Theory of Turbine Cascade with Arbitrary Blade Sections

Abstract

A simple method for calculating the flow around the straight wing lattice with high camber as the case of turbine blade is here developed. In this method the wing lattice with no thickness, which is quite similar to the skeleton line of given blade section, is calculated at first. And using this result, pressure distribution around the given blade section is found by the principle of thin aerofoil theory. A numerical example shows good agreement with the experimental result.