Importance

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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). In order to avoid ice forming on the guide vanes, and also in order to avoid blade tip clearance vortices, at least one of said guide vanes (103) includes an internal cavity (106) with a hot air inlet (107) for deicing the guide vane (103), and the internal cavity (106) presents a first outlet passage (108) towards a trailing edge (112) of the guide vane (103) for injecting an air jet (114) into a boundary layer (115) adjacent to the casing (101) upstream from the blades (105) of the rotor (104).

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First Claim