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A Test Facility for the Investigation of Steady and Unsteady Transonic Flows in Annular Cascades FREE

[+] Author Affiliations
Albin Bölcs

Federal Institute of Technology, Lausanne, Switzerland

Paper No. 83-GT-34, pp. V001T01A014; 6 pages
doi:10.1115/83-GT-34
From:
  • ASME 1983 International Gas Turbine Conference and Exhibit
  • Volume 1: Turbomachinery
  • Phoenix, Arizona, USA, March 27–31, 1983
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7951-1
  • Copyright © 1983 by ASME

abstract

A unique non-rotating aerodynamic test facility is presented. It is designed for steady and unsteady transonic flow investigations in annular cascades. The fundamental advantage of this vehicle design, compared to a linear cascade facility, is the absence of boundary disturbances in the cascade and the self-adjustment of the flow periodicity. The downstream flow conditions can therefore be adjusted by the backpressure.

The nozzle consists of a radial-axial section, in which spiral axisymetric flow is generated. With the adjustment of the total pressure and swirl angles in two separate distributors, a continuous variation of Mach number between 0<M<1,4 and flow angles between 12°<β<70° (from tangential) can be obtained.

Further regulation of the flow quantities in the two separate distributors and boundary layer suction permits a continuous spanwise variation of the velocity and flow angle in the test section.

Copyright © 1983 by ASME
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