The Influence of Tip Clearance on Stall Limits of a Rectilinear Cascade of Compressor Blades

An experimental study of the influence of tip clearance on the stall limits of compressor blades was conducted on a rectilinear cascade. By using the mirror and image technique the end wall boundary layer near the clearance was dispensed with. The blade loading was maximum at a distance from the tip clearance, but the clearance was found to relieve the pressure gradient in general and to retard stalling.