The effect of blade profile variations on the erosion of turbine blades subjected to flow containing particulates was analytically determined. To accomplish this end, the two-dimensional inviscid main flow field was determined for each blade passage. A semi-empirical model of erosion was combined with available experimental data to predict erosion on the blade surfaces.

Maximum erosion was found to be at the trailing edge of the stator and rotor and at the leading edge of the rotor. The trailing edge erosion of the stator and rotor was decreased as the blade exit angle was decreased. The trailing edge erosion of the stator and rotor was also decreased when the blade leading edge radius was reduced.

Reducing the degree of reaction of the turbine stage caused a change in distribution of erosion levels along the blade surface.