Asymmetric inlet flow in axial turbomachines
Name
09162313.pdf
Size
3.44 MB
Format
Adobe PDF
Checksum (MD5)
ed95c6ed16e2ea810d5ad172ddded5f9
Author(s)
Seidel, Barry S. (Barry Stanley)
Date Issued
1959
Publisher
Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, 1959
Series/Report no.
GTL report #51
Abstract
A modified actuator disc analysis is made which, through an improved prediction of the blade forces, attempts to give closer correspondence with experiment than the previous theory. The fluid is assumed inviscid and incompressible. Perturbations to the two-dimensional flow through an isolated blade row are considered. The steady flow equations of motion and continuity are linearized. According to experiments conducted on an isolated compressor rotor, the present theory offers an improvement, compared to previous theory, in the prediction of distortion attenuation, effects of flow rate, and effects of varying chord/spacing ratio.
Description
May 1959
Includes bibliographical references (leaves 53-55)
Persistent DSpace Link
