Nonaxisymmetric Flow through Annular Actuator Disks: Inlet Distortion Problem

[+] Author and Article Information
W. R. Hawthorne, N. A. Mitchell

Whittle Laboratory, Engineering Department, University of Cambridge, Cambridge, England

J. E. McCune, C. S. Tan

Gas Turbine and Plasma Dynamics Laboratory, Department of Aeronautics and Astronautics, Massachusetts Institute of Technology, Cambridge, Mass.

J. Eng. Power 100(4), 604-617 (Oct 01, 1978) (14 pages) doi:10.1115/1.3446409 History: Received December 20, 1977; Online July 14, 2010


The passage of distorted flow through an annular axial compressor rotor or stator is analyzed in the actuator disk limit. In such a description the flow is steady in absolute coordinates. The resulting analysis yields an overall description of the blade row performance in the presence of inlet flow defects. The present (actuator-disk) analysis is compared successfully with Dunham’s earlier three-dimensional analysis as well as with recent experimental data. In addition, comparison with a recent theory by Greitzer, employing an alternative approach, is made. The analysis shows that at least two important distinct types of vorticity arise, the one being directly analogous to the trailing vorticity (shed circulation) of classical wing theory, and the second being analogous to the vorticity occurring in “secondary flow” theory. The latter arises directly as a result of inlet distortion. The resulting varying flow angles produce spanwise variation in blade loading, and consequent trailing vorticity (Beltrami Flow). The two types of vorticity are therefore interrelated. The static pressure field is also affected by this coupling in agreement with experiment. This problem provided a striking example for which three-dimensional and two-dimensional analyses disagree qualitatively. The vorticity as viewed in coordinates fixed in the rotor is discussed in the Addendum.

Copyright © 1978 by ASME
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