FIELD: machine building.
SUBSTANCE: invention relates to a low-pressure compressor stage of an axial turbomachine, such as a turboprop. Stage comprises rotor (12), the outer surface of which comprises two lip seals (32), each forming a radial annular rib; and a stator which includes annular row of stator blades (26) extending substantially radially; and inner shell (28) whose radial cross section includes central part (40) connected to the inner tips of blades (26), lateral part (42) extending from each side of the central part to one of two lip seals (32), respectively, thus forming a rotor with the annular cavity. Shell and rotor are configured so that the radial section of annular cavity (38) has length L1 and height H, length L1 being greater than height H, which initiates rotational movement of the air contained therein. Speed of the air reduces its pressure, which limits downstream to upstream leaks. Ends of lateral parts (42) have inner annular grooves and layers of abradable material (30) placed in the annular grooves. Invention also relates to an axial turbomachine comprising a compressor having said compressor stage.
EFFECT: invention makes it possible to reduce leakage at the compressor stage.
15 cl, 6 dwg
