EFFECT OF LEADING EDGE EROSION ON THE PERFORMANCE OF TRANSONIC COMPRESSOR BLADES

Abstract

Within this paper an experimental and numerical investigation about the effect of leading edge erosion at transonic blades was performed. The measurements were carried out on a linear blade cascade in the Transonic Cascade Wind Tunnel of DLR in Cologne at two operating points with an inflow Mach number of 1.05 and 1.12. The numerical simulations were performed by ANSYS Germany. The type and specifications of the erosion for the study were derived from real engine blades and applied to the leading edges of the experimental cascade blades using a waterjet process as well as detailed modelled and meshed within the numerical setup. Numerical simulations and extensive wake measurements were carried out on the cascades to evaluate aerodynamic performance. The increase in losses was quantified to be 4 percent as well as a reduction of deflection and pressure rise was detected at both operating points.