Safran Aircraft Engines

Snecma

Hispano Suiza

Safran Transmission Systems

Nuria Llamas Castro

Bruno Albert Beutin

Bruna Manuela Ramos

Maria Natal

Bellal Waissi

Stéphane Prunera-Usach

Jordane Peltier

Alain Pierre Garassino

Lambert Olivier Marie Demoulin

Frantz Armange

Stephane Prunera-Usach

Jordanne Peltier

The main purpose of the invention is an air circulation device () for a turbomachine (), comprising an air conveyance circuit () adapted to bring hot bleed air (A) from the turbomachine () to a part to be heated (), comprising a first segment fixed in rotation to a rotating part () and comprising at least one hot air (A) conveyance conduit (), and a hot air passage device (), comprising an annular compartment fixed in rotation to the first segment, characterise in that the annular compartment comprises a heat exchanger in contact with external air, and in that the hot air passage device () comprises a hot air bypass system to deviate air entering into the device and to make it circulate along the heat exchanger when the temperature of this intake air is above a predetermined threshold.

Air circulation device for a turbomachine comprising a hot air bypass system to a heat exchanger

An airplane unducted propeller turboshaft engine having a gas generator and a receiver including a propulsion assembly carrying least one propeller, the engine including a first casing, a second casing, and a third casing, the third casing being provided between the first and second casings and surrounding at least a portion of the gas generator, a reinforcing shell presenting a first attachment zone mounted on the first casing, second attachment zone mounted on the second casing, and a wall provided between the first and second attachment zones and surrounding the third casing, wherein the reinforcing shell further includes at least one pipe segment integrated in the wall.

Unducted propeller turboshaft engine provided with a reinforcing shell integrating pipe segments

A turbine engine having a nacelle is provided. The nacelle includes, upstream, an air intake fairing and an element for deflecting foreign objects which defines with the fairing an air intake flow path for supplying air to two coaxial flow paths which are a radially inner flow path and a radially outer flow path. The outer flow path being is by a hub housing and scoops, the hub housing and the scoops being installed downstream of the element for deflecting objects. Each scoop includes two independent portions which are an upstream portion borne by the hub housing, and a downstream portion borne by the nacelle.

Turbine engine having an element for deflecting foreign objects

A gearbox to be mounted on a turbomachine and driven by a radial drive shaft of the latter. The gearbox has a three-dimensional or sinuous shape, which can house a large quantity of equipment to be driven, without occupying a large amount of space in any dimension, since the gearbox remains close to the turbomachine and the equipment can be distributed over a large surface. The drive train of gears successively extends into several non-parallel planes and comprises an axial branch on the turbomachine and a branch forming an arc of circle around the turbomachine.

Drive gearbox on a turbomachine, consisting of a drive train with gear lines extending into non-parallel planes

Growing community of inventors

Savigny sur Orge, France

Nuria Llamas Castro