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The Supersonic Axial Inlet Component in a Compressor FREE

[+] Author Affiliations
F. A. E. Breugelmans

von Karman Institute for Fluid Dynamics, Belgium

Paper No. 75-GT-26, pp. V01AT01A025; 8 pages
doi:10.1115/75-GT-26
From:
  • ASME 1975 International Gas Turbine Conference and Products Show
  • Volume 1A: General
  • Houston, Texas, USA, March 2–6, 1975
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7976-4
  • Copyright © 1975 by ASME

abstract

A prototype rotor has been designed to investigate the supersonic axial component at the inlet face of a compressor. A flexible inflatable nozzle is installed in the inlet duct in order to simulate a continuously variable inlet Mach number up to 1.5. A relative inlet Mach number of 2.4 was achieved at 90 percent of the design speed. The transition from the subsonic to the supersonic axial component is explored. A blade failure prevented completion of the research on the dynamic response of the compressor to throttle valve, speed and inlet nozzle variations.

Copyright © 1975 by ASME
Topics: Compressors
This article is only available in the PDF format.

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