US 11,988,107 B2
Method for manufacturing a housing for a turbine engine and tools for the implementation thereof
Vincent Pascal Fiore, Moissy-Cramayel (FR); Clémentine Arnold, Moissy-Cramayel (FR); Clément Bourolleau, Moissy-Cramayel (FR); Thomas Dupays, Moissy-Cramayel (FR); and Serge Domingues, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 17/622,637
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Jun. 26, 2020, PCT No. PCT/FR2020/051114
§ 371(c)(1), (2) Date Dec. 23, 2021,
PCT Pub. No. WO2020/260835, PCT Pub. Date Dec. 30, 2020.
Claims priority of application No. 1907058 (FR), filed on Jun. 27, 2019.
Prior Publication US 2022/0268175 A1, Aug. 25, 2022
Int. Cl. F01D 25/24 (2006.01); B29D 23/00 (2006.01)
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
OG exemplary drawing
 
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.