Air-gap fins for a turbine engine compressor

A vane stage extending around a longitudinal axis and designed to be fitted in a turbine engine compressor, the vane stage comprising an annular row of mobile vanes arranged upstream from an annular row of stator vanes, wherein the annular row of stator vanes comprises a radially internal annular platform bearing radial blades, an upstream annular portion of which is arranged upstream from said blades and is surrounded radially outwards by a downstream annular portion of an annular platform of the upstream row of mobile vanes, wherein the upstream annular portion of the annular platform of the annular row of stator vanes comprises a radially external annular face from which fins extend, said fins 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, characterised in that the fins each comprise an intrados face and an extrados face oriented circumferentially in an identical manner to the intrados faces and extrados faces of the blades of the stator vanes.