Abstract: The invention relates to a twelve-hour structure for a thrust reverser, that comprises a half beam (1) capable of holding a reverser half cowling and including a plurality of hinge yokes (9c) for rotatingly mounting said half beam (1) on a nacelle-holding mast. The half beam (1) is at least partially made of a composite material.

Abstract: The invention relates to a method for joining a first acoustic panel (2), having a cellular structure of the honeycomb type, with a second acoustic panel (2), wherein said method comprises the steps of: inserting at least one mandrel, (5, 8) having a shape adapted to the cells (3), into at least one cell (3) located in the vicinity of a junction edge (6) of the acoustic panel; passing a roller (12) on said junction edge of the acoustic panel; joining the junction edge of the acoustic panel together with a junction edge (6?) of the second panel and connecting the same by applying a linking means.

Abstract: The invention relates to a twelve-hour structure for a thrust reverser, that comprises a half beam (1) capable of holding a reverser half cowling and including a plurality of hinge yokes (9c) for rotatingly mounting said half beam (1) on a nacelle-holding mast. The half beam (1) is at least partially made of a composite material.

Abstract: The invention relates to an effort recovery structure (101) of a connecting strut for attaching a turboreactor to the wing system of an aircraft. Said structure comprises a first lateral block (102) and a second lateral block (103) to be attached to the wing system of the aircraft, and a spigot fastener to be attached to the turboreactor, said lateral blocks (102, 103) surrounding an essentially long central plate (104) following the main axis (105) of the structure (101). The central plate (104) is connected to the spigot fastener and is produced from a metal or an alloy that can resist a temperature of at least 1000° C. over a period of at least 15 minutes, such as to recover the static and dynamic efforts generated by the turboreactor according to the main axis (105). The invention also relates to a connecting strut for attaching a turboreactor to a wing system of an aircraft, comprising such a primary structure (101).

Abstract: The invention relates to a method for joining a first acoustic panel (2), having a cellular structure of the honeycomb type, with a second acoustic panel (2), wherein said method comprises the steps of: inserting at least one mandrel, (5, 8) having a shape adapted to the cells (3), into at least one cell (3) located in the vicinity of a junction edge (6) of the acoustic panel; passing a roller (12) on said junction edge of the acoustic panel; joining the junction edge of the acoustic panel together with a junction edge (6?) of the second panel and connecting the same by applying a linking means.

Abstract: A device for centering a component positioned inside and rotationally secured at its end to a turbine hollow shaft positioned in a gas turbine engine. The device includes a sheath enclosing and solidly joined to the component, and an elastic ring interposed between the sheath and the shaft. The ring includes a plurality of pairs of opposed shoes extending radially outwardly therefrom and configured to radially expand so as to extend against an inner portion of the shaft. The shoes include thin, elastic cylindrical walls having an external diameter configured slightly less than the internal diameter of the shaft prior to assembly onto the shaft, and arranged to expand to the inner wall of the shaft when assembled thereon.

Abstract: A device for centering a tube component positioned inside and rotationally secured at its end to a turbine hollow shaft positioned in a gas turbine engine. The device includes a sheath enclosing and solidly joined to the tube component, and an elastic ring interposed between the sheath and the shaft. The ring includes a plurality of pairs of opposed shoes extending radially outwardly therefrom and configured to radially expand so as to extend against an inner portion of the shaft. The shoes include thin, elastic cylindrical walls having an external diameter configured slightly less than the internal diameter of the shaft prior to assembly onto the shaft, and arranged to expand to the inner wall of the shaft when assembled thereon.

Abstract: The housing is heated or cooled to adjust its diameter and, in particular, the play between the tips of the rotor blades and the housing. The apparatus consists of networks of tubes (1) covering complementary portions of the circumference of the housing and consisting of a pair of distributors (3) and parallel tubes (2) between said distributors, said tubes (2) being alternately connected to one or other of the distributors and provided with apertures to blow the gas onto the housing. The counter-flow circulation in the tubes (2) makes it possible to supply both gas that has been greatly heated by traveling a considerable distance through the tubes (2) and cooler gas that has traveled less far in other tubes (2) to any point on the housing, thereby balancing out the heat applied to every portion of the housing.