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Measurement and Calculation of the Three-Dimensional Flow in Axial Compressor Stators, With and Without End-Bends PUBLIC ACCESS

[+] Author Affiliations
C. J. Robinson, J. D. Northall

Rolls-Royce plc, Derby, UK

C. W. R. McFarlane

Cranfield Institute of Technology, Cranfield, UK

Paper No. 89-GT-6, pp. V001T01A003; 11 pages
doi:10.1115/89-GT-6
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

This paper presents results from tests of two stators, one conventional and one with end-bends, operating at low-speed in the buried stage environment of the Cranfield, 4-stage research compressor (LSRC). The aerofoil velocity distributions are modelled on those of a high speed, 10 stage, high pressure compressor with ‘supercritical’ blading, and the stators were cantilevered with clearances of 1.8% of annulus height. The test results are compared with predictions from the Moore Elliptic Flow Program (MEFP) which solves the full, three-dimensional, Navier-Stokes equations with a pressure correction algorithm. The calculation results capture the essential physics of the viscous flow in these two bladerows. The calculated deviations agree well with experimental data across the blade spans, including the near hub-region, which is dominated by the clearance flow. The calculated, radial profiles of loss are in reasonable agreement with experiment, although the magnitude of loss is over-predicted.

Copyright © 1989 by ASME
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