Safran Aircraft Engines

Pierre-Hugues Ambroise Maxime Victor Retiveau

Damien Bernard Emeric Guegan

Sébastien Claude Cochon

Jonathan Evert Vlastuin

Mickael Cavarec

Prasaad Cojande

A variable-pitch stator blade includes an airfoil having a central portion with a first chord and a first skeleton line delimited by a leading edge and a trailing edge. An end portion has a second chord and a second skeleton line delimited by the leading edge and a downstream limit. A skeleton angle at a first length Iof the first chord is defined by a function G(), and the skeleton angle at a second length lof the second rope being chord is defined by a function G(). The absolute value of the average increase Aof G′() between the leading edge and the downstream limit is greater than the absolute value of the average increase Al of Gl′() between the leading edge and a point P, wherein the first length Icorresponds to the total length of the second chord.

Variable-pitch stator vane for an aircraft turbine engine

A vane stage with a longitudinal axis designed to be fitted in a turbine engine compressor. The van stage has an annular row of mobile vanes arranged upstream from an annular row of stator vanes. The annular row of stator vanes has a radially internal annular platform bearing radial blades, an upstream annular portion of which is arranged upstream from the blades and is surrounded radially outwards by a downstream annular portion of an annular platform of the upstream row of mobile vanes. The upstream annular portion of the annular platform of the annular row of stator vanes has a radially external annular face from which fins extend, which are distributed around the longitudinal axis and extend radially outwards towards the downstream annular portion of the platform of the annular row of mobile vanes.

Air-gap fins for a turbine engine compressor

A vane configured to be placed with a plurality of identical vanes so as to form a vane wheel for an aeroengine, the vane wheel defining an axis, the vane having an airfoil presenting a leading edge and a trailing edge, the leading-edge curve describing the shape of the leading edge of the airfoil in a view perpendicular to the airfoil presenting at least one leading-edge undulation, said at least one leading-edge undulation extending over less than 30% of a length of the airfoil from the first end of the airfoil.

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Moissy-Cramayel, France

Pierre-Hugues Ambroise Maxime Victor Retiveau