Asymmetric Inlet Flow in Axial Turbomachines

[+] Author and Article Information
Barry S. Seidel

Gas Turbine Laboratory, Massachusetts Institute of Technology

J. Eng. Power 86(1), 18-28 (Jan 01, 1964) (11 pages) doi:10.1115/1.3675412 History: Received February 26, 1962; Online January 10, 2012


A modified actuator disk 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.

Copyright © 1964 by ASME
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