Abstract: The present application relates to a compressor stator of an axial turbomachine having an inner shell formed of a plurality of annular segments arranged end to end, a layer of abradable material applied on the inner face of the shell, and an annular array of blades connected to the shell. The stator has at least one strip located in the layer of abradable material and extending from either side of the junctions between two adjacent annular segments. The inner tips of the blades have hooks mating mechanically with the strip.

Abstract: The invention relates to a mechanical assembly (1) for the field of aeronautics, including: a part (3) comprising an attachable end; a recess for receiving the part (3), said recess having a wall (2) comprising an organic matrix composite or OMC; and a sealing composite (4) including a thermoplastic or heat-curable material including 0 to 70 wt % of a filler and forming a mechanical and/or physicochemical link between the part (3) and the recess having the OMC wall (2).

Abstract: The present invention relates to a method for making a preform (1) for a composite with a thermoplastic matrix, said preform (1) comprising one or several layers of reinforcement fibers (3) sewn on a support (2) by means of at least one attachment yarn (4)and according to the TFP process, characterized in that the method comprises one or several steps for depositing a thermoplastic-resin layer (5a,5b) on the support (2) or on a layer (3) of reinforcement fibers.

Abstract: The present invention relates to a composite-material turbomachine vane (1) comprising a blade (2), wherein said vane (1) comprises a first resin (4) reinforced with long fiber and a second resin (5) reinforced with short fibers, said first and second resins being chemically compatible or identical, said long fibers (4) serving to stiffen the vane (1) and said short fibers (5) dispersed in the second resin serving to fill in the parts of the vane that are not reinforced by the long fibers (4) and giving the vane (1) its substantially final shape.

Abstract: The present invention relates to a turbomachine rectifier comprising a plurality of stator vanes (5) connecting an inner collar (4) to an outer collar (3), each of said vanes (5) comprising a blade (11) and a blade-head platform (10), comprising an intermediate piece (6) arranged between the inner collar (4) and the outer collar (3) and fastened to the outer collar (3), said intermediate piece (6) comprising openings (14) for the passage of the vane blades (11) and said vane platforms (10) resting, on one side, on the outer collar (3) and, on the other side, on the intermediate piece (6).