Abstract: A tool attachment for installing key-locking inserts, and a kit including such a tool attachment. For installing the key-locking insert, which is configured to be locked by a key, the tool attachment can be mounted on a power head, and connected to a pneumatic power supply, and includes a tightening torque transmission device, tightening the insert, and, in a casing, a key striker device configured to crimp the key onto the insert when crimping pressure is applied to the key by the pneumatic power supply. The striker device includes plural plates that are substantially perpendicular to the tightening axis. Crimping pressure applied suddenly to the plates inside the casing drives the key striker device and to crimp the keys. The tool attachment does not include moving mechanical parts, and is highly reliable.

Abstract: The invention relates to a rotation-locking device of a sector of rectifier blades (5) mounted in a sector of the turbojet housing. A sector of blades comprises a support base (3). A housing sector comprises two recesses perpendicular to the axis of the housing, each receiving an edge (34-1, 34-2) of the support base. At one and the same axial end of the housing sector, each recess opens out into a seat (30-1, 30-2) defining an axial face (32-1). The device comprises an axial stop (26) adapting itself on each side in the seats (30-1; 30-1) of the two recesses, and once the complementary sector of the housing is installed and during operation of the turbojet, bearing on the axial faces (32-1) under the thrust of the complementary sector of rectifier blades in order to provide rotation locking.

Abstract: The invention relates to a rotation-locking device of a sector of rectifier blades (5) mounted in a sector of the turbojet housing. A sector of blades comprises a support base (3). A housing sector comprises two recesses perpendicular to the axis of the housing, each receiving an edge (34-1, 34-2) of the support base. At one and the same axial end of the housing sector, each recess opens out into a seat (30-1, 30-2) defining an axial face (32-1). The device comprises an axial stop (26) adapting itself on each side in the seats (30-1; 30-1) of the two recesses, and once the complementary sector of the housing is installed and during operation of the turbojet, bearing on the axial faces (32-1) under the thrust of the complementary sector of rectifier blades in order to provide rotation locking.