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Modeling Tip Clearance Efects in Multi–Stage Axial Compressors FREE

[+] Author Affiliations
S. Baghdadi

Pratt & Whitney, United Technologies, West Palm Beach, FL

Paper No. 95-GT-291, pp. V001T01A077; 17 pages
doi:10.1115/95-GT-291
From:
  • ASME 1995 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 1: Turbomachinery
  • Houston, Texas, USA, June 5–8, 1995
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7878-1
  • Copyright © 1995 by ASME

abstract

A variety of techniques for simulating the effects of rotor tip clearances in multi–stage axial compressors is discussed. Proper recognition of stage coupling and re–matching effects is shown to be key to successful modeling of the overall behavior of actual engine compression systems. The application of a relatively simple 1–D unsteady row–by–row systems analysis is presented and shown to compare well to test data from several engine compressors.

Copyright © 1995 by ASME
This article is only available in the PDF format.

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