Lifting-line theory for subsonic axial compressor rotors
Name
09677041.pdf
Size
1.69 MB
Format
Adobe PDF
Checksum (MD5)
63cc1d9551ae2f18c5cef75060f6770c
Author(s)
McCune, James E. (James Elliot)
Dharwadkar, Shashikant Prabhakar
Date Issued
1972
Publisher
Cambridge, Mass. : Gas Turbine Laboratory , Massachusetts Institute of Technology, [1972]
Series/Report no.
GTL report #110
Abstract
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)
Persistent DSpace Link
