Unsteady 3D Flow in a Single-Stage Transonic Fan: Part II — Unsteady Stator Exit Flow Field PUBLIC ACCESS

[+] Author Affiliations
M. A. Cherrett, J. D. Bryce, R. B. Ginder

Defence Research Agency, Pyestock, Farnborough, UK

Paper No. 94-GT-224, pp. V001T01A083; 9 pages
  • ASME 1994 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 1: Turbomachinery
  • The Hague, Netherlands, June 13–16, 1994
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7883-5
  • Copyright © 1994 by ASME


Detailed unsteady aerodynamic measurements have been taken in a single-stage transonic fan with a very high stage-hub loading. 2D dynamic yawmeter probes, capable of measuring mean levels and fluctuations in stagnation pressure, static pressure and yaw angle have been traversed at rotor exit and downstream of the stator, along with several types of pneumatic 3D probe. Part I* describes measurements taken at rotor exit. This paper, Part II, describes measurements taken at stator exit when the fan was operating at near peak efficiency, on the design speed characteristic. The measurements indicate the effects of rotor-stator interaction on the development of the viscous endwall-corner flows at the hub and casing. In addition, they illustrate that significant changes in stagnation pressure level occur within much of the stator exit flow field during the rotor passing cycle.

Copyright © 1994 by ASME
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