Abstract: A housing for an aircraft turbine engine includes an annular body extending around an axis A. The body includes a securing flange extending radially outwards at each of the axial ends thereof, and an abradable layer arranged inside the body. A method for manufacturing the housing includes a step b) of bonding the layer to the first surface, during which the housing is heated and compressed by a system present at least partially inside the housing. The method further includes, prior to step b), a step a) of mounting at least two 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 the flanges.

Abstract: A fibrous texture has the shape of a strip extending in a longitudinal direction over a determined length between a proximal portion and a distal portion and in a lateral direction over a determined width between a first lateral edge and a second lateral edge. The fibrous texture has a three-dimensional or multi-layer weaving between a plurality of layers of warp strands extending in the longitudinal direction and a plurality of layers of weft strands extending in the lateral direction, the fibrous texture including first and second longitudinal sections extending over a width from the first or second lateral edge smaller than the determined width of the fibrous texture along the lateral direction. The first and second longitudinal sections each include warp strands and weft strands constituted by carbon fibers. The fibrous texture further includes a third section present between the first and second sections.

Abstract: The invention relates to a method for manufacturing an aircraft turbine engine housing, the housing (23) comprising: —an annular shell (29) with axis A; —an annular element (24; 253, 254) attached to the inside of the shell (29), the annular element comprising a body (25) made of NIDA-type cellular material and comprising a downstream portion (252) covered with an abradable material (26), and an upstream portion (251) without abradable material, the body (25) extending in a continuous manner from the upstream portion (251) to the downstream portion (252), the method comprising: —manufacturing the annular element in the form of a continuous annular body, —cutting the annular body into segments (253, 254), —attaching the segments to the shell, and —depositing the abradable material (26) onto the inside surface (25a) of the downstream portion (252).

Abstract: A housing for an aircraft turbine engine includes an annular body extending around an axis A. The body includes a securing flange extending radially outwards at each of the axial ends thereof, and an abradable layer arranged inside the body. A method for manufacturing the housing includes a step b) of bonding the layer to the first surface, during which the housing is heated and compressed by a system present at least partially inside the housing. The method further includes, prior to step b), a step a) of mounting at least two 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 the flanges.