Safran Aircraft Engines

Maria Natal

Bruno Albert Beutin

Bruna Manuela Ramos

Nuria Llamas Castro

Sara Bustillo

Arnaud Ple

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 nacelle for a propulsion unit includes at least one scoop opening to the external air, and a canal supplying external air from the scoop to two ducts which separate downstream of the canal, forming a dividing lip, and at least one exchanger to cool a stream of fluid entering the exchanger. The exchanger is arranged in the region of and in contact with the separation lip. The external air circulates from the scoop towards the two ducts making it possible to cool the stream of fluid entering the exchanger.

Nacelle comprising an exchanger for cooling a stream of fluid

A device for suspending a casing of a turbine engine to the structure of an aircraft is provided. The device includes a suspension ring including a plurality of attachment surfaces positioned so as to protrude on the circumference of the suspension ring and having attachment holes for attachment to the structure; a circumferential flange including a plurality of holes for attaching the suspension ring to the casing; and one or several hanging surfaces for hanging at least one piece of equipment, positioned so as to protrude on the circumference of the suspension ring, and having holes for hanging the piece of equipment to the ring.

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Paris, France

Maria Natal