Abstract: An acoustic attenuation panel for a turbojet engine nacelle is provided by the present disclosure. The panel includes at least one alveolar core disposed between at least one internal skin and at least one external skin. In one form, the alveolar core includes a plurality of alveoli having a helical-shaped cavity along an axis in a direction normal to at least one internal skin and at least one external skin.

Abstract: An acoustic attenuation panel for a turbojet engine nacelle is provided by the present disclosure. The panel includes at least one alveolar core disposed between at least one internal skin and at least one external skin. In one form, the alveolar core includes a plurality of alveoli having a helical-shaped cavity along an axis in a direction normal to at least one internal skin and at least one external skin.

Abstract: A suspension part for mounting a turbojet engine includes two ends equipped with two elements, juxtaposed in a widthwise direction of the suspension part, for fixing the suspension part to the fixed structure. The ends are shaped into pairs of yokes respectively flanking connecting rods and each including fixing elements and a bearing of a journal of a connecting rod which bearing is situated underneath a fixing element. The suspension part also includes slots passing through the two ends of the suspension part and running between the yokes without running over a central portion of the suspension part. Each of the yokes has an upper portion with an additional thickness located on an inside of each of the yokes.

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: A jet engine suspension includes a master component for attachment, fixed to an aircraft pylon. In the event of breakage of the master component and in the situation where the fixing screws are no longer able to transmit force, a peg is provided which resists transmitted loads such that the master component collapses until an upper shoulder rests on the pylon and supports the master component. The peg is free of dynamic stress in normal service and there is absolutely no risk of it cracking in fatigue.

Abstract: The invention concerns a suspension part (1) comprising ends supporting connecting rods (8 and 9) articulated to a turbojet engine (3) which is constructed such that the ends form a pair of yokes (5) separated by a slot (19) bisecting the part (1) over part of its length so as to stop fatigue crack propagation (20). The fixing elements (11) comprising lock bolts (13) are arranged in enlarged portions (15) of the yokes (5) which extend above the connecting rods (8) and (9), thereby ensuring static resistance of the yokes (5) when the counterpart has given way. Said arrangement also reduces cantilever between the fixing elements (11) and the connecting rod (8) and (9).

Abstract: A jet engine suspension comprises a master component for attachment, fixed to an aircraft pylon. If it breaks and if the situation arises where the fixing screws are no longer able to transmit force, a peg takes over: the master component collapses until an upper shoulder rests on the pylon and supports this component. The peg is free of dynamic stress in normal service and there is absolutely no risk of it cracking in fatigue.