Research on Dynamic Response Law of an Aeroengine Rotor Under Impact Load

To study the dynamic response law of aviation engine rotor under impact load, this paper takes a simulated power turbine rotor that well reflects the real rotor dynamic characteristics as the research object, simulates the impact load conditions when the carrier-based aircraft landing, conducts research on the vibration characteristics and dynamic response of the aviation engine rotor, and reveals the dynamic response law of rotor under large impact loads. An experimental method for conducting dynamic response research on a vibration and impact test table was proposed. A high-speed motor was used as the driving source to conduct rotor vibration characteristics tests under different impact load sizes, impact directions, and impact pulse widths at different speeds. The dynamic response of the rotor under different test conditions was obtained, and the influences of impact load size, impact direction, and impact pulse width on the dynamic response of aero-engine rotor were revealed. This paper verifies the feasibility of the experimental method, and provides technical support and reference for dynamic testing of the same type of rotor under impact load, which has important engineering application value. The results show that the dynamic response of the rotor increases with the magnitude of the impact load, the vertical dynamic response of the rotor is greater than the horizontal dynamic response at the instant of being subjected to the impact load. Besides, the dynamic response of the rotor under axial impact is greater than that under vertical impact at the same rotational speed and impact load size. Furthermore, within a certain range, the dynamic response of the rotor at the instant of impact decreases as the pulse width increases at the same rotational speed and impact load.