Comparative study of tip clearance effects in compressors and turbines
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Massachusetts Institute of Technology. Gas Turbine Laboratory
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The influence of tip clearance on the lift distribution along a blade span was studied on linear compressor and turbine cascades. The wall boundary layer was removed by means of the image technique. The lift distribution in the span direction was found to be almost similar for both compressor and turbine cascades having the similar velocity diagrams. The lift acting on the blades increases toward the blade tip. The phenomena were explained theoretically by considering the velocity induced by tip vortices on the blade surface.
Description
May 1961 Also issued as: Thesis (M.S.)--Massachusetts Institute of Technology, Dept. of Mechanical Engineering, 1961 Includes bibliographical references
Date issued
1961Publisher
Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1961]
Series/Report no.
GTL report #63