Abstract: Unbalanced mass effects can occur at the low pressure compressor (5) of an aircraft engine. Stiffeners (20) are proposed to increase the stiffness of the assembly and therefore reduce possible cracks due to accidental unbalanced masses, one end (22) of the stiffener can be fixed to the engine casing (7) at the structural arm (10), and the other end (32) can be fixed to the compressor (5), preferably at the upstream face of the third guide vane (RD3). Advantageously, the stiffeners (20) are made of two parts fixed to each other; their manufacturing is optimized to limit the additional weight due to their presence.

Abstract: The system enables an increase in the guidance length of the outer pivot of the vane, so that the bushing can be extracted without needing to open the stator casing. It mainly includes a bushing placed inside a bossing of the stator, the length of which is greater than the length of the bossing projecting outwards from the bossing. Thus, the contact length of the outer pivot is prolonged. The bushing is terminated at its end by a gripping hook to enable extraction of the bushing by means of a claw. It is advantageously also provided with a positioning edge.

Abstract: Unbalanced mass effects can occur at the low pressure compressor (5) of an aircraft engine. Stiffeners (20) are proposed to increase the stiffness of the assembly and therefore reduce possible cracks due to accidental unbalanced masses, one end (22) of the stiffener can be fixed to the engine casing (7) at the structural arm (10), and the other end (32) can be fixed to the compressor (5), preferably at the upstream face of the third guide vane (RD3). Advantageously, the stiffeners (20) are made of two parts fixed to each other; their manufacturing is optimized to limit the additional weight due to their presence.

Abstract: The invention concerns a turbine engine with an axis of rotation B comprising a blower casing (10) and a blower (V) with movable blades (17). A clearance lies between the internal surface of the casing and the free ends of the blades. A bearing of the blower is connected to fixed parts of the turbine engine by connections such that, in the event of a load on the blower blades, these connections break and the axis of rotation of the blower oscillates about the axis of rotation B. The casing comprises, bonded to its internal surface and over at least part of the extent of the clearance, a layer of thermoformable foam (19) placed opposite the ends of the blades (17) of the blower (V).

Abstract: The system enables an increase in the guidance length of the outer pivot (11) of the vane (10), so that the bushing (50) can be extracted without needing to open the stator casing. It mainly includes a bushing (50) placed inside a bossing (21) of the stator, the length of which is greater than the length of the bossing (21) projecting outwards from the bossing. Thus, the contact length of the outer pivot (11) is prolonged. The bushing is terminated at its end by a gripping hook (41) to enable extraction of the bushing by means of a claw. It is advantageously also provided with a positioning edge (42).