Abstract: The present invention relates to a nozzle guide vane for a turbine, having an axis of revolution and comprising: a flange extending radially relative to the axis; —a ring seal mounted on the flange and comprising an inner face that is configured to bear an abradable element; —a ventilation cavity delimited radially on the inside by an outer face of the ring seal and downstream by an upstream face of the flange; —a baffle configured to guide an airflow toward the ventilation cavity; and—at least one through-opening formed in the ring seal and configured to put the ventilation cavity in fluidic communication with the inner face of the ring seal.

Abstract: The invention relates to a stator assembly for an aircraft turbomachine extending about an axis and including: a shroud ring, a plurality of bladed ring sectors, sliding assembly allowing relative movement between the shroud ring and each of the ring sectors, the sliding assembly including two outer annular flanges which are upstream and downstream of the shroud ring, respectively, and an inner flange of each of the ring sectors which is inserted axially between the two outer flanges, wherein each of the ring sectors includes a deflector which is supported by the inner flange of the sector and extends around the upstream annular flange of the shroud ring.

Abstract: The present invention relates to a nozzle guide vane for a turbine, having an axis of revolution and comprising: a flange extending radially relative to the axis; —a ring seal mounted on the flange and comprising an inner face that is configured to bear an abradable element; —a ventilation cavity delimited radially on the inside by an outer face of the ring seal and downstream by an upstream face of the flange; —a baffle configured to guide an airflow toward the ventilation cavity; and—at least one through-opening formed in the ring seal and configured to put the ventilation cavity in fluidic communication with the inner face of the ring seal.

Abstract: The invention relates to a stator assembly for an aircraft turbomachine extending about an axis and including: a shroud ring, a plurality of bladed ring sectors, sliding assembly allowing relative movement between the shroud ring and each of the ring sectors, the sliding assembly including two outer annular flanges which are upstream and downstream of the shroud ring, respectively, and an inner flange of each of the ring sectors which is inserted axially between the two outer flanges, wherein each of the ring sectors includes a deflector which is supported by the inner flange of the sector and extends around the upstream annular flange of the shroud ring.