Lifting-line theory for subsonic axial compressor rotors
Author(s)
McCune, James E. (James Elliot); Dharwadkar, Shashikant Prabhakar![Thumbnail](/bitstream/handle/1721.1/104693/09677041.pdf.jpg?sequence=4&isAllowed=y)
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Other Contributors
Massachusetts Institute of Technology. Gas Turbine Laboratory
Metadata
Show full item recordAbstract
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.
Description
July 1972 Includes bibliographical references (leaf 25)
Date issued
1972Publisher
Cambridge, Mass. : Gas Turbine Laboratory , Massachusetts Institute of Technology, [1972]
Series/Report no.
GTL report #110