A pivot load response analysis method of comprehensively considering various mechanical processes

such as impact

inertia asymmetry

and deceleration over-critical for load control of aero engine under extreme load of blades off

was established. A safety design of buffer damping support structure for the thrust support was proposed

which can affect the dynamic characteristics of the rotor system by controlling the stiffness and damping parameters of the support structure

reducing the critical speed of the rotor. Quantitative evaluation of effectiveness for the buffer damping structure was carried out by the above pivot load response analysis method. The effects of pivot load during the impact-deceleration process was proved. Results showed that the impact effect and deceleration over the critical process caused by the blade off are the main factors that threaten the bearing capacity of the supporting structure. And the use of a buffer damping pivot structure can effectively reduce the pivot of the rotor system to 20% when fan blade off appeared

making it an effective design for the safety of the support structure.