Lifting-line theory for subsonic axial compressor rotors

Abstract

The three-dimensional compressible vortex theory of an axial compressor rotor or ducted fan is extended by relating blade loading to blade geometry in the lifting-line approximation. The resulting integral equation, which is valid up to high subsonic Mach numbers, is solved for both design and off-design problems. It is shown that three-dimensional effects must be taken into account, for rotors with non-uniform spanwise loading, in order to obtain accurate predictions of flow angles and other performance parameters.