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Simulating the Multi-Stage Environment for Single-Stage Compressor Experiments FREE

[+] Author Affiliations
J. M. M. Place, M. A. Howard

Rolls-Royce plc, Derby, UK

N. A. Cumpsty

University of Cambridge, Cambridge, UK

Paper No. 95-GT-187, pp. V001T01A046; 12 pages
doi:10.1115/95-GT-187
From:
  • ASME 1995 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 1: Turbomachinery
  • Houston, Texas, USA, June 5–8, 1995
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7878-1
  • Copyright © 1995 by ASME

abstract

The performance of a single-stage low-speed compressor has been measured both before and after the introduction of certain features of the multi-stage flow environment. The aim is to make the single-stage rig more appropriate for developing design rules for multi-stage compressors. End-wall blockage was generated by teeth on the hub and casing upstream of the rotor. A grid fitted upstream produced free-stream turbulence at rotor inlet typical of multi-stage machines and raised stage efficiency by 1.8% at the design point. The potential field that would be generated by blade rows downstream of an embedded stage was replicated by introducing a pressure loss screen at stage exit. This reduced the stator hub corner separation and increased the rotor pressure rise at flow rates below design, changing the shape of the pressure-rise characteristic markedly. These results highlight the importance of features of the flow environment that are often omitted from single-stage experiments and offer improved understanding of stage aerodynamics.

Copyright © 1995 by ASME
Topics: Compressors
This article is only available in the PDF format.

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