Propagation of Steady Circumferential Distortion Through an Axial Compressor Rotor PUBLIC ACCESS

[+] Author Affiliations
Zhang Hui Min, Hu Jun

Nanjing Aeronautical Institute, Nanjing, The People’s Republic of China

Paper No. 85-IGT-81, pp. V001T02A031; 5 pages
  • ASME 1985 Beijing International Gas Turbine Symposium and Exposition
  • Volume 1: Aircraft Engine; Turbomachinery
  • Beijing, People’s Republic of China, September 1–7, 1985
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7942-9
  • Copyright © 1985 by ASME


In this paper, a time marching method is proposed to predict the propagation of steady inlet circumferential distortion through an axial flow compressor rotor (or stator). This method also adopt the “Semi-actuator disk” concept to replace the rotor. It is assumed that the flow fields outside of the disk are described by a set of ideal, compressible and unsteady quasi-linear partial differential flow equations. Furthermore, the unsteady response of rotor is also taken into account. This method can be easily developed to a stage or extended to investigate the effect of transient disturbance on the stability of a compressor. Through numerical experiments, it has been found that distortion amplitude, rotation of the rotor, the chord length and especially the characteristic curves of the blade row have crucial effect on the attenuation behavior of the rotor.

Copyright © 1985 by ASME
Topics: Compressors , Rotors
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