Investigation on damage mechanism of compressor blades in turboshaft engine induced by ice impacts at various locations

Ice causes impact damage to different positions of the compressor blade, destroys the structural integrity of the rotor structure, and then causes unbalanced failure and even causes nonlinear vibration accidents such as collision and friction, which affects the execution of helicopter tasks. To investigate the influence of impact position on the damage form and dynamic response of blades during ice impact, a dynamic model by finite element-smooth particle fluid dynamic coupling method is created. The ice impact damage experiment of the TC4 plate based on the air gun experimental platform was carried out to verify the reliability of the simulation model. The damage of compressor blades impacted by ice from different positions under static and design speed of 45000 r/min is analyzed. The research results indicate that under static conditions, the damage caused by ice impact from the leading edge blade tip to the leading edge blade root first increases and then decreases, with the maximum damage occurring at the 66.7% blade height position on the leading edge. At the design speed, the closer the impact locations are to the leaf tip, the greater the damage is, and the plastic damage, equivalent stress, and kinetic energy loss of the ice impact are lower than the blade static condition. The research conclusion can provide theoretical reference and data support for the design of structural strength and protection of compressor blades in turboshaft engines.