A compressor stage , in particular for a bypass flow engine for aircraft, comprising: - a fan rotatable about a rotation axis (X); and - a plurality of stator blades , which are distributed in the peripheral direction and are arranged downstream of the fan , wherein the stator blades each extend from a radially inner stator hub to a radially outer external housing , wherein an angle of inclination (α), which is a lean angle, of a respective stator blade is variable, wherein the stator blades , in each case in a blade portion bordering the external housing , have an angle of inclination (α) with a value of less than 30° and, in at least one radially further inwardly located region, have an angle of inclination (α) with a value differing therefrom, wherein the stator blades , in each case viewed from radially inwards to radially outwards, have a radially inner blade portion , a radially outer blade portion and the radially outermost blade portion bordering the external housing , and wherein the angle of inclinations (α) of the directly successive blade portions each differ from one another, specifically in such a way that the radially outer blade portion is inclined to a greater extent compared to the radially inner blade portion and the radially outermost blade portion is inclined to a lesser extent than the radially outer blade portion , wherein, in the radially inner blade portion , there is provided an angle of inclination (α) with a value of less than 30°, characterised in that in the radially outer blade portion there is provided an angle of inclination (α) with a value of between 40° and 70°, both inclusive. - a fan rotatable about a rotation axis (X); and - a plurality of stator blades , which are distributed in the peripheral direction and are arranged downstream of the fan , wherein the stator blades each extend from a radially inner stator hub to a radially outer external housing , wherein an angle of inclination (α), which is a lean angle, of a respective stator blade is variable, wherein the stator blades , in each case in a blade portion bordering the external housing , have an angle of inclination (α) with a value of less than 30° and, in at least one radially further inwardly located region, have an angle of inclination (α) with a value differing therefrom, wherein the stator blades , in each case viewed from radially inwards to radially outwards, have a radially inner blade portion , a radially outer blade portion and the radially outermost blade portion bordering the external housing , and wherein the angle of inclinations (α) of the directly successive blade portions each differ from one another, specifically in such a way that the radially outer blade portion is inclined to a greater extent compared to the radially inner blade portion and the radially outermost blade portion is inclined to a lesser extent than the radially outer blade portion , wherein, in the radially inner blade portion , there is provided an angle of inclination (α) with a value of less than 30°, characterised in that in the radially outer blade portion there is provided an angle of inclination (α) with a value of between 40° and 70°, both inclusive. <EOS>