Unsteady aerodynamic response and aeroelastic stability of oscillating compressor cascade

An accurate and efficient numerical method was developed for aeroelastic analysis of turbomachinery blading in unsteady transonic flows.The unsteady Reynolds-averaged Navier-Stokes equation with Spalart-Allmaras turbulence model was solved with an implicit dual-time stepping technique.The blade passages were discretised using finite volume method with multi-block.The unsteady aerodynamic responses and the aeroelastic stability of the 10th standard configuration undergoing bending blade vibration were calculated in subsonic and transonic flows.The effects of flow conditions,reduced frequency and inter-blade phase angle on cascade aeroelastic stability were analyzed.The results indicate that the shock destabilizes the cascade and the influence of inter-blade phase angle is enforced under higher reduced frequency.