A turbine comprising a casing and a nozzle including an outer metallic shroud (9) secured to the casing, an inner metallic shroud, and a plurality of nozzle segments (20) made of CMC forming a crown extending between the outer shroud (9) and the inner shroud, each segment including a strut (6), an inner platform, an outer platform and at least one airfoil having a hollow profile traversed by the strut (6).
For each airfoil (20), the outer platform (26) comprises an axial stop (260) extending in outward radial protrusion from the outer platform (26), and the outer metallic shroud (9) comprises a complementary axial stop (96) extending in inward radial protrusion from the outer metallic shroud (9), the axial stop (260) being upstream and axially bearing against the complementary axial stop (96), and machined with an angle of machining chosen to adjust the orientation of said at least one blade of the segment with respect to the axial direction (DA).