CPC F01D 25/24 (2013.01) [B29D 23/00 (2013.01); F05D 2220/323 (2013.01); F05D 2230/23 (2013.01); F05D 2240/14 (2013.01)] | 19 Claims |
1. A method for manufacturing a casing of an aircraft turbine engine, said casing comprising:
an annular body extending around an axis (A) and made of a composite material comprising fibres woven and embedded in a resin, said body comprising an annular fastening flange extending radially outwards at each axial ends thereof, and
an annular layer of abradable material arranged inside said body, and covering a first internal annular surface of an intermediate section of said body,
the method comprising a step b) of bonding the layer to the first surface, during which the casing is heated and compressed by a system present at least partly inside the casing,
the method further comprising, prior to the step b) of heating and compressing the casing, a step a) of mounting at least two shaping tools between the flanges, each of the tools being located in a circumferential area outside the body so as to exert bearing forces in opposite axial directions on these flanges.
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