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: A turbine for a turbomachine has a first rotor and a second rotor configured to pivot about an axis in two opposite directions of rotation. The first rotor includes a radially outer drum from which blades extend radially inwards. The turbine has cooling means attached relative to the outer drum. The cooling means include a support plate with at least one first orifice and a calibration plate that is attached to the support plate and located radially inside the support plate. The calibration plate has at least one second calibration orifice facing the outer drum to allow the passage of cooling air radially from the outside to the inside through the first and second orifices.

Abstract: A turbine has a first rotor and a second rotor configured to pivot about a longitudinal axis (X) according to two opposite directions of rotation. The first rotor has a radially outer drum from which bladesextend radially inwards. The first rotorand the second rotor are surrounded by a stator annular part. The stator annular partdelimits, with the drum, at least one upstream annular cavityand one downstream annular cavityseparated from each other by sealing means.

Abstract: A turbine for a turbomachine has a first rotor and a second rotor configured to pivot about an axis in two opposite directions of rotation. The first rotor includes a radially outer drum from which blades extend radially inwards. The turbine has cooling means attached relative to the outer drum. The cooling means include a support plate with at least one first orifice and a calibration plate that is attached to the support plate and located radially inside the support plate. The calibration plate has at least one second calibration orifice facing the outer drum to allow the passage of cooling air radially from the outside to the inside through the first and second orifices.

Abstract: The invention relates to a turbine engine extending longitudinally along an X axis and including a main duct in which an air stream flows, the turbine engine including at least one upstream compressor disc, at least one downstream compressor disc and a circuit for collecting air from an air stream collected in the main duct, the air collection circuit including a radial portion in which at least one air collection tube is mounted and a longitudinal portion extending between a cylindrical body and a central bore of the downstream compressor disc. The turbine engine includes a plurality of blades extending in the longitudinal portion of the air collection circuit, configured to be rotated about the X axis, in order to rotate the collected air stream.

Abstract: The invention relates to a turbine engine extending longitudinally along an X axis and including a main duct in which an air stream flows, the turbine engine including at least one upstream compressor disc, at least one downstream compressor disc and a circuit for collecting air from an air stream collected in the main duct, the air collection circuit including a radial portion in which at least one air collection tube is mounted and a longitudinal portion extending between a cylindrical body and a central bore of the downstream compressor disc. The turbine engine includes a plurality of blades extending in the longitudinal portion of the air collection circuit, configured to be rotated about the X axis, in order to rotate the collected air stream.