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Aerodynamic Analysis of a Two Stage Transonic Compressor With Variable Stator Vanes FREE

[+] Author Affiliations
K.-D. Broichhausen, P. Harster

MTU München

Paper No. 90-GT-073, pp. V001T01A024; 12 pages
doi:10.1115/90-GT-073
From:
  • ASME 1990 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 1: Turbomachinery
  • Brussels, Belgium, June 11–14, 1990
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7904-7
  • Copyright © 1990 by ASME

abstract

Within the scope of a compressor research program a highly loaded two stage transonic compressor was investigated.

The submitted paper presents global information on the performance characteristics of the compressor as a whole and of the two stages as a function of the variable Stator and inlet guide vane settings. For the investigated two stage compressor a variable stator 1 is able to improve the performance to the same extent as a variable inlet guide vane.

Subsequently on the basis of L2F velocimetry, hotfilm gauges and probe traverses a more detailed view of the flow inside of the compressor is given. The main results can be summarized as follows:

In spite of high supersonic relative Mach numbers in front of rotor 1 the incidence angles change evenly from hub to tip depending on the back pressure. This is in contrast to plane cascade experience and is attributed to the bow shocks.

In the downstream rotor the shock pattern is strongly influenced by the relative position between rotor 1 and rotor 2 blades. As the glue on hotfilms on the stator 2 suction side show, the influence of the rotor 1 wakes can still be recognized in the laminar separation bubble and the turbulent boundary layer. Downstream of the compressor the mixing of the rotor wakes causes strong pitchwise gradients of total temperature.

Copyright © 1990 by ASME
Topics: Compressors , Stators
This article is only available in the PDF format.

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