U.S. Patent Specifications

Abstract

A rotor for an axial flow compressor having a plurality of stages, at least one of said stages comprising a plurality of circumferentially spaced blades, and adjacent blades being of different blade section whereby one of said blades has a relatively sharp leading edge and the next adjacent blade has a relatively blunt leading edge, with the blades with blunt leading edges alternating with blades with sharp leading edges, all of said blades having leading and trailing edges terminating in the same positions respectively along the axis of flow and all of the blades having relatively sharp trailing edges.

Citation

(1959), "U.S. Patent Specifications", Aircraft Engineering and Aerospace Technology, Vol. 31 No. 8, pp. 260-260. https://doi.org/10.1108/eb033152