On the choice of parameters of device to reduce load on components of turbojet engine pressure vessels after fan blade breakage

When a fan blade breakage occures a considerable imbalance appears in the rotor. The load reduction device is introduced in one or several supports of the fan shaft. It breaks down under the certain loads, but the loads applied to the pressure vessels components and the engine fastener assembly (suspention) could be considerably reduced. The model for simulating the rotor behavior after the fan blade breakage and for selecting LRD parameters is presented.