FIELD: machine building.
SUBSTANCE: invention relates to an axial compressor of the turbine engine, comprising: a stator with an annular near the blades (32) of the stator extending in the radial direction, an inner hub (36) located on the inner ends of the blades (32) of the stator, a rear brush seal (40) located on the inner hub (36) which comprises a rotation profile passing in a substantially axial direction. The brush seal comprises bristles which pass in a substantially axial direction. The compressor also comprises a rotor with an annular sealing surface (42) having generally a cylindrical or truncated cone located on the rear side of the blades (32) of the stator and which cooperates with a brush seal (40) to provide a seal between the inner hub (36) and the rotor. The annular surface (42) encircles the brush seal (40), so that the pressure at the outlet of the brush seal (40) tends to push the seal against the annular surface (42).
EFFECT: invention provides increased efficiency and service life of the brush seal, increasing the compactness of the compressor.
15 cl, 4 dwg
