Abstract: An aircraft turbine-engine module casing including an external module casing and at least one sealing ring intended to surround a movable impeller of the module and arranged radially towards the inside with respect to the external casing. The casing includes at least one capillary heat pipe, a first end which is fixed to the sealing ring, and a second end which, opposite to the first, is fixed to a casing element arranged radially towards the outside with respect to the ring.

Abstract: A compressor shroud for an aircraft turbine engine, the shroud being arranged between two bladed rotary wheels and radially in line with a deflector, the shroud including a sealing device including one or more sealing elements, including a downstream end sealing element on which, projecting downstream, an air entraining and diverting structure is provided, designed to axially divert the discharge air issuing from the end sealing element.

Abstract: The invention relates to the field of compressors, and specifically a compressor stage (100) comprising at least a casing (101) delimiting an air passage (2), a stator (102) comprising a plurality of guide vanes (103) arranged radially around a central axis (X) in the air passage (2), and a rotor (104) suitable for rotating about the central axis (X) relative to the stator (102) and comprising a plurality of blades (105) arranged radially around the central axis (X) in the air passage (2) downstream from the guide vanes (103). Each blade (105) of the rotor (104) extends from a blade root (105a) to a blade tip (105b) further away from the central axis (X) than the blade root (105a) and presents radial clearance (j) between the blade tip (105b) and the casing (101).

Abstract: A sealing system in a cavity under the stator of a turbomachine flow path, the cavity being located between a root of a vane of the stator and a complementary rotor device, the root including two surfaces each provided with an abradable coating, the rotor device being provided with a first and a second sealing element, arranged facing the first and the second surface respectively, the first surface and the first sealing element forming a first sealing pair and delimiting a first leakage section between them, the second surface and the second sealing element forming a second sealing pair and delimiting a second leakage section between them, one of the two pairs tending towards a minimum leakage section when the other tends towards a maximum leakage section, and vice versa.