AEROELASTIC ANALYSIS OF A TRANSONIC COMPRESSOR BLADE BASED ON FLUID-STRUCTURE INTERACTION METHOD

In order to study the effect of a transonic rotor blade static aeroelastic deformation on the aerodynamic performance, a time domain numerical simulation method for the Two-Way Fluid-Structure Interaction is applied to simulate the flow field and the solid domain of one-stage transonic compressor blades, The comparison of the aerodynamic performance and the natural frequency is analyzed in 100% rotating speed. The results show that the total aeroelastic deformation is dominated by the torsional deformation under aerodynamic and centrifugal forces. The aerodynamic force contribution to the total deformation at the leading edge is up to 20%, the flow capacity of the blade passage is enhanced and the aerodynamic characteristic map is shifted to the larger flow rate direction after the static deformation.