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Axial Compressor Response to Inlet Flow Distortions by a CFD Analysis

[+] Author Affiliations
Nikolaos Charalambous, Tiziano Ghisu, Giuseppe Iurisci, Vassilios Pachidis, Pericles Pilidis

Cranfield University, Cranfield, Bedfordshire, UK

Paper No. GT2004-53846, pp. 1637-1649; 13 pages
doi:10.1115/GT2004-53846
From:
  • ASME Turbo Expo 2004: Power for Land, Sea, and Air
  • Volume 5: Turbo Expo 2004, Parts A and B
  • Vienna, Austria, June 14–17, 2004
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 0-7918-4170-7 | eISBN: 0-7918-3739-4
  • Copyright © 2004 by ASME

abstract

The usual approach to compressor design considers uniform inlet flow characteristics. Especially in aircraft applications, the inlet flow is quite often non uniform, and this can result in severe performance degradation. The magnitude of this phenomenon is amplified in military engines due to the complexity of inlet duct configurations and the extreme flight conditions. CFD simulation is an innovative and powerful tool for studying inlet distortions and can bring this inside the very early phases of the design process. This project attempts to study the effects of inlet flow distortions in an axial flow compressor trying to minimize the use computer resources and computational time. The first stage of a low bypass ratio compressor has been analyzed and its clean and distorted performance compared outlining the principal changes due to uneven flow distribution: drop in mass flow, increase in pressure and temperature ratios, decrease in surge margin. Three different studies have then been conducted to better understand the effects of the level, the type and the frequency of the distortion.

Copyright © 2004 by ASME

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