Angular stator sector for a turbomachine compressor comprising a brush seal
The main object of the invention is an angular stator sector ( 10 ) for a turbomachine compressor, comprising an outer shroud and an inner shroud (S) arranged coaxially one inside the other, and at least one vane (P) extending radially between the outer shroud and the inner shroud (S) and connected to the latter by its radial ends, characterized in that the inner shroud (S) comprises at least one brush seal ( 1, 2, 3 ) forming an obstacle to the recirculation of the downstream gases upstream of the inner shroud (S).
1. 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.
2. The turbomachine compressor according to claim 1 , wherein the inner shroud comprises a second brush seal on an upstream axial end of the inner shroud.
3. The turbomachine compressor according to claim 1 , wherein the inner shroud comprises a brush seal on a radial inner end of the inner shroud.
4. The turbomachine compressor according to claim 1 , wherein the inner shroud of the angular stator sector comprises a brush seal fastened on a radial inner end of the inner shroud, extending in contact with the rotor shroud, and wherein one or several lips are arranged on a radially outer portion of the rotor shroud by being axially separated from said brush seal.
5. The turbomachine compressor according to claim 1 , wherein the first brush seal and/or a second brush seal are extending from the inner shroud to the downstream rotor platform and/or the upstream rotor platform, respectively, according to a respective first angle and/or a respective second angle in relation to an axis of rotation of a turbomachine, in such a way as to form a continuous evolution of an inner wall of an aerodynamic stream at a passage between the inner shroud and the downstream rotor platform and/or at a passage between the inner shroud and the upstream rotor platform.
6. A turbomachine comprising the turbomachine compressor as claimed in claim 1 .
7. The turbomachine compressor according to claim 1 , wherein the inner shroud of the angular stator sector comprises a second brush seal fastened on an upstream axial end of the inner shroud, the second brush seal extending from the inner shroud to the upstream rotor platform in contact with a downstream axial end of the upstream rotor platform.