Abstract：An accurate and efficient numerical method is developed for the aeroelastic analysis of turbomachinery blading in unsteady transonic flows. The unsteady Reynolds-averaged Navier-Stokes equation with the Spalart-Allmaras turbulence model is 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 effect of the flow conditions, reduced frequency and inter-blade phase angle on the cascade aeroelastic stability is analyzed. The results indicate that the shock destabilizes the cascade and the influence of the inter-blade phase angle is enforced under the higher reduced frequency.
2012, Vol. 31 
