Abstract: 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.

Abstract: 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.

Abstract: A centrifugal impeller having an axis of rotation extending from front to rear, and including a body extending around the axis of rotation, the body having a front portion and a rear portion of larger section than the front portion, the impeller also have blades projecting from a front face of the body, the body presenting a setback in its front face between two consecutive blades, which setback is situated at a circumferential distance from the two blades.

Abstract: 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.

Abstract: 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.

Abstract: A centrifugal impeller (18) having an axis of rotation (X) extending from front to rear, and comprising a body (20) extending around the axis of rotation (X), the body (20) having a front portion and a rear portion of larger section than the front portion, the impeller also have blades (24, 25) projecting from a front face (20a) of the body (20), the body (20) presenting a setback (30) in its front face (20a) between two consecutive blades (24, 25), which setback (30) is situated at a circumferential distance from said two blades (24, 25).