Safran Aircraft Engines

Eric Pierre Georges Lemarechal

Thierry Georges Paul Papin

Sebastien Christophe Chalaud

Cedric Zaccardi

Mohamed-Lamine Boutaleb

Antoine Robert Alain Brunet

Mathieu Simon Paul Gruber

Claire Marie Figeureu

Benjamin Bulot

Raphaël Barrier

Cyril Polacsek

Alexandre Franck Arnaud Chartoire

David Joseph Serlan

An abradable element () for a turbomachine comprises a body () formed from an abradable material and extending between a wear face () and a bottom (). The body comprises blind cavities () opening up into the wear face and filled in with a material with a colour different from the colour of the material forming the body of the element () to form wear indicators of the wear face () of the element ().

Abradable turbomachine element provided with visual wear indicators

A stator vane including a vane root, a vane tip, a leading edge extending between the root and the tip, the leading edge having a serrated profile having a succession of teeth and of troughs each having an amplitude and a thickness, wherein a series of at least three teeth and three consecutive troughs starting from the vane root and/or from the vane tip have a growing amplitude and/or thickness.

Modulation of vane end serrations

A guide vane for a dual flow aircraft turbine engine, the aerodynamic part of the vane including an inner duct for lubricant cooling extending in a main direction and being partly bounded by a pressure side wall and a suction side wall of the vane. A heat conduction matrix is lodged in the duct, and presents main heat transfer wings extending parallel to the direction, and laid out in staggered rows.

Output director vane for an aircraft turbine engine, with an improved lubricant cooling function using a heat conduction matrix housed in an inner duct of the vane

A guide vane for a dual flow aircraft turbine engine includes an aerodynamic part. The aerodynamic part includes an inner duct for lubricant cooling extending in a main direction and being partly bounded by a pressure side wall and a suction side wall of the vane. The aerodynamic part is embodied as a single piece, and includes heat transfer fins arranged in the duct expanding substantially parallel to a direction of the duct. The fins are spaced from each other depending on the direction of the duct and a transversal direction of the vane, so that at least some of the fins are arranged substantially staggered.

Outlet guide vane for aircraft turbine engine, presenting an improved lubricant cooling function

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Alfortville, France

Eric Pierre Georges Lemarechal