Calculation of Blade-profile Icing and Analysis of Flow Field

Abstract

The icing of the blade will change its original aerodynamic shape and affect its aerodynamic characteristics. The FENSAP-ICE software is used to compare and verify the numerical calculation results of icing on NACA0012 airfoil with the experimental results. The two-dimensional icing calculation of the compressor inlet guide vane profile is carried out, and the numerical calculation results of flow field are analyzed. The results show that the aerodynamic effect of glaze ice on the blade profile is greater than that of rime ice, the aerodynamic characteristics of the blade profile are mainly affected by the upper separation vortex in the separation zone, the upturned glaze ice on the leading edge of blade profile causes the tailing separation area to expand, and the strong separation vortex can increase the pressure loss of the icing blade profile.

Keywords

• fensap-ice
• inlet guide vane
• two-dimensional icing shape
• icing typical factor
• flow field analysis