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The Role of Tip Clearance in High-Speed Fan Stall PUBLIC ACCESS

[+] Author Affiliations
J. J. Adamczyk

NASA Lewis Research Center, Cleveland, OH

M. L. Celestina

Sverdrup Technology, Inc., Cleveland, OH

E. M. Greitzer

Massachusetts Institute of Technology, Cambridge, MA

Paper No. 91-GT-083, pp. V001T01A031; 13 pages
doi:10.1115/91-GT-083
From:
  • ASME 1991 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 1: Turbomachinery
  • Orlando, Florida, USA, June 3–6, 1991
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7898-9
  • Copyright © 1991 by ASME

abstract

A numerical experiment has been carried out to define the near stall casing endwall flow field of a high-speed fan rotor. The experiment used a simulation code incorporating a simple clearance model, whose calibration is presented. The results of the simulation show that the interaction of the tip leakage vortex and the in-passage shock plays a major role in determining the fan flow range. More specifically, the computations imply that it is the area increase of this vortex as it passes through the in-passage shock, which is the source of the blockage associated with stall. In addition, for fans of this type, it is the clearance over the forward portion of the fan blade which controls the flow processes leading to stall.

Copyright © 1991 by ASME
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