CPC F01D 9/041 (2013.01) [F01D 5/282 (2013.01); F01D 9/06 (2013.01); F01D 25/24 (2013.01); F05D 2220/323 (2013.01); F05D 2230/10 (2013.01); F05D 2240/128 (2013.01)] | 4 Claims |
1. A method for manufacturing a turbomachine turbine,
wherein the turbomachine turbine comprises a casing, an outer support shroud made of metal secured to the casing and defining an axial direction and a radial direction, an inner support shroud made of metal, an annular turbine nozzle including a plurality of nozzle segments made of ceramic matrix composite material forming a crown extending between the outer support shroud and the inner support shroud,
each segment including an inner platform, an outer platform and at least one airfoil extending radially between the inner and outer platforms and having a hollow profile defining an inner housing extending radially,
and the turbine further comprising, for each segment, at least one strut secured to the outer metallic support shroud and radially traversing the segment via the housing of an airfoil,
for each segment, the outer platform comprising a radially outer surface facing the outer metallic shroud and an axial stop extending in radial protrusion from the radially outer surface of the outer platform, and the outer metallic shroud comprises a radially inner surface facing the outer platform and a complementary axial stop extending in radial protrusion from the radially inner surface of the outer metallic shroud, the axial stop bearing along the axial direction against the complementary axial stop and located upstream of the complementary axial stop with respect to the direction of a stream of air intended to flow through the turbine, and a surface of the axial stop in contact with the complementary axial stop having an angle of machining with respect to a plane orthogonal to the axial direction, the angle of machining being chosen to adjust an orientation of said at least one airfoil of the segment with respect to the axial direction,
and wherein the annular turbine nozzle is formed of the ceramic matrix composite material in a first step, then the orientation of the at least one airfoil is controlled in a second step, then the angle of machining of the surface of the axial stop in contact with the complementary axial stop is determined to adjust the orientation of said at least one airfoil with respect to the outer metallic shroud in a third step, the surface of the axial stop in contact with the complementary axial stop is machined in a fourth step, and the annular turbine nozzle is assembled on the outer and inner support shrouds and on the casing of the turbine in a fifth step.
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