Aeroelastic Calculations on the Front Stage of an Industrial Compressor

Abstract

In the race for more efficient gas turbine compressors designs the blades are pushed to increasing aeromechanical challenges. More loaded blades decrease the allowable stresses in critical locations. Additionally, thinner airfoils tend to reduce the dynamic frequencies, increasing the flutter risks. To estimate the feasibility of a specific design unsteady calculations are being used more frequently in the industrial environment. However, validation of new emerging tools vs. in-house tools is still required in order to gain more confidence in the solutions. The proposed project aims to perform aeroelastic calculations on the first stage of a compressor rotor blade using an in-house solver. The risk to flutter will be evaluated at relevant operating conditions and at relevant mode-shapes. The results will be compared with those obtained from a commercial solver. Additionally, the forced response aerodynamic excitation for relevant resonances will also be performed. Analysis of the results with respect to the aeromechanical behaviour and mechanical integrity risks will be performed as well as an evaluation of the different solvers with respect to accuracy, calculation efficiency and industrial applicability.