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Dual Pressure Ratio Compressor PUBLIC ACCESS

[+] Author Affiliations
Charles J. Paine

Allied-Signal Aerospace Company

Paper No. 89-GT-121, pp. V001T01A053; 6 pages
doi:10.1115/89-GT-121
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

The dual pressure ratio centrifugal compressor was conceived and developed as part of an advanced auxiliary power unit (APU) program (Ref. 1). The objective was to provide relatively low pressure bleed flow and high pressure turbine flow from a single stage centrifugal compressor.

Concept feasibility was first demonstrated by modifying and rig testing an existing centrifugal compressor. Subsequently, a second compressor (reference compressor), meeting the overall APU power section and bleed cycle pressure ratio requirements was designed and rig tested. This configuration was then scaled and tested in an APU.

Test results showed that the compressor efficiency and pressure ratio were approximately as predicted for the flow split off to the turbine (referred to as the turbine flow side). The bleed flow side vaneless diffuser experienced a strong flow separation. Mechanical problems were also encountered with the flow splitter shroud.

Although further development was indicated to correct the mechanical and aerodynamic problems encountered, the experiment provided a benchmark for the dual pressure ratio compressor concept.

Copyright © 1989 by ASME
Topics: Pressure , Compressors
This article is only available in the PDF format.

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