Angular stator sector for a turbomachine compressor comprising a brush seal

A turbomachine compressor, comprising:

• a stator formed from an angular stator sector or from a plurality of angular stator sectors, comprising:
• an outer shroud and an inner shroud arranged coaxially one inside the other, and
• at least one vane extending radially between the outer shroud and the inner shroud and connected to the outer shroud and the inner shroud by radial ends of the at least one vane,
• with the inner shroud comprising at least one brush seal forming an obstacle to the recirculation of the downstream gases upstream of the inner shroud,
• with the turbomachine compressor further comprising:
• a downstream rotor platform located immediately downstream of the inner shroud of the angular stator sector and/or an upstream rotor platform located immediately upstream of the inner shroud of the angular stator sector, and
• a rotor shroud of the turbomachine compressor connected to the downstream rotor platform and/or the upstream rotor platform,
• said at least one brush seal being fastened to the inner shroud of the angular stator sector and extending in contact with the downstream rotor platform and/or with the upstream rotor platform and/or with the rotor shroud, wherein
• the inner shroud of the angular stator sector comprises a first brush seal fastened on a downstream axial end of the inner shroud, the first brush seal extending from the inner shroud to the downstream rotor platform in contact with a radial outer end of the downstream rotor platform.