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The Interaction Between the Axial Compressor and the Downstream Distorting Component FREE

[+] Author Affiliations
Guo-Cai Tang

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

Paper No. 90-GT-209, pp. V001T01A062; 7 pages
doi:10.1115/90-GT-209
From:
  • ASME 1990 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 1: Turbomachinery
  • Brussels, Belgium, June 11–14, 1990
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7904-7
  • Copyright © 1990 by ASME

abstract

An investigation is presented of the interaction between a compressor and a downstream distorting component, which is of increasing importance for modern aircraft turbine engines with compact size. The prediction is based on a time–marching method for compressible flow and large perturbation. The results show that the flow field of a compressor is modified by the interaction between the compressor and the downstream distorting component. Nonuniformity in the exit static pressure, maximum distortion at the last blade row implying possible critical source for instability are characteristic of the flow field with downstream distortion. A matching map is introduced to describe the whole flow process, giving clearer insight in the physical aspect to the influence of various factors on the propagation of the downstream distortion. The spacing between the compressor and the downstream distorting component is shown to have an influence of exponential type on the distortion at every axial position. The variation of the distortion with distortion coefficient is basically linear. Steeper characteristics of the compressor will produce stronger attenuation of the distortion. Compressors of multistages have an effect similar to the steeper characteristic.

Copyright © 1990 by ASME
Topics: Compressors
This article is only available in the PDF format.

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