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The Effect of Hub Leakage Flow in a Transonic Compressor Stator FREE

[+] Author Affiliations
Udai K. Singh, Robert B. Ginder

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

Paper No. 98-GT-424, pp. V001T01A099; 11 pages
doi:10.1115/98-GT-424
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 effect of hub leakage flow on the performance of a transonic fan stator has been investigated numerically using the NEWT unstructured grid Navier-Stokes solver. The experimental configuration which has been modelled has two leakage flow paths: the first being a channel under the stator platform starting in the rotor-stator cavity upstream of the blade leading edge and rejoining the main flow downstream of the blade trailing edge; the second channel is in the form of a small gap between adjacent stator hub platforms, which joins up with the first channel. The experimental results indicate a severe corner separation in the stator hub region. Predictions with no leakage path considerably underestimate this corner separation. When the under-platform channel is modelled the corner stall becomes much worse than measured but it is considerably reduced when the inter-platform gap is included.

Copyright © 1998 by ASME. © British Crown Copyright 1997/DERA. Published with the permission of the controller of Her Britannic Majesty’s Stationery Office.
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