Abstract: In order to obtain the containment capability of the composite casing with bolted structures, the numerical analysis of the impact behavior of the bolted structures was carried out by using the simulated blade projectiles in the simulation software. It was found that: the simulated blade projectiles were rebounded impacting the 6 mm thick bolted connection structure of laminates with three different layups of [45/0/-45/90]_12S, [-45/-0/45/90]_12S and [90/45/0]_16S and metal plate at 130 m/s, 150 m/s and 165 m/s impact velocity, respectively. The simulated blade projectiles penetrated the laminates with the impact velocity of 180 m/s. As the impact velocity increases, the value of energy absorbed by the laminates during the impact process is larger, and the damage is more serious. Under the containment condition, the laminates with [45/0/-45/90]_12S layup has the best energy absorption and impact resistance ability. Under the impact of the simulated blades, a large area of fiber breakage and delamination damage occurr in the laminates, which is mainly concentrated at the blade impact location and at the chamfered corners of the mounting edges. The screws of the two middle-most bolts of the structure are subjected to high stresses during impact and plastic deformation occur.

Key words: aero-engine, impact behavior, composite casing, bolted joint structure, lay-up form