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A Comparison of Measured and Predicted Unsteadiness in a Transonic Fan FREE

[+] Author Affiliations
Udai K. Singh, Graham C. Smith

Defence Evaluation and Research Agency, Pyestock, Farnborough, Hampshire, United Kingdom

Paper No. 98-GT-274, pp. V001T01A074; 10 pages
doi:10.1115/98-GT-274
From:
  • ASME 1998 International Gas Turbine and Aeroengine Congress and Exhibition
  • Volume 1: Turbomachinery
  • Stockholm, Sweden, June 2–5, 1998
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7862-0
  • Copyright © 1998 by ASME. © British Crown Copyright 1997/DERA. Published with the permission of the controller of Her Britannic Majesty’s Stationery Office.

abstract

The two dimensional, viscous, non-linear unsteady code UNSFLO has been used to model a highly loaded transonic fan stage along a mid-span section. This paper examines the results of this unsteady calculation, and compares with time resolved measurements taken on a continuous flow test rig. The main features of the time resolved experimental data are shown to be captured by the calculation. Comparison of losses for steady and unsteady calculations show that the stator loss is significantly increased by the blade row interaction effects. The origin of static pressure fluctuations within the stator passage has also been examined.

Copyright © 1998 by ASME. © British Crown Copyright 1997/DERA. Published with the permission of the controller of Her Britannic Majesty’s Stationery Office.
This article is only available in the PDF format.

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