

Guillaume Glemarec

Augustin Marc Michel Curlier

Philippe Gerard Chanez

Nicolas Alain Bader

Christian Sylvain Vessot

Hervé Jean Albert Mouton

Jean-Baptiste Manuel Nicolas Vignes

Ludovic Michael Laurent Toupet

Mathieu Marc Christian Gaillot

Mathieu Lallia

Lionel Jean Leon Lefranc

Gwénolé Yann Le Pache

A triple-flow turbine engine for an aircraft, this turbine engine having a longitudinal axis and including upstream suspension elements which are located in a first plane perpendicular to the axis and are connected or fixed to the gas generator of the turbine engine; downstream suspension elements which are located in a second plane perpendicular to the axis and are connected or fixed to the gas generator; and thrust-absorbing rods which include first ends which are connected or fixed to the gas generator and opposing second ends which are located in a third plane perpendicular to the axis, wherein the first, second and third planes are located at a cold compartment of the gas generator.

Suspension of a triple-flow aircraft turbine engine

An aircraft including a fuselage, a lateral support wing () and a propulsion assembly () mounted under the wing. The wing includes at least two structural spars () extending from the fuselage toward the tip of the wing, one of these () being upstream and the other () downstream. The propulsion assembly includes a gas generator () and at least two offset fans () arranged on either side of the axis of the gas generator. The offset fans () are attached directly to one of the spars () and the gas generator () is attached directly to the two spars. The leading edge of the wing forms a given sweep of angle (&#x3b1;) with the axis of the fuselage. The two offset fans () are axially offset from one another.

Aircraft with multiple fan propulsion assembly fixed under the wing

A turbomachine for an aircraft, comprising a rotor shaft, a turbomachine case, a lubricated bearing chamber, at least one bearing supporting the rotor shaft and being located in the bearing chamber, a lubrication device comprising oil injection means to inject oil into the bearing chamber, and oil supply means to supply oil to said oil injection means, and an electric current generator, comprising an armature driven by the rotor shaft and a field coil fixed to the turbomachine case. The generator has an orifice, which passes longitudinally through the generator from one end to the other, and the oil injection means pass through the orifice so that oil can circulate in the axial direction through the generator.

Turbomachine comprising an electric current generator allowing oil injection from the inside of a rotor shaft

Growing community of inventors

Moissy-Cramayel, France

Nicolas Maurice Herve Aussedat