Analysis of the Influence of Blade Tip Geometry on the Aeroelastic Response of Rotors

Abstract

Using the theory of moderately deformed beams and considering the nonlinear displacement coordination relationship at the blade tip, a differential equation of rotor aeroelasticity with different blade tip shapes was established. The aeroelastic responses of rotor blades with forward convex and backward swept, backward swept and backward reversed angles were systematically analyzed. The results showed that forward swept and backward swept were beneficial for rotor vibration reduction, while downward reversed caused significant fluctuations in response, and the amplitude changes of the blade tip were different at different reverse angles, this may have adverse effects on the vertical vibration response of the aircraft body. When using a lower angle to achieve noise reduction and improve rotor aerodynamic performance, the dynamic impact caused by the complexity of flow field motion should be considered to avoid excessive vibration.