CPC F01D 25/24 (2013.01) [B29C 66/612 (2013.01); B29C 66/919 (2013.01); B29C 66/929 (2013.01); B29L 2031/7504 (2013.01); F05D 2220/323 (2013.01); F05D 2220/36 (2013.01); F05D 2230/60 (2013.01); F05D 2300/603 (2013.01)] | 12 Claims |
1. A method for manufacturing a casing of an aircraft turbomachine, said casing comprising:
an annular shell extending about an axis and made of a composite material comprising fibres that are woven and immersed in a resin,
an annular layer comprising an abradable material arranged inside the shell, and covering a first inner annular surface of an intermediate section of the shell,
the method comprising a step of gluing the layer on the first surface, during which the casing is heated and compressed by means of a system that is present at least partially inside the casing,
wherein, prior to the heating and compression of the casing, a forming tool is mounted inside the casing and made of a first ring arranged inside the shell, and covering a second inner annular surface of an end section of the shell, and a second ring arranged inside the shell, and covering a third inner annular surface of another end section of the shell, said intermediate section being arranged between the two end sections.
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