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Design and Performance of Advanced Blading for a High-Speed HP Compressor PUBLIC ACCESS

[+] Author Affiliations
R. B. Ginder

Royal Aerospace Establishment, Pyestock, Farnborough, Hants, UK

Paper No. 91-GT-374, pp. V001T01A103; 8 pages
doi:10.1115/91-GT-374
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 set of advanced blading has been designed for a 5-stage high-speed research core compressor. The blade profiles were aerodynamically-tailored using a sophisticated quasi-3D S1-S2 flow calculation system which was developed at RAE Pyestock. This system involves iteration between blade-to-blade calculations using an inviscid-viscous code, and a streamline-curvature calculation for the pitchwise-averaged throughflow. The design and measured performance of the new compressor are compared with an initial conventionally-bladed 4-stage version. The new design achieved a peak level of poly tropic efficiency approaching 91%, a substantial improvement on the initial version, but showed a shortfall in pressure ratio compared with design intent. Post-test analyses based on measured performance data are used to give further insight into this result and indicate possible improvements in the design approach.

Copyright © 1991 by ASME
Topics: Compressors , Design
This article is only available in the PDF format.

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