The influence of tip clearance on stall limits of a rectilinear cascade of compressor blades
Author(s)Khabbaz, Ghassan R. (Ghassan Raji)
Massachusetts Institute of Technology. Gas Turbine Laboratory
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An experimental study of the influence of tip clearance on the stall limits of compressor blades was conducted on a two dimensional rectilinear cascade. By using the mirror and image technique the end wall boundary layer in the gap was dispensed with. The clearance was found to relieve the pressure gradient and to retard stalling. The loading on the blade near the slot was found to be higher than that at a distance further along.
August 1959Also issued as: Thesis (M.S.)--Massachusetts Institute of Technology, Dept. of Mechanical Engineering, 1959Includes bibliographical references (leaves 20-21)
Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, 
GTL report #54