Rotor Design to Attenuate Flow Distortion—Part II: An Unsteady Thin Airfoil Cascade Analysis

[+] Author and Article Information
C. T. Savell

Theoretical Aeroacoustics, General Electric Co.

W. R. Wells

University of Cincinnati

J. Eng. Power 97(1), 37-46 (Jan 01, 1975) (10 pages) doi:10.1115/1.3445911 History: Received November 27, 1973; Online July 14, 2010


The transfer of stationary circumferential inlet distortion through a rotor is analyzed using unsteady thin airfoil cascade theory which can account for the distortion wave length, rotor chord and cascade solidity. The model consists of representing each blade by a moving doublet filament of finite length immersed in a compressible stream containing a velocity distortion. The study is limited to an unloaded, flat plate rotor. This model provides a new physical interpretation for the flow adjustments observed ahead of the rotor and for the generation of sound when an inlet distortion is imposed. The analytical results show the influence of solidity and other rotor design parameters on the distortion transfer. They are found to approach the semi-actuator disk results as the solidity tends to infinity.

Copyright © 1975 by ASME
Your Session has timed out. Please sign back in to continue.






Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In