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Influence of the Radial Component of Total Pressure Gradient on Tip Clearance Secondary Flow in Axial Compressors PUBLIC ACCESS

[+] Author Affiliations
Ian N. Moyle

Naval Postgraduate School, Monterey, CA

Paper No. 89-GT-19, pp. V001T01A009; 9 pages
doi:10.1115/89-GT-19
From:
  • ASME 1989 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 1: Turbomachinery
  • Toronto, Ontario, Canada, June 4–8, 1989
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7913-9
  • Copyright © 1989 by ASME

abstract

The interaction of tip leakage and the rotor passage secondary flow is examined. An analytical expression is developed which relates radial components of the total pressure gradient near the wall to the passage geometry, tip speed, skew, throughflow and wall skin friction coefficient. This expression provides a correlation with the differences observed in the passage secondary velocity patterns associated with tip clearance gaps in experimental compressors. The analysis is qualitatively supported by comparison with secondary flow velocity measurements from a small sample of published test data.

Copyright © 1989 by ASME
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