Safran Aircraft Engines

Bruna Manuela Ramos

Bruno Albert Beutin

Nuria Llamas Castro

Carmen Gina Ancuta

Maria Natal

Thierry Kohn

Florian Benjamin Kévin Lacroix

Antonin Etienne Diego Tessiereau

Pascal Xavier Delaitre

A dual-flow turbomachine generally includes a cooling and turbine clearance control system located in a primary air flow path of the turbomachine, supplied a scoop configured to take air from a secondary air flow path arranged around the primary air flow path through an air inlet of the scoop, where the scoop may further include one wall configured to be arranged in the extension of a wall of the secondary flow path, and further where the air inlet may be formed in and flush with the wall.

Turbomachine including a cooling and turbine clearance control system having an air supply scoop

A turbomachine comprises an inter-flow compartment extending radially between first and second intermediate walls, gas bypass ducts passing through the second intermediate wall and communicating with evacuation outlets opening up into a secondary gas flow; an oil reservoir arranged in the inter-flow compartment, and a surface air-oil heat exchanger communicating with the oil reservoir for fluid circulation. Circumferentially in relation to the inter-flow compartment, the surface air-oil heat exchanger extends at least partially between the evacuation outlets which pass through the first intermediate wall.

Turbomachine comprising a surface air-oil heat exchanger built into an inter-flow compartment

An aircraft propulsion assembly having a thrust reverser with moving guards, including an engine covered by a front cover and a rear cover that are both mobile; moving guards supported by the rear cover, the guards being covered by the front cover in normal operation, and extending into a space separating the front cover from the rear cover when the rear cover is moved to the rear; two arcuate frames, which are spaced apart and surround the engine in order to support actuators for moving the rear cover; the space located between the two arcuate frames being uncovered when the front and rear covers are moved to the front and rear; and wherein the two arcuate frames jointly support a series of elements forming steps which constitute a ladder for quick access to the top of the propulsion assembly.

Aircraft propulsion assembly provided with steps allowing an operator to reach the top of same

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.

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Seine Port, France

Bruna Manuela Ramos